Philip C. E. Jorgenson and Joseph P. Veres

Glenn Research Center, Cleveland, Ohio

William B. Wright

ASRC Aerospace Corporation, Cleveland, Ohio

Peter M. Struk

Glenn Research Center, Cleveland, Ohio

A Model to Assess the Risk of Ice Accretion Due to 

Ice Crystal Ingestion in a Turbofan Engine and its 

Effects on Performance

NASA/TM—2013-218094

November 2013
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Philip C. E. Jorgenson and Joseph P. Veres

Glenn Research Center, Cleveland, Ohio

William B. Wright

ASRC Aerospace Corporation, Cleveland, Ohio

Peter M. Struk

Glenn Research Center, Cleveland, Ohio

A Model to Assess the Risk of Ice Accretion Due to 

Ice Crystal Ingestion in a Turbofan Engine and its 

Effects on Performance

NASA/TM—2013-218094

November 2013

National Aeronautics and

Space Administration

Glenn Research Center

Cleveland, Ohio 44135

A revised and expanded version of AIAA–2012–3038, presented at the

Atmospheric and Space Environments Conference

sponsored by the American Institute of Aeronautics and Astronautics

New Orleans, Louisiana, June 25–28, 2012
Acknowledgments

This work is supported by the Atmospheric Environment Safety Technology Project (AEST) in the NASA Aviation Safety Program, 

and is in response to the Engine Icing Technical Challenge. A high level goal in that project is to provide a “First Generation Engine 

Icing Performance Degradation Parametric Simulation Capability.” The APG milestone was due on 2Q2012 and the code that was 

developed is the deliverable. We would like to thank Dr. Renato Colantonio, manager of the NASA Atmospheric Environment 

Safety Technologies (AEST) project, under the Aviation Safety Program (ASP) for supporting this work. We would also like to 

acknowledge Dr. Jen-Ching Tsao, Ohio Aerospace Institute (OAI) for his insights and analyses of the NASA/National Research 

Council of Canada (NRCC) laboratory test data analyses. We also acknowledge the help and guidance we received from Mr. Scott 

Jones at NASA Glenn Research Center in the use of the NPSS engine cycle code.

Available from

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7115 Standard Drive

Hanover, MD 21076–1320

National Technical Information Service

5301 Shawnee Road

Alexandria, VA 22312

Available electronically at http://www.sti.nasa.gov

This work was sponsored by the Fundamental Aeronautics Program 

at the NASA Glenn Research Center.

Level of Review: This material has been technically reviewed by technical management. 
A Model to Assess the Risk of Ice Accretion Due to Ice Crystal 

Ingestion in a Turbofan Engine and its Effects on Performance

Philip C. E. Jorgenson and Joseph P. Veres

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135 

William B. Wright

ASRC Aerospace Corporation

Cleveland, Ohio 44135

Peter M. Struk

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Abstract

The occurrence of ice accretion within commercial high bypass aircraft turbine engines has 

been reported under certain atmospheric conditions. Engine anomalies have taken place at high 

altitudes that were attributed to ice crystal ingestion, partially melting, and ice accretion on the 

compression system components. The result was one or more of the following anomalies: degraded 

engine performance, engine roll back, compressor surge and stall, and flameout of the combustor. 

The main focus of this research is the development of a computational tool that can estimate

whether there is a risk of ice accretion by tracking key parameters through the compression system 

blade rows at all engine operating points within the flight trajectory. The tool has an engine system 

thermodynamic cycle code, coupled with a compressor flow analysis code, and an ice particle melt 

code that has the capability of determining the rate of sublimation, melting, and evaporation through 

the compressor blade rows. Assumptions are made to predict the complex physics involved in 

engine icing. Specifically, the code does not directly estimate ice accretion and does not have 

models for particle breakup or erosion. Two key parameters have been suggested as conditions that 

must be met at the same location for ice accretion to occur: the local wet-bulb temperature to be near 

freezing or below and the local melt ratio must be above 10%. These parameters were deduced from 

analyzing laboratory icing test data and are the criteria used to predict the possibility of ice accretion 

within an engine including the specific blade row where it could occur. Once the possibility of 

accretion is determined from these parameters, the degree of blockage due to ice accretion on the 

local stator vane can be estimated from an empirical model of ice growth rate and time spent at that

operating point in the flight trajectory. The computational tool can be used to assess specific turbine 

engines to their susceptibility to ice accretion in an ice crystal environment. 

NASA/TM—2013-218094 1
Nomenclature 

A = Area, ft2

pw c , pa c = Specific heat of water vapor, air, 

 BTU/(lbm-R)

pwet c = Specific heat air-water vapor mix, 

 BTU/(lbm-R)

pi c = Specific heat of ice, BTU/(lbm-R)

C

CU

= Blade chord, in

= Tangential velocity of air, ft/s

Dv = Diffusion coeff. of water vapor into air

d = Ice particle size, diameter, μm

Fw, Fa = Molar flow rates of water vapor, air,

G

 mole/s

= Ice growth rate, in/s

gc = Unit conversion, 32.2 lbm-ft/(lbf-sec

2

)

hm = Mass transfer coefficient, ft/hr

h = Convective heat transfer coefficient,

 BTU/(hr-ft2-R)

ΔHmelt = Enthalpy change of ice and air

IWC = Ice water content, kg/m3

J = Units conversion, 778.28 ft-lbf / BTU

k = Thermal conductivity, BTU/(hr-ft-R)

Lv = Latent heat of evaporation, BTU/lbm

Le = Lewis Number

Lf = Latent heat of freezing, BTU/lbm

Ls = Latent heat of sublimation, BTU/lbm

LWC = Liquid Water Content, kg/m3

Ma,Mw = Molecular weight of air, water vapor

Mwet = Molecular weight of air-water mixture

mw = Evaporation rate of water, lbm/hr

N = Compressor rotational speed (RPM)

n melt = Melt fraction

Nu = Nusselt number 

Pa, Pw = Partial pressure of air, water vapor, psia

Pw,s, Pw,∞ = Partial pressure of water vapor at surface,

 and in free stream, psia

PSAT = Saturation pressure, psia

Pr = Prandtl number 

q = Heat flux, BTU/(sec-in2

)

r2 = Blade tip radius, in 

rC = Arc radius of blade at mid-chord, in

R = Gas constant, ft-lbf/(lbm-R)

R = Universal Gas constant,

 1545.5 ft-lbf/(lb-mole-R)

Re = Reynolds number 

Rwet = Gas constant of air-water vapor mixture,

 ft-lbf/(lbm-R)

S = Blade spacing, baseline, in

S’ = Reduced blade spacing, in

Sc = Schmidt number 

Sh = Sherwood Number

Ts = Surface temperature, R

TStat = Static air temperature, R

TTot = Total air temperature, R

TWB = Wet-bulb temperature; surface, R

T∞ = Free-stream temperature, R

TM = Averaged temperature of control volume, R

TWC = Total water content = LWC + IWC

t = Time, s

U = Rotor peripheral velocity, ft/s

Vd = Ice particle velocity, ft/s

V∞ = Free-stream air velocity, ft/s

V

~ = Control volume

Ww, Wa = Flow rates of water vapor and air, lbm/s

wa,ww

w∞,ws

= Mass fraction of air, water vapor

= Mass fraction of water vapor in dry air

 in the free-stream, and at the surface

X, = Axial gap between rotor and stator, in

X0, Y0 = Blade circular arc center point x, y

X2, Y2 = Blade trailing edge coordinate, in

x0, x = Initial location ice particle, current

Y1

 location of ice particle, in

= Blade leading edge y coordinate, in

Z = Axial distance, in

Greek:

α = Thermal diffusivity, ft2

/s

β1, β2 = Angles, leading; trailing edge, degrees

γwet = Ratio of specific heats of air-water mix

θ = Blade arc angle, degrees

μ = Viscosity of air, absolute, lbm/(ft-s)

τ = Thermal response time, s

φ = Relative humidity

ρi,ρw,ρa, = Density of ice, water vapor, air, lbm/ft3

σ = Blade tip solidity

χa, χw = Mole fraction of air, water vapor

ω = Specific humidity

NASA/TM—2013-218094 2
I. Introduction

The purpose of this study is to document the development of a computational tool to estimate the risk of ice 

accretion and its effect on turbofan engine performance. Ice crystals ingested into the engines during the operation 

of an aircraft at high altitudes in high ice water content (HIWC) environments can result in ice accretion in the low 

pressure compression system. As ice crystals are ingested into the fan and low pressure compression system, the air 

temperature increases and a portion of the ice crystals melt. This allows the ice-water mixture to stick to the metal

surfaces of the compressor components. The resulting accretion causes a blockage on stationary components such as 

the stator vanes, and subsequently results in the deterioration in performance of the compressor and engine. There 

have been numerous reported engine icing events1, 2 that have occurred on commercial airlines (Figure 1). The total 

number of engine icing events per year, that were attributed to high ice water clouds, appear to be increasing since 

20023

. 

 

Figure 1: Reported engine icing events. The engine events occurred at altitudes between 10K and 40K feet and at 

temperatures between ISA and +36 R). 

The computational tool that was developed in this study provides the capability to analyze a turbine engine through 

an ice cloud along a vehicle flight trajectory from takeoff, climb, cruise, and descent modes, and to evaluate the 

susceptibility of the engine to ice accretion. The tool has an engine system thermodynamic cycle code, coupled with 

a compressor flow analysis code, a fluid properties code, and an ice particle melt code. The mixed fidelity 

computational tool provides details of the flow conditions within each blade row of the fan and low pressure 

compression system during operation in the engine system environment. This work leverages from the previous 

code development effort and parametric study of the effects of blockage due to ice on engine and compressor 

performance reported in References 4, 5. 

Ice accretion in the low pressure compression system can result in deteriorating the performance of the compressor, 

and consequently on the overall performance of the engine. In this study we utilize a representative notional engine 

in the 40K lbf thrust class and a typical flight trajectory that is appropriate for a commercial aircraft equipped with 

this class of engine. 

In order to perform the study, it was necessary to have the details of the low pressure compressor (LPC) geometry to 

compute the flow conditions between each blade row with the mean line compressor flow analysis code. To that

end, a conceptual design of a notional fan-core and LPC was completed to determine the key dimensions that define 

the blade and flow path. Details of the LPC design are provided in the appendix of this paper. The engine system 

analysis was performed by the Numerical Propulsion System Simulation (NPSS) code6

. This code has been coupled 

with a mean line compressor analysis code (COMDES7

) such that blade row flow details of the LPC can be 

extracted. The baseline engine performance was computed with the NPSS-COMDES code, across the complete

flight trajectory. The locations within the LPC where there is a risk of ice accretion were determined. At those 

operating points and locations within the LPC, a parametric analysis with additional blockage due to ice accretion 

could be performed, as was demonstrated in References 4, 5. These previous parametric analyses completed in 

NASA/TM—2013-218094 3
References 4, 5 predicted that as the amount of blockage is increased, the LPC pressure ratio, choke margin, 

efficiency, and stall margin are reduced. All of these have a net detrimental effect on engine performance that can 

potentially cause an increase in turbine inlet temperature for a given thrust setting, or a reduced level of thrust, or 

rollback, for a given maximum turbine temperature. Additionally both of these possible scenarios result in an 

increase in the specific fuel consumption. 

II. Code Enhancements 

The computational tool that has been developed for this study leverages from the coupled Numerical Propulsion 

System Simulation engine thermodynamic cycle code and the mean line compressor flow analysis code (COMDES). 

A fluid properties model has been added to the COMDES code to account for supplemental water vapor in the air. 

Additionally, a code named MELT has been developed to model the melting of ice particles. This code leverages 

capabilities from the LEWICE2D code8, 9. Modifications to account for water and ice crystals in the airflow have 

been made to the compressor code. These codes have been coupled together such that they exchange boundary 

conditions at each iteration. The compressor analysis code computes the detailed blade row by blade row flow 

conditions, as well as the overall compressor performance, thus the code is utilized by the system modeling code 

directly, and takes the place of a characteristic performance map. The mean line compressor code effectively 

eliminates the need for a map in the NPSS engine system modeling code for the fan-core and LPC components. A 

code named MELT has been developed that computes the melting rate of ice crystals, as they pass through the 

engine inlet, fan and low pressure compressor blade rows. The models for sublimation, melting, and evaporation in 

the MELT code have been adapted from the LEWICE2D code. However, there are no models for ice accretion, 

particle breakup, shedding, or erosion in MELT. The compressor code and MELT have been coupled to exchange 

boundary conditions at the blade leading and trailing edges. The compressor code has several additional capabilities, 

including the ability to calculate the effects of water vapor on the fluid properties of the air–water vapor mixture 

based on the mole fraction of air to water vapor. The specific humidity at the engine inlet is obtained from the NPSS 

code, and the local relative humidity is estimated through each component of the inlet-fan-LPC, taking the 

sublimation, melting, and evaporation into consideration, as well as the local air temperature. The resulting effect of 

the humid air on the performance of the compressor is computed. 

A. Numerical Propulsion System Simulation (NPSS)

NPSS6 is an advanced thermodynamic cycle code written in an object-oriented language for system modeling of gas 

turbine engines. The code provides the overall component-level performance and flow conditions of pressures and 

temperatures. However, the NPSS system modeling code alone does not have the fidelity to provide the flow 

conditions within the stages and blade rows. Therefore COMDES7

, a mean line compressor flow code, was coupled 

to NPSS to provide the flow conditions at a higher fidelity, that is, within each blade row of the multi-stage fan-core 

and low pressure compressor. The block diagram in Figure 2 illustrates the turbofan engine model and its 

components as modeled with the NPSS-COMDES codes. 

Figure 2: The NPSS engine system model of the two spool turbofan engine with the coupled COMDES 

compressor flow analysis code and MELT ice melting models. The fan-core performance (dashed box) is 

computed with the COMDES mean line flow code and the MELT code.

NASA/TM—2013-218094 4
The COMDES and the NPSS codes were coupled such that they exchange boundary conditions iteratively at each 

operating point through the flight trajectory. The fan-core and LPC performance illustrated in Figure 2 with the 

dashed box is not obtained from component characteristic maps, but rather is calculated with the COMDES mean 

line flow analysis code, and the MELT code. This process is illustrated in more detail in Figure 3, where the codes 

and their functionalities that have been developed for this study are described in more detail. The codes are outlined 

with the rectangular shaped border, while the boundary condition information passed between the codes have 

borders with rounded corners.

Figure 3: The NPSS engine system model, COMDES compressor flow model and MELT ice melting 

computer model boundary exchange strategy for the fan-core and LPC. The fan-core and LPC performance is 

computed with the COMDES code, and the MELT code.

While the fan-core and LPC performance is evaluated by means of the results from the COMDES code, the rest of 

the turbine engine components are modeled in NPSS with the use of traditional component characteristic 

performance maps. With this combined engine-compressor performance modeling tool, the detailed blade row 

conditions are determined while operating in an engine system environment. The notional engine is analyzed though

the notional flight trajectory of a commercial carrier to determine the flow conditions, including the local pressure 

and temperature between each rotor and stator blade row of the multistage low pressure compressor (LPC).

Based on preliminary experimental results of ice accretion on a wedge shaped airfoil performed jointly by NASA 

and the National Research Council of Canada (NRCC)

10, well-adhered ice accretions with rapid growth were 

observed to occur when the wet-bulb temperature was near freezing or below. Another key parameter was to have 

sufficient liquid water which is characterized in this study using the melt ratio, or the local value of the liquid water 

to the total water ratio (ice + water). For icing to occur, this study utilized a melt ratio of 10% based on observations 

that were made from the analysis of laboratory test data10. As a side note, the experiments conducted by NASA and 

NRCC showed that ice accretion could also occur at wet-bulb temperatures above freezing, particularly at higher ice

water concentrations. However, this ice did not appear to be well-adhered and had a tendency to shed periodically. 

This shedding can also pose a hazard in the engine but is not considered in this study. 

NASA/TM—2013-218094 5
The critical values of wet-bulb temperature and the melt ratio are the two key parameters that together are the 

necessary conditions which must be met simultaneously, at the same calculating station in the compressor, in order 

for there to be a high risk of ice accretion. Since the wet-bulb temperature and the melt ratio both change through 

each blade row, this technique also identifies the blade row where there is a high risk of ice accretion. However, it is 

recognized that other parameters such as the heat transfer rate through the blades may need to be considered as well, 

but are not included in the current version of the NPSS-COMDES codes. It is assumed in this study that accretion 

does not occur on the rotors, since the water/ice mixture would likely not have enough time to accrete on the high 

speed blade surface due to high centrifugal forces. Therefore the assumption is that accretion can only occur on the 

stator vanes and flow path walls.

Once a stator has been located in which the two parameters simultaneously indicate a risk of ice accretion, the 

amount of blockage at that stator vane location can be estimated as a function of time spent at that operating 

condition, and the measured ice accretion growth rate obtained from laboratory experiments10. The growth rate in 

terms of inches per second is converted to a value of additional blockage at that stator location, and the performance 

of the compressor with the additional blockage can then be computed with the compressor flow analysis code as a 

function of time spent at that operating condition. Parametric blockage is not addressed in this study, but was

detailed in previous studies4, 5. The updated performance of the iced compressor is then passed to the engine cycle 

code, and the engine performance with the iced compressor is aero-thermodynamically rebalanced. 

B. Compressor Flow Analysis Code Enhancements

The compressor flow analysis code utilized in this study is the COMDES mean line flow code. The code computes 

the velocity, pressure, temperature, and flow angles at the leading edge and trailing edge of each blade row, at the 

hub, mean, and tip sections. The mean line compressor design and flow analysis code has been modified to include 

the effects of relative humidity on the fluid properties of air and water vapor mixture, and the subsequent effects on 

compressor performance. The capability of calculating the local relative humidity in each blade row is based on the 

initial value of specific humidity (mass of water/mass of air) at the compressor inlet. Additional modifications have 

been made to enable calculating the two key parameters which have been identified as early indicators of ice 

accretion: the local wet-bulb temperature and the percent of melt ratio within each blade row. If the limiting values 

of these key parameters are met, there is a risk that ice will accrete on the surfaces of the compressor. With these

parameters as the precursors to ice accretion, the blade row within the compression system can be identified that is 

likely to experience ice buildup at a particular engine operating condition in the vehicle flight trajectory. The local 

wet-bulb temperature is calculated at each blade row. The geometry section of the code was improved with the 

addition of simple circular arc blades and vanes. An ice particle melting and evaporation model was coupled to the 

compressor code to compute the local melt ratio through each blade row. 

Water Vapor

Additional modification to the COMDES code includes the capability of modeling the effects of water vapor on the 

gas properties of air. The model is based on a specified value of specific humidity at the inlet of the 

engine/compressor. The values for fluid properties of the water vapor and air are obtained in COMDES from the 

GASPLUS11 code. The mole fraction of water vapor to air is used to compute the average mole weight of the fluid,

the average gas constant, and the average specific heat ratios for water vapor ( p w

c ) and air ( p a

c ). Molar flow 

rates (Fw, Fa) are given by: 

w

w w M

W F = (1)

a

a a M

W F = (2)

NASA/TM—2013-218094 6
( ) aw

w

w FF

F

+

χ = (3)

( ) aw

a

a w FF

F

+

1 χχ =−= (4)

Mass fractions (ww, wa) are given by: 

wwaa

ww

w a MM

M

ww

χχ

χ

+

1 =−= (5)

 

wwaa

aa

a MM

M

w

χχ

χ

+ = (6)

Average molar mass of the mixture:

Mwet += χχ MM wwaa (7)

 

The specific heat of the air-water vapor mixture ( p wet

c ) is calculated with the following formula: 

 

pa a pw w p wet

c += cwcw (8) 

Average gas constant ( Rwet ) of the air-water vapor mixture, in terms of the universal gas constant (R ): 

wwaa wet

wet MMM

R R = +

R = ( χχ ) (9) 

The ratio of specific heats for the air-water vapor mixture:

1( /( ))

1

p wet wet

wet − JR c

γ = (10) 

Rotor and Stator Blade Geometry

The geometry portion of the compressor code has been improved with the addition of a circular arc blade geometry

generator. The code generates rotor blades and stator vanes based on the values of the blade angles at the leading 

and training edges, the tip solidity, and the flow path radii. The circular arc shaped mean camber lines of the blades 

are created at the hub, mean, and tip section of each rotor and stator of the stage. When used in the analysis mode, 

the circular arc blades act as reasonable approximations of the actual rotors and stators, Figure 4. This represents one 

stage of the five stage fan-core and LPC that are analyzed in this study, as will be illustrated in a later figure. With 

this method, the blade-to-blade distances and passage chord lengths can be computed with reasonable accuracy. 

NASA/TM—2013-218094 7

Mole fractions ( χ w, χ a ) are given by: 
 Rotor Gap Stator Gap 

Figure 4: Rotor and stator blade mean camber line chords at the mid-span section for a typical stage. The 

station numbers 1 and 2 refer to the rotor leading and training edges respectively, while stations 3 and 4 refer to the 

stator leading and trailing edges respectively.

The lengths are used to estimate ice particle residence time and for calculating the sublimation, melt, and 

evaporation rates which will be addressed in the subsequent “Ice Particle Melting and Evaporation” section. The

circular arc blade generation methodology that was used to determine the compressor rotor and stator blade 

dimensions are detailed below and the compressor geometry used in this study is provided in a later section on fan 

and low pressure compressor conceptual design. 

The geometry section of the compressor code includes the capability to generate approximate blade shapes based on 

a simple circular arc blade camber line profile. The compressor code is run in the analysis mode, and the blade 

angles at the leading and trailing edges are specified. For rotors, the design point incidence, flow rate, and shaft 

rotational speed provides the blade angle at the leading edge. At the trailing edge, the work, or flow turning angle 

defines the blade angle at the blade exit. The tip solidity, number of blades, and flow path inner and outer radii are 

input parameters. The simple circular arc blade camber line is generated by the code at the hub, mean, and tip 

sections. The same procedure is followed to provide the stator vane camber line with simple circular arc shape. The 

following equations define the rotor blade and stator vane (referred to as airfoils in the following) camber geometric 

shape. The chord, C, is determined from the tip solidity,σ , the tip radius, r2, and the number of airfoils, N, by the

following equation.

N

r

C

2 2 σπ = (11) 

The true chord can be closely approximated by the following equation which is for the isosceles triangle in Figure 5. 

2

2 θ

C r Sin = C (12) 

NASA/TM—2013-218094 8
Figure 5: Compressor airfoil camber line geometry creation in COMDES. A simple circular arc camber line 

with radius rc is generated in the compressor code based on input values of tip solidity of the rotor and stator, and 

angles at the leading (β1) and trailing (β2) edges. 

The following equations are used to solve for the coordinates of the airfoil leading and trailing edges and the 

coordinates of the center of the circular arc (Xo, Yo) which defines the arc radius rc at the blade mid-chord.

222 += YXr OOC (13) 

( ) 2

2

2 2

2

2

O YXXrC +−= (14) 

C

O

r

X Sinβ1 = (15) 

Cr

Y Cos 2 β 2 = (16) 

The airfoil section coordinates shown in Figure 5 are determined using the above equations for a circular arc. Both 

the rotor blades as well as the stator vanes are generated with a single circular arc. 

Energy Balance between Ice Particle and the Air

As the ice passes through the inlet, fan, and LPC blade rows, it is continuously absorbing heat from the warmer air 

through the compressor blades. The amount of energy that the ice particle absorbs from the air while it experiences 

sublimation, melting, and evaporation will be described in the subsequent section named “Ice Particle Melting and 

Evaporation.” The transfer of energy between the air and the ice particle can be expressed as a change in enthalpy. 

The enthalpy increase of the ice particle is equal to the enthalpy decrease of the air, which results in a decrease of

the total temperature of the air. The energy balance between the ice particle and the air is determined iteratively with

the results from the compressor code and the particle melt code exchanging boundary conditions of static 

temperature, static pressure and change in enthalpy until convergence. The change in total temperature of the air 

through the rotor is a function of the enthalpy rise due to the work input by the rotor, and the enthalpy that the ice 

particle removes from the air, as determined from the particle melt code. To account for effects of the energy 

exchange between the ice particle and the air through the compressor rotor, the Euler equation energy balance in the 

NASA/TM—2013-218094 9
compressor code has been modified to account for the enthalpy exchange between the particle and the air, and is 

represented by the following equation, where the subscripts 1 and 2 represent the conditions at the rotor leading edge 

(station 1) and trailing edge (station 2) respectively (see Figure 4). 

( ) ( ) wet cp U U112212 ∆−−=− HCUCUTTgcJ melt − )12( (17) 

The solution of flow conditions at the rotor exit is obtained by executing the compressor code and the particle melt 

code iteratively, by passing boundary conditions of static temperature and velocity from the compressor code to the 

MELT code, where the enthalpy change (ΔHmelt) of the ice particle is calculated, and returned to the compressor 

code where the change in air temperature due to the change in enthalpy is calculated. A similar iterative process is 

utilized to calculate the change in air temperature due to enthalpy exchange between the air and the ice particles 

through the gaps between the rotor and stator, and through the stator vanes, where the subscripts 1 and 2 represent 

the inlet and outlet of the gap, and subscripts 3 and 4 represent the conditions at the stator leading edge and trailing 

edge respectively (see Figure 4). Note that when calculating the air temperature in the gap, the subscripts 3 and 4 are 

replaced with subscripts 2 and 3, respectively, in the following equation.

( ) pwet c 34 ∆− H=TTgcJ melt − )34( (18) 

Wet-Bulb Temperature 

In this study, the wet-bulb temperature parameter is utilized as one of the key indicators of whether there is a risk of 

ice accretion within one of the compressor blade rows. A mathematical derivation of a wet-bulb temperature (TWB) 

for application in analysis of mixed-phase icing tests has been derived and implemented into the mean line 

compressor flow analysis code, thus enabling the multistage code to compute the local wet-bulb temperature at each 

rotor and stator leading and trailing edge and at the stator throat. In this derivation TWB is the temperature of an 

evaporating wet adiabatic surface and is a function of the surrounding air temperature (dry-bulb), air pressure, and 

moisture content. The TWB is obtained by equating the rate of heat transfer to a surface to the heat loss by 

evaporation. During this process, it is assumed that the surface remains wet and any water added to replace that lost 

by evaporation is at TWB. The analysis is an adaptation of heat and mass transfer principles described in Incropera & 

DeWitt12 and thermodynamic concepts presented in Çengel and Boles13. It is assumed that the process is steady 

state, with adiabatic boundaries, except at the edge of the boundary layer. The surface (and water layer) is 

maintained at TWB. The surface always remains wet (either evaporation is negligible from a mass loss perspective or 

water is replaced at TS via some process). The static pressure remains constant, and the partial pressure of water 

vapor at the surface is assumed to be the saturation value at the surface temperature. Figure 6 illustrates the 

conceptual representation of the control volume for the thermodynamic balance model that is utilized to derive the 

wet-bulb temperature. 

Figure 6: The control volume for the thermodynamic balance model. 

qconvection  m nevaporatio 

q = 0

T∞

Pa 

Pw,∞

Air-Water 

Ts, Pw,s = PSAT (Ts) Interface

 Air

 V

~ (Volume)

Boundary Layer

Water

q = 0 q = 0

NASA/TM—2013-218094 10
An energy balance performed on the above control volume with the given assumptions is shown in Eq. (19).

vws Mpa LmTTAh

dt

dT cV a −−=  ∞ )( ~ ρ (19) 

Assuming a steady state process, the above equation can be rearranged to solve for the surface temperature as shown 

in Eq. (20). 

Ah

Lm

TT vw

s



∞ −= (20) 

Examination of the above equation shows that TWB will be less than the T∞ when there is evaporation from the 

surface given the assumptions stated above. 

To determine the amount of mass evaporated leaving the top of the boundary layer, it is assumed that the process is 

steady (i.e., no accumulation in the control volume). The evaporated water leaving the control volume is resupplied 

to the surface at TWB via some unspecified process. It is also assumed that saturated conditions exist at the water and 

interface. Under these assumptions, the mass flux leaving the control volume is shown in Eq. (21): 

( ) = ρ samw − wwAhm ∞  (21) 

Combining the mass flux leaving the control volume, Eq. (21), with the energy balance, Eq. (20), provides another 

expression for the surface temperature, as shown in Eq. (22): 

∞ −= ( ) − wwL ∞ h

h TT sav m s ρ (22) 

Invoking the analogy of heat and mass transfer yields another expression for the surface temperature, equation. This 

analogy is valid for both local and bulk transfer coefficients as well as laminar or turbulent conditions. The

properties values are evaluated at the average of the free-stream and the surface temperature. A more detailed 

derivation of this expression is presented in Reference 14. 





 



 − 













 −=

∞

∞

∞ T

P

T

P

P

T

M

M

Lec

L TT w

s

sw

a

M

a

w

p

v s

a

,,

3

2

 (23) 

Eq. (23) can be solved iteratively. The surface temperature, Ts, is the wet-bulb temperature, based on the above 

assumptions. 

The partial pressure of water vapor at the surface is assumed to be the saturation value at the surface temperature, 

Eq. (24). The partial pressure of water vapor outside the boundary layer can be defined based on the ambient 

relative humidity, φ, as shown in Eq. (25). 

, = φ PP ,ssatssw ; evaluated at TWB (φs= 1.0, fully saturated) (24) 

w, = φ PP sat,∞∞∞ ; evaluated at T∞ (25) 

For this work, total conditions were used for T∞ and P∞ to calculate wet-bulb temperature to represent conditions at a 

stagnation point.

NASA/TM—2013-218094 11
Ice Particle Melting and Evaporation

The capability to model ice particle and evaporation has been added to the COMDES compressor analysis code. The 

appropriate equations were taken from the LEWICE2D code and were implemented into the compressor code in the 

subroutine named MELT. This enables the code to calculate the change of phase of an ice particle which sublimates, 

melts, and evaporates, as it passes through the fan and low pressure compressor blades and stator vanes. The ice 

particle residence times through the compressor of existing engines are estimated based on the velocities at the 

leading and trailing edge of each blade row, and the blade chords and the axial spacing of the gap between the rotors 

and stators. This provides a reasonable estimate of the actual residence times of the ice crystals through each blade 

passage and gap, resulting in an accurate estimate of the sublimation, melting, and evaporation physics. The inlet 

specific humidity and the ice particle concentration (grams per cubic meter) and size distributions are specified at 

the inlet to the engine. For this study, values for ice particle size and concentrations in the atmosphere are varied 

parametrically, as there is limited data currently available on the ice crystal content of high altitude convective 

clouds. 

After the flow conditions through the blade rows have been calculated by the compressor code, the static 

temperatures, pressures, and velocities are passed to the ice melting subroutine to determine the rate of melting and 

evaporation, and thus, the local melt ratio in each blade row. The ice particle sublimation, melting, and evaporation 

equations are shown below. The calculations for sublimation, melting, and evaporation take into consideration the 

local temperatures, pressures and residence times as they traverse the blade passages and gaps between blades at 

their mid span location. Conservation of mass on each particle results in the following equation for the ice particle 

size as a function of position, where ws is the mass fraction of water vapor at the surface and w∞ is the mass fraction 

of the water vapor in the free-stream. 

 ( )( ) ∞

∞

−= −− wwxx

V

DSh

dd so

i

a

o ρ

ρ ν 4 22 (26) 

Similarly, the rise in specific humidity is related to the amount of mass lost by the particle and is given by the 

equation below.

































−+=

3

1

a o

o d

IWC d

ρ

ωω (27) 

Equating the heat absorbed by the particles to a decrease in enthalpy in the airstream provides the decrease in air 

temperature. 































 −= −

3

, 1

ap o

s

oaa d

IWC d

c

L TT

a ρ

 (28) 

The enthalpy increase of the particle through the compressor is equal to the heat absorbed from conduction plus the 

energy provided by evaporation, resulting in the following equation for the change in particle temperature prior to 

melt

( ) ( )s

pT

s

ia

T

i ww

ScVc

ShL

TT

V

Nu

dx

dT

a

= +− ∞ −

∞ ∞

Pr

τ τ

 (29) 

The mass fractions of water vapor in the above equation are given by the equations below.

a

w

a

w

P

P

M

M

w ∞ = ∞∞

, φ (30) 

a

sw

a

w ss P

P

M

M

w , = φ (φs = 1.0, fully saturated) (31) 

NASA/TM—2013-218094 12
The non-dimensionalization of the energy equation above results in the following term for the thermal response time

a

ip

T k

dc

i

6

2 ρ

τ = (32) 

The Nusselt number, Sherwood number, and the Prandtl number in these equations are provided by assuming 

spherical particles. If other particle geometries are of interest, the correlations can be easily modified for those cases. 

a

p

k

c

















=

μ

Pr (33) 

ak

dh

Nu = (34) 

3

1

2

1

Nu += PrRe6.02 (35)

The Schmidt number is defined by the following equation.

va

a

D

Sc

ρ

μ = (36) 

The Sherwood number is defined by the following equation.

v

m

D

dh

Sh = (37) 

3

1

2

1

Sh += Re6.02 Sc (38) 

The Reynolds number in the above equation is based on the particle size and the relative velocity of the particle to

the velocity of the air stream

a

da dVV

μ

ρ − = ∞ Re (39) 

where the particle/drop velocity, Vd, is obtained by integrating the equation of motion

3

2

2 Re

4

3

d

C

dt

dV

ia

a

d

d

ρρ

μ = (40)

Once the particle starts to melt, its temperature no longer changes. In this case, the energy equation above can be 

written as a change in the enthalpy or a change in the melt fraction8 as shown below. 

( ) ( )s

pT

s

f

p

ia

Tf

melt p ww

ScVc

ShL

L

c

TT

V

Nu

L

c

dx

dn

a

i i = +− ∞ −

∞ ∞

Pr

τ τ

 (41) 

The local fluid conditions of temperature and pressure are used in the above equations to determine the rate of 

sublimation, ice melting, and evaporation. The distance the ice particle traverses through the compressor rotors and 

stators is determined from the length of the engine inlet, and the geometry of the rotor blades, stator vanes, and the 

axial gaps between the rotors and stators. The distance through the fan and LPC blade rows is estimated from the 

true blade chord of the rotors and stators at the mid span, and the axial distance through the gaps between the blades, 

as illustrated in Figure 7. Note that each stage is analyzed at the blade edges as shown in Figure 4. In this study, the 

NASA/TM—2013-218094 13
simple circular arc blade camber line shapes are utilized and provide a means of easily estimating the geometry of 

the compressor blades and vanes. This facilitates estimating the distance traveled by the water/ice particle. The 

COMDES and MELT codes exchange boundary conditions of pressure, temperature and velocity, to estimate the 

residence time of the particle through each blade row, as well as to determine the rate of ice sublimation, melting, 

and evaporation.

 Rotor 1 Rotor 2 Rotor 3 Rotor 4 Rotor 5 

 Stator 1 Stator 2 Stator 3 Stator 4 Stator 5 

|-------------- Engine Inlet -------------| |-------------- Fan-Core -------------| |------------------------ LPC ---------------------------------| 

Figure 7: Ice particle path through the fan-core and low pressure compressor stages. Rotor and stator blade 

mean camber line chord at the mid-span section is used to estimate the distance traveled and residence time of the 

ice particles. 

Figure 7 illustrates the ice particle path through the rotor blades in the relative frame of reference, while the path 

through the stator vanes is in the absolute frame of reference. The calculations of ice sublimation, melt, and

evaporation are performed in increments from the leading to the trailing edge of each rotor and stator, as well as 

through the axial gap between the blades. As the engine is flown through the flight trajectory, the ice particle 

sublimation, melting, and evaporation is calculated in each rotor and stator blade row. The amount of water due to 

sublimation and evaporation is added to the local value of specific humidity, thus having an effect on the local 

relative humidity, and likewise on the local wet-bulb temperature calculation in the compressor code. The MELT 

code is also used to evaluate the particle conditions through the engine inlet which is then provided as ice particle 

initial conditions at the leading edge of the fan-core.

Identifying the Risk of Ice Accretion

When the wet-bulb temperature and melt ratio parameters indicate a risk of ice accretion at a particular location in 

the compressor, an additional blockage can be applied, which will result in a change in the performance of the 

compressor and engine. Though not implemented in the current study, the capability to simulate turbofan engine 

performance with additional blockage due to accretion has been previously demonstrated in References 4, 5. In that 

study, the blockage due to accretion was varied parametrically. The approach was to add blockage as a function of 

empirically derived ice growth rate, and time spent at that operating condition. However, the main focus of this 

paper was to determine the risk of ice accretion and its location, with an estimate of ice particle melt ratio, and the 

wet-bulb temperature calculation with no additional blockage due to ice accretion. 

Using data from laboratory testing,10 Figure 8 shows the normalized ice accretion growth rate as a function of 

measured liquid water content (LWCm) to injected total water content (TWCinj). In this figure, the measured ice 

growth rates (G) are normalized by the theoretical maximum ice growth rate, Gmax, as shown in Eq. (42). The data 

from this experiment suggest that some liquid water needs to be present for accretion to occur. A non-zero growth 

rate, G/Gmax, was first observed when the ratio of LWC to TWC increased to 14% (Figure 8). Only the portion of 

the data with wet-bulb temperatures below freezing is represented in Figure 8. However, data for wet-bulb 

temperatures marginally above freezing have also resulted in ice accretion with shedding, as reported in Reference 

14. The ice accretion growth rate as a function of the ratio of LWC to TWC data shown in Figure 8 is included in 

Appendix A. 

In this study it is assumed that ice accretion can only occur at values of TWB that are below the temperature of 499 R

(~ 4°C). This assumption is based on observations10 that showed significant growth rates and buildup of ice at values 

of TWB below 499 R. However, at values just above freezing (between 492 R and 499 R), the ice was slushy, and had 

a tendency to shed before a large buildup of ice could occur, but at values below freezing, the accreted ice did not 

shed and continued to grow as a function of time, provided that there was a positive melt ratio. Note that the effects 

NASA/TM—2013-218094 14
of ice shedding have not been modeled in this study. However, the detrimental effects of shedding on engine 

performance cannot be ruled out. Therefore, in this study the upper limit of 499 R is used as the maximum wet-bulb 

temperature ice accretion risk indicator. The criteria for the risk of ice accretion therefore are the wet-bulb 

temperature being less than 499R (i.e., slightly above freezing or below), and when the ratio of LWC to TWC

exceeded 10%, which includes some margin in comparison to the 14% ratio that was observed in the experiment to 

have significant growth rate. In this study, the ratio of LWC to TWC is an approximation to the melt ratio used 

elsewhere in this document. 

It is important to note that the data in Figure 8 is preliminary as the values LWCm and TWCinj require corrections 

which are not yet well understood. The subscripts m, referring to the LWC, denotes a measured value using a hotwire probe which has not yet been characterized in mixed-phase flow. The value used for LWC in Figure 8 is the 

uncorrected value. The subscript inj, referring to the IWC, denotes a bulk injected value using bulk water or ice flow 

rate data assuming a uniform cloud. The corrections to the LWC and IWC are topics of current research efforts. In 

addition, as higher fidelity, multi-disciplinary computational tools become available with accretion, erosion, particle 

breakup, and shedding models, they can result in more accurate predictive capability for the growth rate.

  ∞ 











 = V

TWC

G

i

inj

ρ max (42) 

Figure 8: Ice accretion growth rate as a function of the liquid-water-to-total water content ratio (i.e., melt 

ratio) when the wet-bulb temperature was below freezing10. A finite rate of ice growth was observed when the 

melt ratio was above 10%.

For completeness, an outline of how the additional blockage due to high growth rate of ice accretion can be utilized 

in the compressor flow analysis code. The amount of blockage due to ice accretion on the blades can be estimated 

from the maximum growth rates of ice accretion that have been observed during laboratory testing at the NRCC 

laboratory.10 The size of the ice growth is a function of time (t) spent at that operating condition and the ice growth 

rate is specified in terms of length per time. Although this growth rate is measured at a single point (i.e., the leading 

edge) of a blade, it is used here to generate a first order estimate of the blockage within a compressor. 

The amount of ice blockage in a blade row is estimated in the compressor code from the measured growth rate (G) 

and the blade spacing parameter (S). The ice accretion on the compressor vanes is illustrated in Figure 9, and shows 

how the blade spacing is reduced due to the estimated accretion

NASA/TM—2013-218094 15

.
 

Figure 9: Estimating the blockage due to ice accretion in the stator blade row. The ice accretion can be

modeled in the compressor code as an additional blockage at the stator leading edge and throat. 

The blockage from ice accretion can be modeled in the compressor code as an additional blockage and added to the 

nominal value of aerodynamic blockage. The reduction in the circumferential blade spacing (S’) is estimated by Eq.

(43), from the empirical value of ice growth rate (G), the time spent at that operating condition (t), and the nominal 

blade spacing (S). The reduced blade spacing results in a reduced annular area at the stator inlet and exit, and also a 

reduced throat area. 

S S 2tG ' −= (43) 

The blockage due to ice accretion is estimated from the reduction in blade spacing. The performance of the 

compressor and the engine system, computed with the additional blockage added parametrically (not as a function of 

time and growth rate) at a specific location in the compressor, has been demonstrated in References 4, 5. 

III. Analysis of Turbine Engine Performance in an Ice Crystal Environment

A. Fan and Low Pressure Compressor Conceptual Design

In order to perform the engine icing study, it was necessary to have the geometry of the low pressure compressor 

(LPC) in adequate detail such that the flow conditions between each blade row can be computed with the mean line 

compressor flow code. The conceptual design task was performed for a notional turbofan engine in the 40000 lb 

thrust class having a bypass ratio of 5.8 with the mean line compressor flow analysis code. The rotor and stator 

blade shapes were approximated with simple circular arcs. The conceptual design effort of the notional fan-core and 

LPC determined the key dimensions that define the blade and flow path geometry. Figure 10 illustrates the notional 

fan and low pressure compressor that was used in this study. The fan-core and LPC design point aerodynamic 

performance is included in Appendix B as output from the compressor code analysis. 

NASA/TM—2013-218094 16
Figure 10: Fan and low pressure compressor of the notional high bypass ratio turbofan engine. 

A compressor flow model with the COMDES code represents the fan-core and LPC in the NPSS engine system 

model. The radial view of the blade centerline sections are superimposed onto the flow path in Figure 10. Table I 

lists key aerodynamic and geometric design parameters at the root-mean-square (RMS) radius of each blade row and 

stator vane. The fan-core is considered the first stage in this study, followed by a four stage LPC.

Table I – The Fan-Core and LPC Design Point RMS Radius Geometric and Aerodynamic Parameters

Fan-Core

Rotor1

Fan-Core

Stator1

LPC 

Rotor2 

LPC 

Stator2 

LPC 

Rotor3

LPC 

Stator3 

LPC 

Rotor4 

LPC 

Stator4 

LPC 

Rotor5 

LPC 

Stator5 

Blade Chord, in. 7.434 5.496 2.401 2.401 2.344 2.373 2.240 2.270 2.125 2.132

AxialChord, X2 in 6.804 5.235 2.130 2.130 2.066 2.284 1.969 2.180 1.858 2.044

Blade Gap, X, in. 1.811 1.309 0.567 0.591 0.550 0.571 0.524 0.545 0.495 0.511

Radius, rc, in. 12.535 9.038 7.352 4.645 6.784 4.37 6.354 4.069 5.750 3.752

Leading Edge

Press Static, psia 13.67 14.67 16.61 18.785 20.12 22.45 23.91 26.41 27.88 30.04

Temp Static, R 508.0 522.1 542.22 564.55 576.56 597.76 609.40 629.48 640.0 656.21

Mach no., abs 0.38 0.638 0.46 0.534 0.42 0.499 0.39 0.449 0.34 0.417

Blade β1, deg 47.20 35.4 42.3 30.6 23.5 31.5 43.80 32.4 44.80 33.0

Abs Flow Angle 0 36.15 0 31.22 0 32.18 0 33.00 0 0

Tip Radius, in. 20.63 20.617 20.530 20.3433 20.096 19.6905 19.3131 18.8420 18.2524 17.6890

Hub Radius, in. 12.51 15.102 15.211 15.2026 15.054 14.8484 14.3197 13.7204 13.0749 12.2606

Trailing Edge

Press Static, psia 14.69 16.35 18.76 19.79 22.40 23.56 26.19 27.53 30.06 31.22

Temp Static, R 521.86 539.72 563.96 573.81 597.00 606.82 627.60 637.69 655.84 663.90

Mach no., abs. 0.63 0.481 0.53 0.448 0.49 0.413 0.46 0.368 0.41 0.338

Blade β2, deg 12.7 0 23.5 0 23.5 0 23.5 0 23.5 0

Abs Flow Angle 36.93 0 31.59 0 32.30 0 32.27 0 33.24 0

Tip Radius, in. 20.63 20.573 20.445 20.1704 19.925 19.4117 19.0737 18.4850 17.9280 17.2148

Hub Radius, in. 15.0 15.190 15.223 15.2026 14.848 14.4742 13.9111 13.2848 12.4811 11.6228

NASA/TM—2013-218094 17
B. The Performance of the Notional Turbine Engine System Model through a Typical Commercial Aircraft 

Flight Trajectory

In order to perform the engine icing study, the NPSS-COMDES engine model was executed at numerous operating 

conditions through a flight trajectory. The inlet conditions of ice crystal concentrations in grams per cubic meter, 

particle size, and the elevated ISA (International Standard Atmosphere) temperature were varied parametrically at 

ISA +0 R, +18 R, +27 R, and +36 R, since that is in the range of where ice accretion has been reported, as was 

illustrated in Figure 1. The detailed analysis of the fan-core and low pressure compressor with the COMDES code 

was obtained at each operating condition. The engine analyses were performed with the fully coupled computer 

models described in the above sections. The system model was utilized to determine the performance of the notional 

40000 lbf thrust class engine through a typical flight trajectory of a commercial aircraft (Figure 11). 

Figure 11: Flight trajectory for a typical commercial aircraft. The notional 40000 lb thrust engine is “flown” 

through the vehicle flight trajectory to determine the blade row where conditions for ice accretion may be possible.

The notional flight trajectory4, 5, 15 used in this study includes takeoff, climb, two cruise altitudes, and one descent 

profile. The detailed output listing of the flight trajectory is included in Appendix C. The first cruise altitude is at 

35000 feet, where the engine thrust is reduced from 100% down to 69.9% of maximum thrust at the end of the 

cruise. The aircraft then proceeds to 39000 feet where again the thrust reduces from 100% down to 76.8% 

maximum thrust at that altitude. The engine is then spooled back to 10% maximum thrust at 39000 feet as it 

prepares to descend in altitude. The engine is maintained at 10% maximum thrust as it descends to 10000 feet, 

which was the lowest altitude that was analyzed in this study. 

Figures 12 and 13 illustrate the baseline pressure ratio and efficiency characteristic maps of the fan-core and LPC 

and the superimposed operating points through the flight trajectory. The baseline maps have no additional blockage 

due to ice accretion. These maps were generated by the compressor code executed in the stand-alone mode 

(independent of the NPSS system modeling code); however, the operating points along the map were obtained by 

running the fully coupled engine system model, the compressor flow analysis, and the melt codes as illustrated in 

Figure 3. The plot file of the overall compressor maps shown in Figures 12 and 13 are listed in Appendix D. The 

plot file of the fan-core and LPC performance along the engine operating line is listed in Appendix E. The complete 

output listing of the mean line compressor flow analysis code, along the entire baseline performance map and the 

flight trajectory, are listed in Appendices D and E of Reference 5 respectively. 

NASA/TM—2013-218094 18
The risk of ice accretion on a stator is a function of where in the flight trajectory the engine is operating and the 

atmospheric conditions of temperature and pressure, as well as the ice particle concentration and size. As will be 

illustrated in a later section of this paper, at high altitudes, the rear stages of the LPC may be at risk for accretion, 

while at lower altitudes, the risk of accretion may be in the front stages. 

Even though no additional blockage is added at any location to the compressor, the compressor analysis code was 

utilized in this study to determine which stage had a risk of ice accretion, based on the wet-bulb temperature and 

melt ratio criteria. This could not have been determined from an LPC compressor map showing overall performance 

alone. 

In the previous study4 that included compressor flow analysis with parametric blockage, the LPC performance with 

ice accretion could not be represented by traditional compressor performance maps, since the amount of blockage

due to ice, and the stage where there is blockage, was different along each speed line, and depended on the altitude 

and thrust level it is operating at in the flight trajectory. The solution that was chosen was to fully couple the NPSS 

and the COMDES codes, thus the compressor performance was passed to the system model for each unique point of 

operation, which included the unique amount of blockage due to ice accretion at a specific blade row. 

In this study the performance of the engine with blockage is not addressed; as this was addressed in an earlier 

publication. The focus here is to more accurately predict the locations in the low pressure compression system where 

there is a risk of ice accretion, as well as the atmospheric conditions that could support it, along a flight trajectory. 

The fully coupled NPSS_COMDES_MELT code has been executed through the flight trajectory, and the results of 

the icing risk analyses, in each stage of the LPC, are shown graphically in the following figures. 

 

Figure 12: Fan-core and LPC pressure ratio showing the baseline performance. Operating points of the fancore and LPC throughout the flight trajectory are superimposed onto the baseline pressure ratio map.

NASA/TM—2013-218094 19
Figure 13: Fan-core and LPC performance showing the baseline efficiency map. Operating points of the fancore and LPC throughout the flight trajectory are superimposed onto the baseline efficiency maps. 

A range of ice particle concentrations, and particle diameters were analyzed with the icing code, at various ambient 

temperatures above the ISA standard. The local values of wet-bulb temperature and melt ratio at each LPC blade and 

stator inlet and outlet, were computed for the engine operating conditions through the vehicle flight trajectory. The 

performance of the fan and LPC stages were analyzed. 

Ice Particle vs. Ambient Temperature

In this study we assumed that ice crystals cannot form at temperatures above freezing. As illustrated in Figure 1, the 

range of temperatures where engine icing events occurred was between the ISA temperature and 36 R above the ISA 

temperature. The altitude at which freezing occurs is a function of ISA offset temperature, as illustrated in Figure 14. 

For example, at an ISA offset temperature of 0 R, the minimum altitude where ice crystals can form in the 

atmosphere is 7500 ft, while with an offset of +36 R, the minimum altitude is 17400 ft. In the study the ISA offset 

temperatures of +18, +27, +36 R were considered through a wide range of altitudes along the flight trajectory. 

However, at conditions below the 492 R line in Figure 14, the assumption is that the particle is all liquid water; 

therefore the melt ratio even before entering the engine is equal to 1.0. Likewise, the calculated wet-bulb 

temperature at these conditions is above the range where ice accretion is a risk, based on the analysis. Therefore, no 

conditions exist that would support ice accretion at operating points below the 492 R line shown in Figure 14. 

NASA/TM—2013-218094 20
Figure 14: Altitude vs. ISA offset temperature indicating the assumed minimum altitude where ice crystals 

can form. Note that ice crystals are not expected to form at conditions below the 492 R line. 

Ice/Water Particle vs. Air Temperature through the Engine Inlet

In the NPSS code, there is a model to estimate the aerodynamic performance of the engine inlet, from the entrance 

region through the plane of the fan face, based on the area ratio and length. The change in total temperature due to 

the forward velocity of the vehicle is estimated, and the static temperature is calculated from the entrance of the 

engine to the plane of the fan leading edge. At the entrance, the temperature of an ice crystal is equal to the ambient 

temperature. However, because the aircraft is flying at a moderately high Mach number, the total temperature of the 

air is increased above the ambient, and the change in temperature is calculated based on the Mach numbers at the 

entrance and at the fan face. As the air is diffused through the subsonic inlet, the static temperature of the air rises 

even before reaching the fan leading edge. At high altitude operating points, for example during the descent mode at 

an altitude of 38334 ft. and vehicle Mach .73 in Figure 11, the temperature of the ice particles in the engine inlet is 

typically well below freezing, until the particles are inside the fan-core and LPC, as illustrated in Figure 15. Through 

the inlet and most of the fan-core and LPC, the ice particle temperature rises and also sublimates. Note that 

throughout the flow path the enthalpy exchange between the ice particle and the air is iteratively computed.

 Figure 15: The temperature of the ice crystal particles lags the static temperature of the air through the 

engine inlet, the fan-core and the LPC at 38K ft during the descent mode, with particle travel distance.

NASA/TM—2013-218094 21
At a distance traveled of 64 inches, the particle reaches the freezing temperature of water (492 R) and begins the 

melting and evaporation process. The ice-water particle remains at 492 degrees until it is fully melted at 72 inches of 

distance traveled. At 72 inches the particle is fully melted (melt ratio = 1.0). Beyond 72 inches the fully melted 

particle continues to rise in temperature while continuing to evaporate. Although the computer code models the air 

flow and ice crystal physics through the inlet portion of the engine, the subsequent figures will illustrate the flow 

conditions of wet-bulb temperature and melt ratio only through the fan-core and LPC, since those are the areas 

where there can be risk of accretion due to ice crystals. Details of ice crystal temperature and static temperature of 

the air as a function of temperature data are provided in Appendix F.

Methodology to Determine Ice Risk

The methodology to determine whether there is a potential risk of ice accretion throughout the flight trajectory in the 

low pressure compression system involved tracking the wet-bulb temperature and the melt ratio through the flow 

path. The figures below illustrate how varying the ice particle size and temperature above ISA through the descent 

affected the local wet-bulb temperature and the melt ratio through each blade row in the fan-core and LPC. To 

illustrate this methodology Figure 16(a, b) is provided as an example. Figure 16(a) shows the seven descent mode 

altitudes that were analyzed, from 39000 to 20047 feet. In this and similar figures, the solid lines show the 

calculated wet-bulb temperature while the hatched lines show the melt ratio.

 (a) (b)

Figures 16(a, b): Wet-bulb temperature and melt ratio both indicate that there is a risk of ice accretion 

between stage-3 and stage-4 during descent. (a) All altitudes. (b) Risk of ice accretion at 38334 feet. 

With an ice particle size of 5 μm, an IWC of 4 g/m3

, and the inlet temperature of +36 R offset from the ISA, it was 

found that at 38334 feet altitude, the wet-bulb temperature and the melt ratio criteria are both met at the same 

location, as indicated by the gray shaded area of Figure 16(a). Figure 16(b) shows the results at the 38334 feet 

extracted from Figure 16(a). This indicates that there is a risk of ice accretion in the stator gap of stage-3, 

specifically just past the stator trailing edge. The wet-bulb temperature in the stage-3 stator gap is 498.6 R. The 

range of static temperature is 513.5-514.8 R, while the total temperature is 519.4 R. This methodology was used in 

the parametric icing risk analysis that follows, where particle size, IWC, and ISA offset temperature were varied 

through the flight trajectory (Figure 11), which includes two cruise altitudes and a descent mode. 

Parametric Icing Risk Analysis

The parametric study of the engine performance was carried out by varying the specified inlet conditions of ice 

particle size, concentration, and ambient temperature offset above the ISA. This study extends the work from an 

earlier paper16 with updated COMDES and MELT analysis codes, as well as a broader range of IWC. Furthermore 

the complete analysis results are included in the Appendices. Each cruise altitude was studied at four separate 

operating points, representing different thrust settings, as shown in Figure 11. In Figures 18-23, the ice particle size 

studied were 5, 10, 25, 50, and 100 μm; the ISA temperature increase was varied from +18 R to +36 R. The cruise 

conditions studied were at a range of engine thrust settings from 100% to 69.9% of maximum thrust for the given 

TWB = 498.6 – 499.0 R

TStat = 513.5 – 514.8 R 

TTot = 519.4 R

NASA/TM—2013-218094 22
altitude. In the descent mode, the thrust was set at 10% of maximum thrust at each altitude analyzed. The ice

concentrations in this study were 2, 4, and 9 g/m3

. The results shown in the following figures indicate whether there 

is a risk of ice accretion at the specific altitude operating condition, ice crystal concentration, size, and temperature 

above ISA. The scale in Figures 18-23 indicates the wet-bulb temperature variation through the blade rows and axial 

gaps in the fan-core and low pressure compressor. The melt ratio is also plotted on a scale from 0.0 – 1.0, where 0.0 

indicate no melting, and 1.0 indicates an ice particle that is 100% melted. Note that the inlet relative humidity was 

kept at 10%, since it was noticed early in the analysis that it did not have a strong effect on the results. It was 

observed that even if the ambient relative humidity at the fan face was 80%, the rise in temperature through the rotor 

blades quickly reduced the local relative humidity in each stage to significantly lower levels, as illustrated in Figure 

17. The rate at which the relative humidity is reduced through the stages is also a function of engine thrust level, as 

shown in Figure 17. The local value of relative humidity has a direct effect on the local wet-bulb temperature 

determination, as calculated by the equations (23, 24, and 25). 

Figure 17: Change in relative humidity through the five stage fan-core and low pressure compressor, at 

100% and 10% engine thrust levels. Note that the relative humidity is quickly reduced in each subsequent stage. 

Cruise at 35000 feet: 

The analysis was conducted at the altitude cruise condition of 35000 feet using the methodology described above. 

The engine thrust level was varied between 100% and 69.9% of max thrust at this cruise altitude. The particle size 

was varied from 5 μm to 100 μm, and the IWC was varied between 2 and 9 g/m3

, but only the results for the 2 g/m3 

are presented below as representative at this cruise altitude. 

NASA/TM—2013-218094 23
 (a) (b) 

 

 (c) (d) 

Figure 18(a-d): Cruise condition at 35000 feet altitude, with particle sizes of 5 μm (a, b) and 10 μm (c, d) and 

ISA temperatures of +18R (a, c) and +36R (b, d).

The results illustrated in Figure 18(a-d) show no risk of ice accretion is possible at this cruise condition with these 

particle sizes (5 and 10 μm), since the wet-bulb temperatures are excessively high in the compressor stages where 

the 10% melt ratio condition is met. For example, the 10% melt ratio criterion is reached in stage-3 as shown in 

Figure 18(a), but the wet-bulb temperature there is 512 R, and is well above the 499 R temperature limit. The effects 

of ice particle size and elevated ISA temperature can be seen in the location within the LPC where the minimum 

melt ratio criterion of 10% is reached. At all of these conditions, even though the melt ratio of 10% is achieved in 

the LPC, the wet-bulb temperature is well above the 499 R limit, at that location. Therefore, there is no expected risk 

of ice accretion at these operating conditions. 

The ice crystal particle size was further increased at this cruise altitude to determine the risk of ice accretion, as 

shown in Figure 19(a-f). The particle sizes were 25, 50, and 100 μm, with the same increment of temperatures (+18 

R and +36 R) above ISA. The range of engine thrust settings varied from 100% to 69.9% of maximum thrust. 

NASA/TM—2013-218094 24
 (a) (b)

 

(c) (d) 

 

 (e) (f) 

Figures 19(a-d): Cruise 1 condition, 35000 feet altitude, with particle sizes of 25 μm (a, b), 50 μm (c, d) and 

100 μm (e, f) and ISA temperatures offsets of +18 R (a, c, e) and +36 R (b, d, f).

NASA/TM—2013-218094 25
The results illustrated in Figure 19(a-b) show that the 10% melt ratio limit is reached only in stage-5 with the 25 μm

particle. However, the wet-bulb temperature in stage-5 is well above the 499 R temperature limit. In Figure 19(c-f) 

the 50 and 100 μm particles do not melt through the entire fan-core LPC, and the melt ratio remains zero. Therefore, 

there is no risk of ice accretion at any of the conditions illustrated in Figures 19(a-f). Note that even though the ice 

particle may not have melted, there was some degree of sublimation, adding to the specific humidity of the air and is 

accounted for in the flow analyses. Appendix G is a listing of the NPSS cycle analysis and Appendix H is the 

corresponding output listing of the compressor analysis code for the altitude cruise conditions at 35000 feet.

Cruise at 39000 feet:

The next points in the flight trajectory analyzed were at the cruise altitude of 39000 feet. The ice crystal particle size 

was varied from 5 μm to 100 μm in diameter, with the temperature offset at +18 R and +36 R above ISA. The 

results are illustrated in Figures 20(a-j). The range of engine thrust settings at this cruise condition was varied from 

100% to 76.8% of maximum thrust.

 (a) (b)

 (c) (d) 

NASA/TM—2013-218094 26
 (e) (f)

 (g) (h)

 (i) (j)

Figures 20 (a-j): The cruise condition at 39000 feet altitude, with particle sizes of 5 μm (a, b) and 10 μm (c, d) 

25 μm (e, f), 50 μm (g, h), and 100 μm (i, j) and ISA temperatures offsets of +18 R (a, c, e, g, i) and +36 R (b, 

d, f, h, j).

NASA/TM—2013-218094 27
The results illustrated in Figure 20(a) show that the 10% melt ratio limit is reached in the axial gap at the leading 

edge of the rotor between stages 3 and 4 with the 5 μm particle and ISA temperature offset of +18 R. However, the 

wet-bulb temperature exceeds the maximum limit of 499 R for accretion to occur. In Figure 20(b), at the engine inlet 

temperature of ISA +36 R, the minimum melt ratio of above 10% is achieved in the stator of stage-3, while the wetbulb temperature exceeded the limit that would support ice accretion. In both of these cases, the melt ratio reaches 

the value of 1.0, indicating that the ice particle has completely melted before exiting the LPC. In Figure 20(c) with 

the 10 μm particle and +18 R ISA offset, the results indicate that the minimum melt ratio is achieved in the stator of 

stage-4. At the elevated ISA temperature of +36 R, Figure 20(d), the minimum melt ratio is reached at the leading 

edge of the stage-4 rotor. In both cases the wet-bulb temperature is too high to support ice accretion. In Figures 

20(e) the minimum melt ratio is not reached at the lower temperature of ISA +18 R, but is reached at ISA + 36 R 

near the trailing edge of the stage-5 stator, as shown in Figure 20(f). However, the wet-bulb temperature is well 

above the limit that would support ice accretion. The results with the 50 and 100 μm ice particle sizes as illustrated 

in Figures 20(g, h, and i, j) show that the minimum melt ratio limit is not reached at any stage within the fan-core 

and LPC. Furthermore, the wet-bulb temperature at the end of the LPC is well above the maximum limit for 

accretion. Appendix I is a listing of the NPSS cycle analysis and Appendix J is the corresponding output listing of 

the compressor analysis code for the altitude cruise conditions at 39000 feet.

Descent:

The next operating points in the flight trajectory that were analyzed were computed during the descent mode from 

the 39000 feet cruise altitude, as shown in Figure 11. These consisted of eight altitudes starting at 39000 feet and 

descending to 15435 feet, at +18 R, +27 R and +36 R ISA offset temperatures at reduced engine thrust level of 10% 

of maximum thrust at the given altitude. As before, the ice crystal particle sizes modeled were 5, 10, 25, 50, and 

100 μms in diameter. Due to the ice particle formation limits that are illustrated in Figure 14, there were seven 

altitudes that were analyzed at the +36 R offset temperature between 39000 feet and 20047 feet. In a more refined 

parametric study, it is suggested that smaller increments of altitude, particle size, ice particle concentration, relative 

humidity, and elevated ISA temperatures should be used. The calculated results of wet-bulb temperature and melt 

ratio at each computing station within the fan-core and LPC stages are illustrated in Figures 21(a-f) with an initial 

ice crystal particle diameter of 5 μm and IWC of 2 and 4 grams per cubic meter. Note that the analysis also included 

9 g/m3

, but the results indicated no risk of ice accretion at any altitude, or ISA offset temperature. 

 (a) (b) 

NASA/TM—2013-218094 28
 (c) (d)

 (e) (f)

Figures 21(a-f): Descent mode. The ice particle size used in the analyses was 5 μm. The inlet temperature 

specified were ISA +18R (a, b), ISA +27R (c, d), and ISA +36 R (e, f).

The results illustrated in Figure 21(a) show that the 10% melt ratio limit is reached in the stator and gap after stage-2 

with the 5 μm particle and ISA +18 R at an altitude of 15435 feet. In addition, the maximum wet-bulb temperature 

limit criterion of 499 R is also satisfied at this location. This would indicate that there is a potential risk for ice 

accretion. With the same values for particle size and ISA offset temperature, the IWC is increased to 4 g/m3

. 

However, in this case, the melt ratio criterion is not met where the wet-bulb temperature criterion is satisfied at any 

of the selected operating conditions in the descent flight trajectory, as shown in Figure 21(b). As the IWC is 

increased, the amount water vapor in the air due to sublimation and evaporation rises resulting in an increase in 

relative humidity as well as the wet-bulb temperature. Therefore there is no risk of ice accretion predicted for this 

case. In Figure 21(c), at the engine inlet temperature of ISA +27 R, there are three altitudes where there is a risk of 

ice accretion during descent. The first occurs at an altitude of 37357 feet near the trailing edge section of the stage-5 

stator and in the following gap. Similarly, at an altitude of 34281 feet the ice accretion risk coincides with that at 

37357 feet. The altitude of 15435 feet there is an ice accretion risk predicted in the broad region of the stage-1 rotorstator gap and through the stage-1 stator, likewise illustrated in Figure 21(c). When the IWC is increased from 2 to 

4 g/m3 the region where there is a predicted risk of ice accretion shifts to the stage-4 stator trailing edge and statorrotor gap as illustrated in Figure 21(d). At an ISA temperature offset of +36 R and the IWC of 2 g/m3

, there is a risk 

of ice accretion in the stage-3 stator trailing edge and stator-rotor gap in the descent from the cruise at an altitude of 

NASA/TM—2013-218094 29
39000 feet, as shown in Figure 21(e). When the IWC is increased to 4 g/m3

, the icing region of risk is at the altitude 

of 38334 feet and is located in the gap between the stage-3 stator and the stage-4 rotor, as illustrated in Figure 21(f). 

The NPSS listings along with the corresponding compressor analysis for the descent conditions shown in Figure 21 

(a-f) are provided in Appendices K and L, respectively. 

As mentioned previously, the parametric study also included analyzing an ice particle size of 10 μm with IWC of 2, 

4, and 9 g/m3 at the same range of ISA offset temperatures as in the previous descent analyses. For this particle size, 

a risk of ice accretion during descent was found only at an altitude of 15435 feet with an IWC of 9 g/m3 and an ISA 

temperature offset of +27 R. The accretion risk was located in the region of the stage-1 stator trailing edge and a 

portion of the gap prior to rotor-2, as illustrated in Figure 22 (details of NPSS and compressor analysis output are 

provided in Appendix M). 

Figure 22: Descent condition, from 39000 feet to 15435 feet altitude. There is a risk of icing with an ice 

particle size of 10 μm and a temperature offset of ISA +27 R.

The parametric analysis of the descent mode was continued by further studying the effects of even larger particle 

sizes at a fixed IWC of 2 g/m3 and at ISA offset temperatures of +18 R and +36 R. As during the cruise conditions, 

the particles sizes utilized to analyze the descent portion of the flight trajectory were 10, 25, 50 and 100 μm, and the 

results are presented in Figure 23(a-h). 

 (a) (b)

NASA/TM—2013-218094 30
 (c) (d)

 (e) (f)

 (g) (h)

Figures 23(a-h): Descent mode, from 39000 feet to 15435 feet altitude (a, c, e, g) and 39000 feet to 20047 feet 

altitude (b, d, f, h). The ice particle sizes used in the analyses were: 10 μm (a, b), 25 μm (c, d), 50 μm (e, f), and 

100 μm (g, h). The inlet temperature offset specified were ISA +18R (a, c, e, g) and ISA +36 R (b, d, f, h). 

NASA/TM—2013-218094 31
In Figures 23(a, c, e, g) with particle sizes of 10, 25, 50, and 100 μm, respectively, and an inlet temperature offset 

from ISA of +18 R, and an IWC of 2 g/m3

, the melt ratio was well below the criterion limit minimum of 10%. 

Similarly, in Figure 23(d, f, h) with the equivalent particle size and an inlet offset temperature of ISA +36 R, the 

melt ratio was well below the criterion limit of 10% minimum. Therefore, no risk of ice accretion was expected at 

these conditions. The only case where the minimum melt ratio criterion was met is the 10 μm and +36 R ISA 

temperature offset at the altitude of 39000 feet, in the stage-5 stator as shown in Figure 23(b). However the wetbulb temperature there was almost 3 R above the specified maximum criterion. Therefore there was no risk of ice 

accretion. The NPSS listings for the descent conditions shown in Figure 23 (a-h) are provided in Appendix N with 

the corresponding compressor analysis detailed in Appendix O. 

Summary of Engine Icing Risk Analysis: 

Figures 24(a) and Table II illustrate where the risk of ice accretion was identified along the flight trajectory. Figure 

24(b) shows where this notional engine may have a risk of ice accretion in comparison with the events that have 

been reported in the open literature. The engine events predicted in this study are also summarized in Table II. There 

were other conditions analyzed parametrically in this study, and the cases shown are a sample of the results to

illustrate the method used to determine the icing risk based on the wet-bulb temperature and melt ratio criteria. 

(a)

 

(b)

 

Figures 24(a, b): (a) Aircraft flight trajectory of the notional engine with icing risk identified at two 

particular operating points. (b) Icing risks of notional engine compared to known engine icing events. 

NASA/TM—2013-218094 32
Table II – Summary of Engine Icing Risk at Selected Operating Points Along Flight Trajectory

Altitude, ft Icing 

Risk, 

Stage

Particle 

Size, μm

IWC, 

g/m3

ISA Offset 

Temp, R

Twb , R TStatic , R TTotal , R Ref. 

Figure

Symbol, 

Figure 

24(a, b)

39000 3 5 2 + 36 498.8 521.9-524.1 529.1 20 (e)

38334 4 5 4 + 27 498.4 513.9-515.8 520.1 20 (d)

38334 3 5 4 + 36 498.6 513.5-514.8 519.4 20 (f)

37357 5 5 2 + 27 498.9 519.8-520.2 526.3 20 (c) 

34281 5 5 2 + 27 498.7 517.6-518.0 523.9 20 (c) 

15435 1 5 2 + 27 498.2 510.3-512.2 517.5 20 (c) 

15435 2 5 2 + 18 498.5 505.9-508.0 513.0 20 (a)

15435 1 10 9 + 27 498.7 512.2-513.0 517.4 21

IV.Assumptions and Recommendations for Future Research

This study is ongoing research and is intended to be a status report on the current state of the engine icing modeling 

tool development effort at NASA Glenn Research Center utilizing the NPSS-COMDES-MELT analysis tool. Simple 

empirical models have been used that were derived from test data to determine the aero-thermodynamic conditions 

within the fan and low pressure compressor that identified the risk of ice accretion. Two key parameters were 

identified to predict whether there is a risk of ice accretion within any turbofan engine. Numerous other simplifying 

assumptions were made that enabled studying the very complex physics involved in engine icing due to ice crystal 

ingestion. The actual IWC ice crystal concentration (grams of ice per cubic meter of air) in ice clouds is currently

unknown. Likewise, the actual particle size existing in the atmosphere is also unknown, and is likely larger than was 

assumed in this study, before entering the fan and LPC, but may be broken up into much smaller particles upon 

impact with the high speed rotor blades and stator vanes of the compression system. Also, there may be a particle 

size distribution after impact, as opposed to a particle of a single size, as was assumed in this study. There is 

currently research in these areas that will attempt to quantify the ice particle impact dynamics, as well as the particle 

size distribution after impact. Therefore in this study it was assumed that the ice particles entering the engine have 

already been broken up into small particles due to impact with engine components. In addition it is assumed that the 

small particles are evenly distributed through the bypass duct and the engine core, as well as evenly distributed in 

the radial direction.

The low fidelity approach was selected for this study primarily to provide a fast capability to screen engines for 

potential icing risk in an ice crystal environment. It would be computationally expensive to model the three phase 

flow through the fan and low pressure compressor with a multidisciplinary, time-dependent code that simulates the 

aerodynamics, thermodynamics, ice particle physics, accretion, and heat transfer analyses through the blades and 

end walls. Additionally finer increments of altitude, ISA offset temperatures, and ice particle size can be considered 

for a more refined parametric study. Ranges of particle concentrations at altitude obtained from future flight tests 

may reduce the need to parametrically vary IWC.

Ice accretion is not addressed in the current study, but should be considered in the future. Likewise there is no radial 

distribution of blockage currently available in the low fidelity approach used in this study. However, a bulk value of 

blockage at a specific location in the compressor is available in the code and has been previously demonstrated. 

Further research is necessary to model the effects of shape and roughness of the accreted ice on the surfaces of the 

flow path walls and stator vanes. Unusual ice shapes that accrete on the compressor stators and walls will likely 

have a detrimental effect on the pressure recovery and losses and the cumulative effects on the downstream 

compressor stages, as well as the overall power balance of the engine system. Erosion of ice due to impact of 

incoming ice particles on the accreted ice was likewise not considered in this study, but is a topic for future research. 

Another area of research may be to study the dependence of accretion on the local Mach number and particle 

concentration. High fidelity compressor flow simulations in the future should consider these effects. There is no data 

available on the accreted ice shapes in turbomachinery, as the ice shapes may likely be influenced by the unsteady 

air flow fluctuations between the rotors and stators. Experiments that quantify the accreted ice shapes in rotating 

turbomachinery need to be conducted to determine the unsteady effects on ice accretion for high fidelity flow 

NASA/TM—2013-218094 33
analysis and ice accretion code validation and calibration. These results can also be incorporated in the low fidelity 

modeling to improve its current capabilities. 

The current study does not have an ice shedding model. Based on observed accretion behavior, the assumption in 

this study is that if the wet-bulb temperature is below freezing, then the ice that accretes is firm, and does not shed, 

but continues to grow as a function of time. Although laboratory testing has shown that there is some level of ice 

buildup at conditions that were at wet-bulb temperatures approximately 499 R, the ice accretion at these conditions 

was not firm, but was loose “slushy ice” that quickly shed before a substantial amount of ice could accrete. The 

current analysis was limited for this reason to wet-bulb temperatures less than or equal to 499 R. Even though this 

was not modeled, it is thought that the shedding of loose ice may cause a problem in the compressor by choking the 

downstream compressor stages due to the instantaneous addition of mass flow, thus it could possibly force the fan or 

other upstream stages to surge. Further research is needed in this area to study its effect on the compressor and 

engine system performance. 

V.Conclusion

The purpose of this effort was to develop a system of codes to provide a first order predictive capability to estimate 

the risk of the occurrence of engine ice accretion during flight through high altitude convective ice crystal clouds. A 

first generation computational tool has been developed for estimating the susceptibility of engines to icing. The tool 

consists of an engine thermodynamic cycle model, a compressor mean line flow analysis model that calculates the 

aerodynamic performance of each blade row, and an ice particle sublimation, melting, and evaporation model that 

tracks the state of the ice/water particle through the compressor blade rows. Using this fully integrated capability, a 

notional turbofan engine was studied to predict the risk of ice accretion in the low pressure compressor, operating in 

a gas turbine engine system environment through a flight trajectory of a typical commercial aircraft. Two aerothermodynamic parameters were identified as the criteria for determining whether there is a risk of ice accretion

when flying in a high altitude ice crystal environment: the local wet-bulb temperature and the ice melt ratio. A 

parametric approach was utilized to determine the risk of accretion in the low pressure compressor over a range of 

atmospheric conditions while varying ice crystal size, ice water content, and ambient temperature. With the 

assumptions that were made in this study, it was determined that the notional engine would experience a risk of ice 

accretion at multiple operating conditions during the descent mode of the flight trajectory, with ice particle sizes on 

the order of 5 μm and ambient temperature offset from the ISA were in the range of +18 R to +36 R. The results of 

this study indicate that the risk of ice accretion on this engine occurs between 39000 – 34000 feet, and near 15000 

feet. At the higher altitude near 39000 feet, the risk of accretion occurred in the rear LPC stages, while at the lower 

altitude near 15000 feet, the risk of accretion occurred in the front stages. All of the predicted icing risk operating 

points identified for this notional engine were within the envelope of the known icing events of commercial aircraft 

engines that have been reported in the literature. 

NASA/TM—2013-218094 34
APPENDICES

A. Normalized Growth Rate as a function of LWCm/TWCinj, Figure 8. 

B. Design Point Performance; compressor code output listing for the Fan-Core and LPC. 

C. Vehicle Flight Trajectory (FLOPS output listing), Figure 11. 

D. Overall Performance Characteristic Maps; pressure ratio, efficiency vs. flow and RPM 

(with baseline aerodynamic blockages), Figures 12 and 13. 

E. Fan-Core and LPC Performance along Engine Operating Line, Figures 12 and 13. 

F. Ice Particle Temperature and Static Air Temperature from Inlet through LPC, Figure 15. 

G. NPSS cycle analysis for the altitude cruise conditions at 35000 ft, Figure 18(a) to (d) and 

Figure 19(a) to (d). 

H. Compressor code analysis for the altitude cruise conditions at 35000 feet, Figure 18(a-d) 

and Figure 19(a-d). 

I. NPSS cycle analysis for the altitude cruise conditions at 39000 feet, Figure 20(a-j). 

J. Compressor code analysis for the altitude cruise conditions at 39000 feet, Figure 20(a-j). 

K. NPSS cycle analysis for the descent conditions, Figure 21(a-f). 

L. Compressor code analysis for the descent conditions, Figure 21(a-f). 

M. NPSS cycle analysis and compressor code analysis for the descent conditions, Figure 22. 

N. NPSS cycle analysis for the descent conditions, Figure 23(a-h). 

O. Compressor code analysis for the descent conditions, Figure 23(a-h).

Nomenclature; Variable Description of COMDES Compressor Code Output 

Area1 Rotor leading edge annular area, in2

A1/A* Ratio of annular area at the rotor leading edge to the choke area 

A* Choke area of rotor, in2

AeroBl Aerodynamic blockage (e.g., 0.98 = 2% blockage) 

AthrRotor Throat area of rotor, in2

Alfa Absolute flow angle at stator exit, degrees 

Abs MACH Absolute Mach number 

Beta BLADE Blade angle, degrees 

B2 axial Rotor exit height in axial direction, in. 

BetaFlo Relative flow angle, degrees 

BetaBlade Rotor blade angle, degrees 

Beta FLO Relative flow angle, degrees 

C Absolute velocity, ft/s 

ChokeMargin Choke margin of rotor 

Cu Tangential component of absolute velocity at rotor leading edge, ft/s 

Cm Meridional component of velocity at rotor leading edge, ft/s 

Cp Specific heat at constant pressure 

CFM Volumetric flow rate, ft3

/min 

DelRCu Angular momentum change through blade 

Del Enthalpy Enthalpy rise 

Del_H/U^2 Head coefficient (Enthalpy rise / tip speed squared) 

NASA/TM—2013-218094 35

The following appendixes can be accessed from the hyperlinks below or from the bookmarks 

panel located on the left-hand side of this document. 
Del T Total temperature rise, R

Deviat Flow deviation angle from blade trailing edge, degrees 

Diff Fct Diffusion factor 

DIFF LOSS Diffuser, or stator loss coefficient 

Efficiency Efficiency, adiabatic

EffAVG Rotor average efficiency, adiabatic

GAMMA Ratio of specific heats (Cp / Cv). 

GHP Horsepower 

Incid Rotor leading edge incidence angle, degrees

NBLAD Number of rotor blades 

Ns Specific speed

Ns nondim Specific speed, non-dimensional 

OPR Overall Pressure ratio, total-to-total

PR Stage pressure ratio, total-to-total

Pdisch Discharge pressure, psia

Pt Inlet total pressure, psia 

Ps Static pressure, lbf / ft^2

POTH Potential ratio hub, absolute axial velocity at hub / axial velocity at mean radius radius 

(typical value can be 0.9, or 10% lower velocity at hub) 

POTS Potential ratio shroud, absolute axial velocity at tip / axial velocity at mean radius (typical 

value can be 1.1, or 10% higher velocity at tip) 

RPM cor Shaft rotational speed, corrected to standard temperature conditions of 518.7 R 

Rel Mach Relative Mach number

THK Rotor blade thickness, in 

R Radius from centerline at rotor leading edge, in 

Rg Gas constant, Universal gas constant / mole weight, for air Rg = 53.35 ft-lbf / R 

RPM act Shaft rotational speed, rotations per minute 

Reynolds# Reynolds number 

Slip F Slip factor

Solidity Solidity

SCFM Volumetric flow rate, standard cubic feet per minute (14.7 psia, 518.7 R) 

Stator Setting angle at stator, or inlet guide vane exit, degrees

THK Blade normal thickness, in

Tt Inlet total temperature, degrees, R

Ts Static temperature, R

TR Temperature ratio, total-to-total

Texit Total temperature at last stage exit, R

U Blade peripheral velocity at rotor leading edge, ft/sec

U1 corrected Rotor peripheral tip speed corrected to standard inlet temperature 

W act Mass flow rate, lbm/s

W cor Mass flow rate corrected to standard pressure and temperature conditions (14.7 psia, 

518.7 R) 

Ws1/W2 Inlet tip relative velocity / exit relative velocity

W Relative velocity, ft/s

NASA/TM—2013-218094 36
Subscripts

1 Rotor inlet (leading edge)

2 Rotor exit (trailing edge) 

3 Radial diffuser vane inlet 

4 Radial diffuser exit

NASA/TM—2013-218094 37

Appendix A: Normalized Growth Rate as a function of LWCm/TWCinj

TITLE = "Normalized Growth Rate vs LWC_m/TWC_inj" 

VARIABLES = "LWC_m/TWC_inj","Normalized Growth Rate(G/G_max)" 

ZONE T=" M=0.2 ", I = 5.0 

 0.03 0.0000 

 0.22 0.1092 

 0.31 0.4493 

 0.31 0.2568 

 0.32 0.1787 

ZONE T=" M=0.25", I = 5.0 

 0.14 0.0978 

 0.14 0.1024 

 0.15 0.1866 

 0.21 0.1211 

 0.21 0.0913 

ZONE T=" M=0.3 ", I = 2.0 

 0.04 0.0000 

 0.25 0.0188 

ZONE T=" Accretion Risk", I = 2.0 

 0.10 0.0000 

 0.10 0.5000 

NASA/TM—2013-218094 A–1

APPENDIX B: Design Point Performance; compressor code output listing for the Fan-Core and LPC. 

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 12.0 ************************

 

 COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 RESET = 0.000 BLEED = 0.000 DPInc = 6.012 EfDer = 0.999 RH = 0.00

 

 W act RPM act Pt Tt POTS POTH AeroBl

 176.353 3776.000 15.107 522.810 1.000 1.000 0.980

W Kg/sec = 80.16045 

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.279 3761.129 1.402 0.249 53.349 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 135665.266 138378.281 1.657 831.557 501.715 619.754 1.235

 

 ROTOR LEADING EDGE CONDITIONS, STAGE 1

 R1 Stator Alfa C1 CU1 Cm1 M abs U1 corrected

 TIP 20.63 0.00 -0.02 420.48 -0.14 420.48 0.38 677.10

 MEAN 17.06 0.00 -0.02 420.48 -0.14 420.48 0.38

 HUB 12.51 0.00 -0.02 420.48 -0.14 420.48 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 M rel

 TIP 58.27 50.47 7.80 679.80 799.45 13.67 508.04 489.09 0.72

 MEAN 53.21 47.20 6.01 562.16 702.13 13.67 508.04 489.09 0.64

 HUB 44.44 38.62 5.82 412.23 588.94 13.67 508.04 489.09 0.53

 

 ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2

 TIP 20.63 668.44 381.63 548.79 1126.50 0.59

 MEAN 18.04 703.47 422.65 562.34 1120.84 0.63

 HUB 15.00 808.49 553.16 589.63 1110.61 0.73

 

 U2 W2 Wu2 MachRel2 DelRCu Ws1/W2 

 TIP 679.80 624.55 298.16 0.55 7876.04

 MEAN 594.32 587.96 171.67 0.52 7625.47 1.33

 HUB 494.28 592.57 58.88 0.53 8299.19

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 Eff2uC Eff2incC

 TIP 19.31 1.28 15.21 564.50 1.08 527.19 500.44 0.92 0.91

 MEAN 19.16 1.27 14.69 563.17 1.08 521.86 497.33 0.92 0.91

 HUB 19.56 1.29 13.74 566.74 1.08 512.19 491.44 0.92 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. Diff Fct Solidity AvgRotEff

 TIP 34.82 28.52 24.20 4.32 0.93 0.30 2.90

 MEAN 36.93 16.98 12.70 4.28 0.93 0.25 3.51 0.91

 HUB 43.17 -5.70 -9.30 3.60 0.93 0.10 4.78

 

 blockage3 Cor/U1 Cor/Incid

 0.950 1.000 0.999

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 

 18.0711 715.0781 421.8333 577.4023 1120.8982 0.6380 -0.0051

 

 Pt3 Ps3 Ts3 TwetBulb3 Vane# FloAlpha3 VaneAlpha3 Incid3

 19.2960 14.6681 522.0970 497.4292 24.0000 36.1508 35.4000 -0.7508

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th

 18.0711 598.5550 421.8333 732.2645 1134.5392 0.5276 0.2817

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 19.2234 15.8993 534.8818 504.7196 528.7961 0.0251 0.4304

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 

 18.0829 548.0781 0.0000 548.0781 1139.6547 0.4809 0.3498

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 16.3457 539.7160 507.3303 0.0000 0.0600 0.0399 0.3748

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Texit Del T Ns Ns nondim

 0.8765 19.1525 1.2678 564.8056 41.9956 217.3922 1.6852

 Del Enthalpy Del_H/U^2 GHP Reynolds#

 261458.922 0.566 2605.665 1768070.250

 

NASA/TM—2013-218094 B–1
 

 COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 RESET = 0.000 BLEED = 0.000 DPInc = 6.012 EfDer = 1.000 RH = 100.00

 

 W act RPM act Pt Tt POTS POTH AeroBl

 176.353 3776.000 19.153 564.806 1.000 1.000 0.980

W Kg/sec = 80.16045 

 

 W cor RPM cor GAMMA Cp R Blades THK

 141.243 3618.600 1.402 0.249 53.349 56.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 135665.266 138378.281 1.436 590.487 411.342 474.134 1.153

 

 ROTOR LEADING EDGE CONDITIONS, STAGE 2 

 

 R1 Stator Alfa C1 CU1 Cm1 M abs U1 corrected

 TIP 20.55 0.00 -0.02 520.10 -0.18 520.10 0.46 648.91

 MEAN 18.08 0.00 -0.02 520.10 -0.18 520.10 0.46

 HUB 15.21 0.00 -0.02 520.10 -0.18 520.10 0.46

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 M rel

 TIP 52.48 46.36 6.12 677.16 853.98 16.61 542.22 542.22 0.75

 MEAN 48.89 42.30 6.59 595.71 790.94 16.61 542.22 542.22 0.69

 HUB 43.95 37.84 6.11 501.20 722.41 16.61 542.22 542.22 0.63

 

 ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 56.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2

 TIP 20.42 599.80 307.48 514.99 1169.13 0.51

 MEAN 18.01 614.66 321.99 523.58 1164.97 0.53

 HUB 15.22 668.79 403.63 533.26 1160.89 0.58

 

 U2 W2 Wu2 MachRel2 DelRCu Ws1/W2 

 TIP 672.88 631.45 365.40 0.54 6282.35

 MEAN 593.46 589.77 271.47 0.51 5802.28 1.45 

 HUB 501.63 542.19 97.99 0.47 6147.23

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 Eff2uC Eff2incC

 TIP 23.00 1.20 19.21 598.04 1.06 568.00 568.00 0.92 0.91

 MEAN 22.69 1.18 18.76 595.50 1.05 563.96 563.96 0.92 0.91

 HUB 22.91 1.20 18.29 597.33 1.06 559.99 559.99 0.92 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. Diff Fct Solidity AvgRotEff

 TIP 30.84 35.36 31.50 3.86 0.93 0.32 2.90

 MEAN 31.59 27.41 23.50 3.91 0.93 0.32 3.30 0.91

 HUB 37.12 10.41 6.50 3.91 0.93 0.32 3.92

 

 blockage3 Cor/U1 Cor/Incid

 0.950 1.000 1.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 

 17.9595 622.9638 322.8948 532.7503 1165.5101 0.5345 0.0054

 

 Pt3 Ps3 Ts3 TwetBulb3 Vane# FloAlpha3 VaneAlpha3 Incid3

 22.8224 18.7846 564.5516 564.5516 46.0000 31.2196 30.6000 -0.6196

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th

 17.9595 533.7812 322.8948 623.8456 1174.3680 0.4545 0.2457

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 22.7771 19.7642 573.1653 573.1653 511.1510 0.0210 0.3283

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 

 17.8235 526.5400 0.0000 526.5400 1175.0248 0.4481 0.2436

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 19.7853 573.8065 573.8065 0.0000 0.0600 0.0367 0.2508

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Texit Del T Ns Ns nondim

 0.8798 22.7126 1.1859 596.9559 32.1503 248.8247 1.9289

 

Del Enthalpy Del_H/U^2 GHP Reynolds#

 200283.328 0.442 1995.997 1593531.250

 

 

 

NASA/TM—2013-218094 B–2
 COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 RESET = 0.000 BLEED = 0.000 DPInc = 6.012 EfDer = 1.000 RH = 100.00

 

 W act RPM act Pt Tt POTS POTH AeroBl

 176.353 3776.000 22.713 596.956 1.000 1.000 0.980

W Kg/sec = 80.16045 

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.447 3519.808 1.402 0.249 53.349 56.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 135665.266 138378.281 1.530 545.479 356.621 429.765 1.205

 

 ROTOR LEADING EDGE CONDITIONS, STAGE 3 

 

 R1 Stator Alfa C1 CU1 Cm1 M abs U1 corrected

 TIP 20.07 0.00 -0.02 494.31 -0.17 494.31 0.42 616.45

 MEAN 17.74 0.00 -0.02 494.31 -0.17 494.31 0.42

 HUB 15.05 0.00 -0.02 494.31 -0.17 494.31 0.42

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 M rel

 TIP 53.23 46.36 6.87 661.34 825.80 20.12 576.56 576.56 0.70

 MEAN 49.79 43.40 6.39 584.52 765.64 20.12 576.56 576.56 0.65

 HUB 45.10 38.84 6.26 495.92 700.32 20.12 576.56 576.56 0.59

 

 ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 56.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2

 TIP 19.81 578.30 301.72 493.36 1202.15 0.48

 MEAN 17.51 592.00 316.36 500.38 1198.49 0.49

 HUB 14.85 643.66 394.80 508.36 1194.87 0.54

 

 U2 W2 Wu2 MachRel2 DelRCu Ws1/W2 

 TIP 652.78 605.51 351.06 0.50 5980.44

 MEAN 576.87 564.13 260.52 0.47 5541.31 1.47 

 HUB 489.33 517.07 94.53 0.43 5865.40

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 Eff2uC Eff2incC

 TIP 26.79 1.18 22.86 628.57 1.05 600.66 600.66 0.92 0.91

 MEAN 26.47 1.17 22.40 626.25 1.05 597.00 597.00 0.92 0.91

 HUB 26.71 1.18 21.92 627.97 1.05 593.39 593.39 0.92 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. Diff Fct Solidity AvgRotEff

 TIP 31.45 35.43 31.50 3.93 0.93 0.33 2.90

 MEAN 32.30 27.50 23.50 4.00 0.93 0.33 3.28 0.91

 HUB 37.83 10.53 6.50 4.03 0.93 0.33 3.87

 

 blockage3 Cor/U1 Cor/Incid

 0.950 1.000 1.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 

 17.3924 597.9450 318.4314 506.1024 1199.2048 0.4986 0.0115

 

 Pt3 Ps3 Ts3 TwetBulb3 Vane# FloAlpha3 VaneAlpha3 Incid3

 26.6147 22.4534 597.7551 597.7551 46.0000 32.1774 31.5000 -0.6774

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th

 17.3924 514.7593 318.4314 605.2898 1206.9297 0.4265 0.2467

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 26.5737 23.4463 605.4810 605.4810 471.9919 0.0196 0.3444

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 

 17.1214 498.8988 0.0000 498.8988 1208.2664 0.4129 0.2604

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 23.5633 606.8229 606.8229 0.0000 0.0600 0.0368 0.2741

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Texit Del T Ns Ns nondim

 0.8804 26.5007 1.1668 627.5978 30.6420 241.5946 1.8728

 

Del Enthalpy Del_H/U^2 GHP Reynolds#

 191004.031 0.448 1903.521 1533169.125

 

 

NASA/TM—2013-218094 B–3
 COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 RESET = 0.000 BLEED = 0.000 DPInc = 6.012 EfDer = 1.000 RH = 100.00

 

 W act RPM act Pt Tt POTS POTH AeroBl

 176.353 3776.000 26.501 627.598 1.000 1.000 0.980

W Kg/sec = 80.16045 

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.603 3432.807 1.401 0.249 53.349 56.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 135665.266 138378.281 1.638 513.330 313.412 401.059 1.280

 

 ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 M abs U1 corrected

 TIP 19.26 0.00 -0.02 467.07 -0.16 467.07 0.39 576.95

 MEAN 16.97 0.00 -0.02 467.07 -0.16 467.07 0.39

 HUB 14.32 0.00 -0.02 467.07 -0.16 467.07 0.39

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 M rel

 TIP 53.66 46.36 7.30 634.65 788.13 23.91 609.40 609.40 0.65

 MEAN 50.14 43.80 6.34 559.22 728.74 23.91 609.40 609.40 0.60

 HUB 45.30 37.84 7.46 471.87 664.06 23.91 609.40 609.40 0.55

 

 ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 56.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2

 TIP 18.88 549.86 288.91 467.84 1232.20 0.45

 MEAN 16.57 560.60 299.29 474.02 1228.68 0.46

 HUB 13.89 605.97 368.58 480.98 1225.18 0.49

 

 U2 W2 Wu2 MachRel2 DelRCu Ws1/W2 

 TIP 622.13 574.38 333.22 0.47 5457.75

 MEAN 546.14 534.45 246.85 0.43 4963.05 1.48

 HUB 457.70 489.16 89.12 0.40 5121.93

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 Eff2uC Eff2incC

 TIP 30.60 1.15 26.68 656.43 1.05 631.21 631.21 0.92 0.91

 MEAN 30.21 1.14 26.19 653.82 1.04 627.60 627.60 0.92 0.91

 HUB 30.33 1.14 25.66 654.66 1.04 624.03 624.03 0.92 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. Diff Fct Solidity AvgRotEff

 TIP 31.70 35.46 31.50 3.96 0.93 0.33 2.90

 MEAN 32.27 27.51 23.50 4.01 0.93 0.33 3.29 0.91

 HUB 37.46 10.50 6.50 4.00 0.93 0.33 3.90

 

 blockage3 Cor/U1 Cor/Incid

 0.950 1.000 1.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 

 16.4812 552.7786 300.9688 463.6615 1230.4952 0.4492 0.0535

 

 Pt3 Ps3 Ts3 TwetBulb3 Vane# FloAlpha3 VaneAlpha3 Incid3

 30.3375 26.4107 629.4775 629.4775 46.0000 32.9881 32.4000 -0.5881

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th

 16.4812 479.6051 300.9688 566.2184 1236.6398 0.3878 0.2712

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 30.3053 27.3165 635.7798 635.7798 456.5731 0.0177 0.3598

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 

 16.0960 455.1656 0.0000 455.1656 1238.4919 0.3675 0.2665

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 27.5306 637.6857 637.6857 0.0000 0.0600 0.0367 0.3221

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Texit Del T Ns Ns nondim

 0.8800 30.2252 1.1405 654.9698 27.3719 247.8075 1.9210

 

Del Enthalpy Del_H/U^2 GHP Reynolds#

 170742.469 0.441 1701.597 1524277.375

 

NASA/TM—2013-218094 B–4
 COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 RESET = 0.000 BLEED = 0.000 DPInc = 6.012 EfDer = 1.000 RH = 100.00

 

 W act RPM act Pt Tt POTS POTH AeroBl

 176.353 3776.000 30.225 654.970 1.000 1.000 0.980

W Kg/sec = 80.16045 

 

 W cor RPM cor GAMMA Cp R Blades THK

 96.379 3360.311 1.401 0.249 53.349 56.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 135665.266 138378.281 1.815 509.668 280.740 390.276 1.390

 

 ROTOR LEADING EDGE CONDITIONS, STAGE 5 

 

 R1 Stator Alfa C1 CU1 Cm1 M abs U1 corrected

 TIP 18.32 0.00 -0.02 423.76 -0.15 423.76 0.34 537.20

 MEAN 15.91 0.00 -0.02 423.76 -0.15 423.76 0.34

 HUB 13.07 0.00 -0.02 423.76 -0.15 423.76 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 M rel

 TIP 54.94 47.36 7.58 603.68 737.68 27.88 640.00 640.00 0.59

 MEAN 51.06 44.80 6.26 524.36 674.30 27.88 640.00 640.00 0.54

 HUB 45.47 38.84 6.63 430.68 604.31 27.88 640.00 640.00 0.49

 

 ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 56.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2

 TIP 17.94 513.60 284.99 427.28 1259.83 0.41

 MEAN 15.50 518.15 284.04 433.36 1255.87 0.41

 HUB 12.59 552.12 333.53 439.99 1251.93 0.44

 

 U2 W2 Wu2 MachRel2 DelRCu Ws1/W2 

 TIP 591.16 525.65 306.17 0.42 5115.32

 MEAN 510.67 489.04 226.63 0.39 4404.31 1.51 

 HUB 414.86 447.44 81.33 0.36 4201.11

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 Eff2uC Eff2incC

 TIP 34.40 1.14 30.68 681.97 1.04 659.98 659.98 0.92 0.91

 MEAN 33.79 1.12 30.06 678.22 1.04 655.84 655.84 0.92 0.91

 HUB 33.62 1.11 29.42 677.15 1.03 651.73 651.73 0.92 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. Diff Fct Solidity AvgRotEff

 TIP 33.70 35.62 31.50 4.12 0.93 0.35 2.90

 MEAN 33.24 27.61 23.50 4.11 0.93 0.34 3.34 0.91

 HUB 37.16 10.47 6.50 3.97 0.93 0.33 4.06

 

 blockage3 Cor/U1 Cor/Incid

 0.950 1.000 1.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 

 15.2185 524.1179 289.2517 437.0733 1256.2159 0.4172 -0.0050

 

 Pt3 Ps3 Ts3 TwetBulb3 Vane# FloAlpha3 VaneAlpha3 Incid3

 33.8612 30.0364 656.2099 656.2098 46.0000 33.4963 33.0000 -0.4963

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th

 15.2185 457.4107 289.2517 541.1941 1261.4308 0.3626 0.2117

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 33.8114 30.8730 661.6694 661.6694 440.8271 0.0328 0.3714

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 

 14.7013 427.1457 0.0000 427.1457 1263.5568 0.3381 0.3055

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 31.2244 663.9016 663.9015 0.0000 0.0600 0.0367 0.3021

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Texit Del T Ns Ns nondim

 0.8811 33.7963 1.1181 679.1149 24.1451 258.2498 2.0019

 

Del Enthalpy Del_H/U^2 GHP Reynolds#

 150727.172 0.431 1502.127 1555663.750

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR

 974215.94 9708.9072 172.2792 2.2371 0.8686 6.0120 1.2990

NASA/TM—2013-218094 B–5

APPENDIX C: Vehicle Flight Trajectory (FLOPS output listing) 

 SEGMENT 1 CLIMB 

 WEIGHT ALTITUDE MACH NO. DELTA T DELTA D DELTA F THRUST FUEL FLOW EX POW CLIFT LIFT L/D Q PCODE 

 ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC DH/DT* CDRAG DRAG SP RANGE NOX ENG PAR

 172183. 0. 0.3000 0.00 0.0 0. 38219. 19137. 3205.2 0.93275 172183. 16.006 133.3 1 

 1743. 198.44 9.64 0.0 526. 1.00000 0.50072 2047.8 0.05828 10757. 0.01037 0.0 28.231

 172053. 839. 0.3467 0.41 1.5 130. 36279. 18935. 3685.2 0.71920 172053. 19.327 172.8 1 

 3154. 228.70 10.05 1.5 655. 1.00000 0.52194 2047.8 0.03721 8902. 0.01208 3.3 28.385

 171961. 1500. 0.3799 0.29 1.2 92. 35174. 18824. 3935.6 0.61342 171961. 20.370 202.5 1 

 4267. 250.00 10.34 2.6 747. 1.00000 0.53517 2264.9 0.03011 8442. 0.01328 5.7 28.570

 171847. 2922. 0.3818 0.37 1.5 114. 34151. 18246. 3772.3 0.63946 171847. 20.110 194.1 1 

 5688. 250.00 10.71 4.1 861. 1.00000 0.53427 3853.9 0.03180 8545. 0.01370 8.6 28.025

 171732. 4343. 0.3837 0.39 1.6 115. 33128. 17666. 3605.3 0.66687 171732. 19.803 186.0 1 

 7110. 250.00 11.10 5.7 977. 1.00000 0.53328 3688.8 0.03367 8672. 0.01415 11.5 27.465

 171615. 5765. 0.3857 0.40 1.7 117. 32118. 17122. 3441.6 0.69575 171615. 19.525 178.1 1 

 8531. 250.00 11.50 7.4 1094. 1.00000 0.53308 3523.5 0.03563 8790. 0.01460 14.4 26.962

 171496. 7186. 0.3876 0.42 1.7 119. 31120. 16606. 3274.5 0.72618 171496. 19.185 170.6 1 

 9953. 250.00 11.92 9.1 1213. 1.00000 0.53361 3358.0 0.03785 8939. 0.01505 17.3 26.506

 171374. 8608. 0.3896 0.45 1.8 121. 30123. 16089. 3102.4 0.75827 171374. 18.787 163.2 1 

 11374. 250.00 12.37 11.0 1334. 1.00000 0.53411 3188.5 0.04036 9122. 0.01554 20.2 26.047

 171252. 10000. 0.3916 0.46 1.9 122. 29145. 15580. 2929.3 0.79141 171252. 18.354 156.3 1 

 12767. 250.00 12.83 12.9 1456. 1.00000 0.53457 3015.8 0.04312 9331. 0.01605 23.1 25.593

 171103. 10000. 0.5060 0.57 2.7 149. 27729. 16107. 3624.8 0.47370 171103. 19.516 260.9 1 

 14619. 323.00 13.40 15.6 1605. 1.00000 0.58087 0.0 0.02427 8767. 0.02005 26.6 26.792

 170999. 11212. 0.5187 0.39 2.1 104. 26853. 15718. 3527.8 0.47234 170999. 19.477 261.5 1 

 16021. 329.60 13.79 17.7 1709. 1.00000 0.58533 3090.0 0.02425 8779. 0.02097 29.1 26.429

 170895. 12423. 0.5312 0.40 2.2 104. 25987. 15322. 3425.2 0.47190 170895. 19.446 261.6 1 

 17423. 336.07 14.19 19.9 1813. 1.00000 0.58961 3003.8 0.02427 8788. 0.02193 31.6 26.046

 170790. 13635. 0.5438 0.42 2.3 105. 25132. 14920. 3317.1 0.47230 170790. 19.421 261.2 1 

 18826. 342.42 14.61 22.3 1918. 1.00000 0.59368 2912.8 0.02432 8794. 0.02295 34.1 25.644

 170685. 14847. 0.5562 0.43 2.5 105. 24278. 14504. 3202.4 0.47351 170685. 19.402 260.3 1 

 20228. 348.65 15.04 24.7 2024. 1.00000 0.59739 2816.5 0.02441 8797. 0.02404 36.5 25.207

 170578. 16059. 0.5686 0.44 2.6 106. 23705. 14330. 3139.6 0.47549 170578. 19.388 259.1 1 

 21631. 354.78 15.48 27.3 2130. 1.00000 0.60454 2739.8 0.02452 8798. 0.02476 38.9 25.445

 170471. 17270. 0.5810 0.45 2.7 107. 23224. 14223. 3092.2 0.47820 170471. 19.378 257.5 1 

 23033. 360.79 15.93 30.0 2237. 1.00000 0.61243 2692.3 0.02468 8797. 0.02537 41.3 25.877

 170363. 18482. 0.5933 0.46 2.8 108. 22809. 14156. 3055.0 0.48164 170363. 19.373 255.5 1 

 24435. 366.72 16.39 32.8 2345. 1.00000 0.62063 2655.7 0.02486 8794. 0.02591 43.8 26.432

 170227. 20000. 0.6088 0.58 3.6 136. 22385. 14134. 3024.4 0.48694 170227. 19.362 252.5 1 

 26192. 374.00 16.96 36.3 2481. 1.00000 0.63141 2626.4 0.02515 8792. 0.02646 47.0 27.339

 170119. 21112. 0.6243 0.47 2.9 108. 21476. 13663. 2875.4 0.48475 170119. 19.272 253.5 1 

 27567. 381.88 17.43 39.3 2589. 1.00000 0.63618 2384.6 0.02515 8827. 0.02795 49.4 26.515

 170009. 22223. 0.6398 0.49 3.2 110. 20569. 13176. 2716.6 0.48353 170009. 19.182 253.9 1 

 28943. 389.59 17.92 42.4 2699. 1.00000 0.64059 2260.2 0.02521 8863. 0.02957 51.9 25.609

 169897. 23335. 0.6552 0.52 3.4 113. 19674. 12684. 2551.0 0.48322 169897. 19.093 253.9 1 

 30318. 397.16 18.44 45.8 2812. 1.00000 0.64468 2129.1 0.02531 8898. 0.03131 54.3 24.656

 169781. 24446. 0.6705 0.56 3.7 116. 18801. 12192. 2381.3 0.48375 169781. 19.006 253.5 1 

 31693. 404.58 19.00 49.6 2927. 1.00000 0.64847 1993.6 0.02545 8933. 0.03318 56.8 23.680

 169662. 25558. 0.6857 0.60 4.1 119. 17993. 11740. 2219.0 0.48508 169662. 18.920 252.6 1 

 33068. 411.87 19.60 53.6 3047. 1.00000 0.65245 1859.3 0.02564 8967. 0.03508 59.2 22.833

 169538. 26670. 0.7009 0.64 4.4 123. 17249. 11328. 2064.7 0.48718 169538. 18.837 251.3 1 

 34443. 419.04 20.24 58.1 3170. 1.00000 0.65674 1731.4 0.02586 9000. 0.03699 61.6 22.136

 169410. 27781. 0.7160 0.69 4.9 128. 16516. 10917. 1906.8 0.49002 169410. 18.762 249.7 1 

 35818. 426.08 20.93 62.9 3298. 1.00000 0.66098 1605.2 0.02612 9029. 0.03903 64.1 21.433

 169275. 28893. 0.7311 0.75 5.4 134. 15778. 10488. 1741.0 0.49357 169275. 18.691 247.7 1 

 37193. 433.01 21.69 68.3 3433. 1.00000 0.66475 1474.4 0.02641 9057. 0.04129 66.6 20.642

 169133. 30004. 0.7462 0.83 6.0 142. 15035. 10043. 1567.8 0.49781 169133. 18.623 245.4 1 

 38568. 439.83 22.52 74.4 3575. 1.00000 0.66800 1337.4 0.02673 9082. 0.04379 69.1 19.767

 168981. 31116. 0.7613 0.92 6.8 152. 14382. 9689. 1406.8 0.50273 168981. 18.519 242.8 1 

 39944. 446.55 23.44 81.2 3727. 1.00000 0.67368 1202.3 0.02715 9125. 0.04609 71.7 19.255

 168773. 32702. 0.7720 1.33 10.0 208. 13378. 9056. 1160.4 0.52525 168773. 18.592 232.1 1 

 41656. 449.73 24.78 91.2 3935. 1.00000 0.67691 1189.0 0.02825 9078. 0.04966 75.2 18.196

NASA/TM—2013-218094 C–1
 168607. 33909. 0.7762 1.13 8.5 166. 12586. 8526. 966.3 0.54923 168607. 18.717 221.7 1 

 42862. 449.73 25.91 99.7 4102. 1.00000 0.67741 1063.3 0.02934 9008. 0.05275 77.9 17.264

 168434. 35000. 0.7800 1.25 9.4 172. 11868. 8043. 781.7 0.57203 168434. 18.764 212.7 1 

 43954. 449.73 27.16 109.0 4274. 1.00000 0.67770 874.0 0.03049 8977. 0.05592 80.5 16.404

 SEGMENT 2 CRUISE 

 WEIGHT ALTITUDE MACH NO. DELTA T DELTA D DELTA F THRUST FUEL FLOW EX POW CLIFT LIFT L/D Q PCODE 

 ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC DH/DT* CDRAG DRAG SP RANGE NOX ENG PAR

 168434. 35000. 0.7800 0.00 0.0 0. 8977. 5889. 781.7 0.57203 168434. 18.764 212.7 1 

 43954. 449.73 27.16 109.0 4274. 0.75639 0.65601 0.0 0.03049 8977. 0.07637 80.5 12.730

 168000. 35000. 0.7800 4.42 33.2 434. 8958. 5876. 788.8 0.57055 168000. 18.755 212.7 1 

 43954. 449.73 31.59 142.2 4708. 0.75480 0.65598 0.0 0.03042 8958. 0.07654 86.1 12.713

 166400. 35000. 0.7800 16.40 122.9 1600. 8889. 5830. 815.2 0.56512 166400. 18.720 212.7 1 

 43954. 449.73 47.99 265.1 6308. 0.74901 0.65587 0.0 0.03019 8889. 0.07714 106.4 12.650

 164800. 35000. 0.7800 16.53 123.9 1600. 8821. 5785. 841.8 0.55968 164800. 18.682 212.7 1 

 43954. 449.73 64.52 389.0 7908. 0.74332 0.65576 0.0 0.02996 8821. 0.07774 126.5 12.588

 163200. 35000. 0.7800 16.66 124.9 1600. 8755. 5740. 868.6 0.55425 163200. 18.641 212.7 1 

 43954. 449.73 81.18 513.9 9508. 0.73773 0.65565 0.0 0.02973 8755. 0.07835 146.6 12.528

 161600. 35000. 0.7800 16.78 125.8 1600. 8690. 5699. 895.4 0.54882 161600. 18.595 212.7 1 

 43954. 449.73 97.96 639.7 11108. 0.73227 0.65575 0.0 0.02951 8690. 0.07892 166.6 12.472

 160000. 35000. 0.7800 16.90 126.7 1600. 8628. 5661. 922.1 0.54338 160000. 18.544 212.7 1 

 43954. 449.73 114.86 766.4 12708. 0.72704 0.65609 0.0 0.02930 8628. 0.07944 186.6 12.424

 158400. 35000. 0.7800 17.01 127.5 1600. 8567. 5624. 949.0 0.53795 158400. 18.490 212.7 1 

 43954. 449.73 131.88 893.9 14308. 0.72187 0.65643 0.0 0.02909 8567. 0.07997 206.4 12.376

 156800. 35000. 0.7800 17.13 128.4 1600. 8506. 5587. 976.4 0.53252 156800. 18.434 212.7 1 

 43954. 449.73 149.01 1022.3 15908. 0.71675 0.65677 0.0 0.02889 8506. 0.08050 226.2 12.329

 155200. 35000. 0.7800 17.24 129.2 1600. 8446. 5550. 1004.1 0.52708 155200. 18.376 212.7 1 

 43954. 449.73 166.25 1151.5 17508. 0.71168 0.65712 0.0 0.02868 8446. 0.08103 245.8 12.283

 153600. 35000. 0.7800 17.35 130.1 1600. 8386. 5514. 1032.2 0.52165 153600. 18.315 212.7 1 

 43954. 449.73 183.60 1281.6 19108. 0.70667 0.65746 0.0 0.02848 8386. 0.08156 265.5 12.236

 152000. 35000. 0.7800 17.47 130.9 1600. 8328. 5478. 1060.7 0.51621 152000. 18.252 212.7 1 

 43954. 449.73 201.07 1412.5 20708. 0.70171 0.65781 0.0 0.02828 8328. 0.08210 285.0 12.191

 151276. 35000. 0.7800 7.94 59.6 724. 8301. 5462. 1073.7 0.51375 151276. 18.223 212.7 1 

 43954. 449.73 209.01 1472.1 21432. 0.69949 0.65796 0.0 0.02819 8301. 0.08234 293.8 12.170

 SEGMENT 3 CLIMB 

 WEIGHT ALTITUDE MACH NO. DELTA T DELTA D DELTA F THRUST FUEL FLOW EX POW CLIFT LIFT L/D Q PCODE 

 ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC DH/DT* CDRAG DRAG SP RANGE NOX ENG PAR

 151276. 35000. 0.7800 0.00 0.0 0. 11868. 8043. 1073.7 0.51375 151276. 18.223 212.7 1 

 43954. 449.73 209.01 1472.1 21432. 1.00000 0.67770 1114.3 0.02819 8301. 0.05592 293.8 16.404

 151163. 35954. 0.7793 0.86 6.4 112. 11328. 7696. 937.6 0.53820 151163. 18.436 202.9 1 

 44815. 447.38 209.87 1478.5 21545. 1.00000 0.67941 1114.3 0.02919 8199. 0.05813 295.5 16.003

 150925. 37534. 0.7800 1.93 14.4 238. 10444. 7138. 702.6 0.57855 150925. 18.624 188.4 1 

 46395. 447.38 211.80 1492.8 21783. 1.00000 0.68345 820.1 0.03106 8104. 0.06267 298.9 15.369

 150637. 39000. 0.7800 2.52 18.8 288. 9621. 6615. 462.2 0.61943 150637. 18.633 175.6 1 

 47861. 447.38 214.31 1511.6 22071. 1.00000 0.68755 582.4 0.03324 8084. 0.06763 302.9 14.771

 SEGMENT 4 CRUISE 

 WEIGHT ALTITUDE MACH NO. DELTA T DELTA D DELTA F THRUST FUEL FLOW EX POW CLIFT LIFT L/D Q PCODE 

 ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC DH/DT* CDRAG DRAG SP RANGE NOX ENG PAR

 150637. 39000. 0.7800 0.00 0.0 0. 8084. 5410. 462.2 0.61943 150637. 18.633 175.6 1 

 47861. 447.38 214.31 1511.6 22071. 0.84026 0.66921 0.0 0.03324 8084. 0.08270 302.9 12.406

 150400. 39000. 0.7800 2.62 19.6 237. 8071. 5401. 466.8 0.61846 150400. 18.634 175.6 1 

 47861. 447.38 216.94 1531.2 22308. 0.83893 0.66920 0.0 0.03319 8071. 0.08283 305.8 12.394

 148800. 39000. 0.7800 17.87 133.2 1600. 7986. 5344. 497.7 0.61188 148800. 18.631 175.6 1 

 47861. 447.38 234.81 1664.4 23908. 0.83010 0.66915 0.0 0.03284 7986. 0.08371 325.6 12.309

 147200. 39000. 0.7800 18.06 134.6 1600. 7904. 5289. 528.5 0.60530 147200. 18.624 175.6 1 

 47861. 447.38 252.86 1799.1 25508. 0.82152 0.66911 0.0 0.03250 7904. 0.08459 345.2 12.228

 145600. 39000. 0.7800 18.24 136.0 1600. 7825. 5235. 559.0 0.59872 145600. 18.608 175.6 1 

 47861. 447.38 271.11 1935.1 27108. 0.81327 0.66906 0.0 0.03218 7825. 0.08546 364.7 12.149

 144000. 39000. 0.7800 18.43 137.4 1600. 7750. 5185. 588.7 0.59214 144000. 18.581 175.6 1 

 47861. 447.38 289.53 2072.5 28708. 0.80551 0.66902 0.0 0.03187 7750. 0.08629 384.1 12.075

 142400. 39000. 0.7800 18.60 138.7 1600. 7677. 5136. 618.6 0.58556 142400. 18.550 175.6 1 

 47861. 447.38 308.14 2211.2 30308. 0.79790 0.66897 0.0 0.03157 7677. 0.08712 403.4 12.002

 140800. 39000. 0.7800 18.78 140.0 1600. 7605. 5087. 648.8 0.57898 140800. 18.514 175.6 1 

 47861. 447.38 326.92 2351.3 31908. 0.79044 0.66893 0.0 0.03127 7605. 0.08794 422.5 11.931

 139200. 39000. 0.7800 18.96 141.4 1600. 7535. 5040. 679.1 0.57240 139200. 18.475 175.6 1 

 47861. 447.38 345.88 2492.6 33508. 0.78312 0.66888 0.0 0.03098 7535. 0.08877 441.5 11.861

NASA/TM—2013-218094 C–2
 137600. 39000. 0.7800 19.14 142.7 1600. 7466. 4993. 709.7 0.56582 137600. 18.431 175.6 1 

 47861. 447.38 365.02 2635.3 35108. 0.77595 0.66884 0.0 0.03070 7466. 0.08960 460.5 11.793

 136000. 39000. 0.7800 19.31 144.0 1600. 7398. 4948. 740.6 0.55924 136000. 18.383 175.6 1 

 47861. 447.38 384.33 2779.3 36708. 0.76893 0.66880 0.0 0.03042 7398. 0.09042 479.3 11.726

 135762. 39000. 0.7800 2.89 21.6 238. 7388. 4941. 745.2 0.55826 135762. 18.376 175.6 1 

 47861. 447.38 387.22 2800.9 36946. 0.76790 0.66879 0.0 0.03038 7388. 0.09054 482.1 11.716

 SEGMENT 5 DESCENT 

 WEIGHT ALTITUDE MACH NO. DELTA T DELTA D DELTA F THRUST FUEL FLOW EX POW CLIFT LIFT L/D Q PCODE 

 ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC DH/DT* CDRAG DRAG SP RANGE NOX ENG PAR

 135762. 39000. 0.7800 0.00 0.0 0. -427. 619. -2608.1 0.55826 135762. 18.376 175.6 0 

 47861. 447.38 387.22 2800.9 36946. -0.04441 0.00000 0.0 0.03038 7388. 0.72280 482.1 2.182

 135760. 39000. 0.7587 0.19 1.4 2. -398. 613. -2476.9 0.59008 135760. 18.770 166.2 0 

 47383. 435.15 387.41 2802.3 36948. -0.04176 0.00000 0.0 0.03144 7233. 0.71018 482.1 1.969

 135755. 38334. 0.7296 0.54 3.8 6. -374. 618. -2348.1 0.61801 135755. 18.991 158.6 0 

 46087. 418.48 387.95 2806.1 36954. -0.03825 0.00000 -1239.1 0.03254 7148. 0.67666 482.1 1.740

 135749. 37357. 0.7144 0.56 3.9 6. -377. 629. -2287.6 0.61504 135749. 19.103 159.4 0 

 44791. 409.78 388.51 2810.0 36960. -0.03682 0.00000 -1747.3 0.03220 7106. 0.65175 482.1 1.670

 135743. 36365. 0.6997 0.57 3.9 6. -379. 638. -2229.2 0.61145 135743. 19.209 160.3 0 

 43495. 401.32 389.08 2813.8 36966. -0.03538 0.00000 -1729.2 0.03183 7066. 0.62901 482.1 1.600

 135736. 35310. 0.6852 0.59 3.9 6. -387. 652. -2182.0 0.60629 135736. 19.317 161.7 0 

 42199. 394.49 389.67 2817.7 36972. -0.03444 0.00000 -1796.1 0.03139 7027. 0.60544 482.1 1.546

 135730. 34281. 0.6687 0.60 3.9 7. -380. 672. -2127.7 0.60627 135730. 19.409 161.7 0 

 40903. 386.78 390.27 2821.6 36979. -0.03217 0.00000 -1711.6 0.03124 6993. 0.57600 482.1 1.575

 135723. 33222. 0.6535 0.62 3.9 7. -373. 694. -2078.8 0.60405 135723. 19.491 162.3 0 

 39608. 379.78 390.89 2825.6 36986. -0.02993 0.00000 -1717.4 0.03099 6963. 0.54718 482.1 1.665

 135715. 32176. 0.6376 0.63 4.0 7. -352. 715. -2024.8 0.60430 135715. 19.564 162.2 0 

 38312. 372.29 391.52 2829.5 36993. -0.02689 0.00000 -1657.0 0.03089 6937. 0.52080 482.1 1.746

 135707. 31106. 0.6228 0.65 4.0 8. -333. 735. -1975.5 0.60286 135707. 19.631 162.6 0 

 37016. 365.37 392.17 2833.5 37001. -0.02420 0.00000 -1651.2 0.03071 6913. 0.49741 482.2 1.839

 135699. 30029. 0.6084 0.66 4.0 8. -316. 753. -1928.6 0.60159 135699. 19.691 162.9 0 

 35720. 358.54 392.83 2837.5 37009. -0.02194 0.00000 -1622.4 0.03055 6891. 0.47586 482.2 1.932

 135691. 28950. 0.5939 0.68 4.0 9. -301. 776. -1883.2 0.60114 135691. 19.739 163.0 0 

 34424. 351.65 393.51 2841.5 37018. -0.01988 0.00000 -1587.3 0.03045 6874. 0.45324 482.2 2.064

 135681. 27859. 0.5800 0.70 4.0 9. -277. 799. -1837.7 0.60029 135681. 19.779 163.2 0 

 33128. 345.00 394.21 2845.6 37027. -0.01740 0.00000 -1566.0 0.03035 6860. 0.43168 482.2 2.204

 135672. 26764. 0.5662 0.71 4.1 10. -249. 824. -1792.0 0.60001 135672. 19.815 163.3 0 

 31832. 338.35 394.92 2849.6 37037. -0.01489 0.00000 -1533.1 0.03028 6847. 0.41052 482.2 2.343

 135662. 25666. 0.5524 0.73 4.1 10. -216. 851. -1745.9 0.60045 135662. 19.846 163.2 0 

 30536. 331.67 395.65 2853.7 37047. -0.01236 0.00000 -1498.5 0.03026 6836. 0.38982 482.3 2.480

 135651. 24561. 0.5390 0.75 4.1 11. -203. 874. -1705.9 0.60099 135651. 19.874 163.0 0 

 29240. 325.11 396.40 2857.8 37058. -0.01110 0.00000 -1471.8 0.03024 6825. 0.37209 482.3 2.630 

 135639. 23440. 0.5265 0.77 4.1 11. -200. 897. -1670.8 0.60020 135639. 19.902 163.2 0 

 27944. 318.99 397.17 2861.9 37069. -0.01038 0.00000 -1461.2 0.03016 6815. 0.35566 482.3 2.796

 135628. 22315. 0.5140 0.78 4.1 12. -191. 921. -1634.7 0.60001 135628. 19.926 163.3 0 

 26649. 312.87 397.96 2866.1 37081. -0.00942 0.00000 -1434.5 0.03011 6807. 0.33969 482.3 2.963

 135615. 21184. 0.5018 0.80 4.1 12. -176. 946. -1598.0 0.60000 135615. 19.948 163.2 0 

 25353. 306.85 398.76 2870.2 37093. -0.00828 0.00000 -1410.1 0.03008 6799. 0.32426 482.4 3.132

 135602. 20047. 0.4900 0.82 4.2 13. -157. 976. -1561.8 0.60000 135602. 19.963 163.2 0 

 24057. 300.95 399.58 2874.3 37106. -0.00705 0.00000 -1386.6 0.03006 6793. 0.30836 482.4 3.307

 135588. 18903. 0.4784 0.84 4.2 14. -130. 1011. -1525.1 0.60000 135588. 19.978 163.2 0 

 22761. 295.19 400.42 2878.5 37120. -0.00570 0.00000 -1362.3 0.03003 6787. 0.29191 482.5 3.435

 135573. 17753. 0.4672 0.86 4.2 15. -103. 1047. -1489.1 0.60000 135573. 19.991 163.2 0 

 21465. 289.56 401.28 2882.7 37135. -0.00439 0.00000 -1337.5 0.03001 6782. 0.27649 482.5 3.568

 135558. 16597. 0.4562 0.88 4.2 16. -76. 1084. -1454.1 0.60000 135558. 20.005 163.2 0 

 20169. 284.05 402.16 2886.9 37151. -0.00314 0.00000 -1312.8 0.02999 6776. 0.26208 482.6 3.706

 135541. 15435. 0.4456 0.90 4.2 17. -47. 1122. -1419.5 0.60000 135541. 20.018 163.2 0 

 18873. 278.67 403.06 2891.1 37167. -0.00187 0.00000 -1288.1 0.02997 6771. 0.24826 482.6 3.852

 135523. 14268. 0.4352 0.92 4.2 18. -14. 1171. -1385.1 0.60000 135523. 20.031 163.1 0 

 17577. 273.41 403.98 2895.4 37185. -0.00055 0.00000 -1263.2 0.02995 6766. 0.23354 482.7 4.009

 135504. 13095. 0.4251 0.95 4.3 19. 26. 1223. -1350.1 0.60000 135504. 20.044 163.1 0 

 16281. 268.27 404.93 2899.7 37204. 0.00099 0.00000 -1237.5 0.02993 6760. 0.21930 482.8 4.167

 135484. 11918. 0.4153 0.97 4.3 20. 75. 1276. -1314.3 0.60000 135484. 20.057 163.1 0 

 14985. 263.24 405.90 2904.0 37224. 0.00274 16.91116 -1210.7 0.02992 6755. 0.20627 482.9 4.326

NASA/TM—2013-218094 C–3
 135463. 10735. 0.4058 1.00 4.3 22. 133. 1329. -1277.9 0.60000 135463. 20.070 163.1 0 

 13690. 258.33 406.90 2908.3 37246. 0.00466 10.02060 -1182.7 0.02990 6750. 0.19432 483.0 4.484

 135392. 7357. 0.3801 2.99 12.5 70. 276. 1499. -1182.9 0.60000 135392. 20.118 163.0 0 

 10015. 245.02 409.89 2920.8 37316. 0.00885 5.43932 -1131.0 0.02982 6730. 0.16346 483.3 4.893

 135307. 3978. 0.3566 3.20 12.7 85. 440. 1689. -1092.1 0.60000 135307. 20.162 162.9 0 

 6375. 232.67 413.09 2933.5 37401. 0.01298 3.84134 -1055.8 0.02976 6711. 0.13776 483.7 5.297

 135167. 0. 0.3000 4.59 16.5 140. 874. 1980. -927.9 0.73223 135167. 18.998 133.3 0 

 1743. 198.44 417.68 2950.0 37541. 0.02286 2.26642 -867.5 0.03854 7115. 0.10020 484.5 5.551

NASA/TM—2013-218094 C–4
Appendix D: Overall Performance Characteristic Maps; pressure ratio, efficiency vs. flow 

and RPM. (with baseline aerodynamic blockages) 

Flow Rate, Corr., lbm/sec, Pressure Ratio, Efficiency, Rotor 1 Incidence, Temp. Ratio 

ZONE T=" 110% of Design Corrected Speed = 4137 RPM", I = 17.0 

206.3230 2.2794 0.8126 2.5142 1.3279 

203.8517 2.3806 0.8341 2.9529 1.3385 

202.2476 2.4331 0.8434 3.2376 1.3443 

201.0352 2.4669 0.8485 3.4529 1.3483 

198.2180 2.5330 0.8567 3.9532 1.3564 

195.2791 2.5876 0.8613 4.4756 1.3638 

192.3645 2.6299 0.8629 4.9942 1.3703 

189.4935 2.6638 0.8626 5.5058 1.3760 

186.6652 2.6912 0.8611 6.0106 1.3812 

183.8792 2.7134 0.8586 6.5087 1.3860 

181.1348 2.7315 0.8554 7.0004 1.3904 

178.4314 2.7462 0.8518 7.4857 1.3944 

175.7682 2.7581 0.8477 7.9649 1.3983 

173.0626 2.7674 0.8431 8.4529 1.4020 

170.2964 2.7741 0.8380 8.9531 1.4056 

167.1750 2.7796 0.8319 9.5192 1.4095 

164.6798 2.7825 0.8268 9.9730 1.4125 

ZONE T=" 105% of Design Corrected Speed = 3949.3 RPM", I = 14.0 

199.2340 2.0035 0.7782 2.4621 1.2833 

196.2604 2.1310 0.8172 2.9953 1.2964 

193.3312 2.2235 0.8397 3.5215 1.3066 

190.4457 2.2930 0.8528 4.0409 1.3150 

188.1599 2.3383 0.8596 4.4532 1.3208 

185.3932 2.3829 0.8642 4.9534 1.3271 

182.6354 2.4198 0.8665 5.4534 1.3328 

179.8873 2.4504 0.8669 5.9529 1.3380 

174.0149 2.4999 0.8635 7.0256 1.3479 

168.8593 2.5293 0.8572 7.9735 1.3556 

163.5658 2.5485 0.8481 8.9533 1.3628 

158.2028 2.5605 0.8375 9.9531 1.3694 

152.7519 2.5667 0.8258 10.9770 1.3758 

147.4851 2.5682 0.8138 11.9740 1.3816 

ZONE T=" 100% of Design Corrected Speed = 3761.1 RPM", I = 20.0 

190.2553 1.8420 0.7636 2.7031 1.2507 

188.5460 1.9109 0.7916 3.0144 1.2577 

185.7319 1.9995 0.8216 3.5283 1.2675 

184.7755 2.0253 0.8293 3.7034 1.2704 

182.9599 2.0686 0.8408 4.0364 1.2756 

180.2291 2.1238 0.8533 4.5386 1.2825 

177.5392 2.1686 0.8612 5.0352 1.2886 

174.8894 2.2059 0.8660 5.5263 1.2940 

172.2791 2.2371 0.8686 6.0120 1.2990 

169.7079 2.2633 0.8695 6.4923 1.3035 

167.1750 2.2853 0.8691 6.9673 1.3077 

164.5934 2.3037 0.8673 7.4534 1.3117 

161.9505 2.3192 0.8645 7.9532 1.3156 

159.0018 2.3336 0.8604 8.5135 1.3196 

156.6287 2.3430 0.8566 8.9664 1.3228 

151.2282 2.3589 0.8465 10.0040 1.3296 

NASA/TM—2013-218094 D–1
146.0140 2.3680 0.8352 11.0152 1.3357 

140.9795 2.3722 0.8234 12.0004 1.3413 

136.1186 2.3728 0.8114 12.9602 1.3465 

133.4166 2.3719 0.8046 13.4974 1.3492 

ZONE T=" 95% of Design Corrected Speed = 3572.9 RPM", I = 17.0 

181.0216 1.7094 0.7505 2.9530 1.2214 

179.3280 1.7675 0.7798 3.2685 1.2275 

178.3378 1.7961 0.7924 3.4534 1.2307 

175.6672 1.8635 0.8190 3.9536 1.2386 

173.0107 1.9184 0.8372 4.4535 1.2453 

170.3689 1.9648 0.8501 4.9531 1.2514 

167.7381 2.0045 0.8591 5.4531 1.2568 

164.6798 2.0437 0.8660 6.0376 1.2626 

159.8008 2.0923 0.8702 6.9773 1.2709 

154.7835 2.1290 0.8688 7.9532 1.2785 

149.6973 2.1560 0.8632 8.9529 1.2855 

144.5575 2.1749 0.8547 9.9739 1.2920 

139.5732 2.1869 0.8445 10.9747 1.2978 

134.7507 2.1938 0.8333 11.9530 1.3032 

129.4638 2.1971 0.8199 13.0371 1.3088 

125.0000 2.1971 0.8079 13.9618 1.3134 

120.0866 2.1944 0.7943 14.9898 1.3182 

ZONE T=" 90% of Design Corrected Speed = 3384.6 RPM", I = 16.0 

171.4177 1.6064 0.7440 3.2406 1.1957 

170.3092 1.6381 0.7634 3.4530 1.1991 

167.7087 1.6988 0.7951 3.9535 1.2064 

164.6798 1.7572 0.8209 4.5402 1.2137 

162.2220 1.7986 0.8367 5.0193 1.2191 

157.4157 1.8653 0.8569 5.9641 1.2284 

151.9881 1.9221 0.8676 7.0442 1.2375 

147.4741 1.9579 0.8697 7.9534 1.2443 

142.3999 1.9881 0.8670 8.9875 1.2512 

137.4901 2.0092 0.8606 10.0004 1.2574 

132.7495 2.0234 0.8517 10.9901 1.2629 

128.1724 2.0324 0.8414 11.9567 1.2680 

123.1343 2.0380 0.8286 13.0332 1.2733 

118.8768 2.0399 0.8169 13.9533 1.2776 

114.2156 2.0394 0.8034 14.9715 1.2822 

109.7261 2.0366 0.7899 15.9629 1.2864 

ZONE T=" 85% of Design Corrected Speed = 3197.3 RPM", I = 17.0 

162.1044 1.5115 0.7336 3.4535 1.1714 

159.5892 1.5634 0.7688 3.9533 1.1778 

156.6287 1.6157 0.7990 4.5460 1.1846 

154.2909 1.6521 0.8174 5.0175 1.1894 

151.9881 1.6845 0.8320 5.4850 1.1938 

149.6973 1.7136 0.8436 5.9530 1.1980 

144.5575 1.7687 0.8605 7.0142 1.2064 

140.0713 1.8063 0.8673 7.9532 1.2130 

135.3568 1.8370 0.8683 8.9530 1.2194 

130.7028 1.8597 0.8646 9.9532 1.2252 

126.1111 1.8761 0.8577 10.9531 1.2305 

121.2965 1.8880 0.8476 12.0155 1.2358 

117.0996 1.8946 0.8372 12.9533 1.2402 

112.5109 1.8986 0.8244 13.9913 1.2448 

108.0884 1.8997 0.8111 15.0041 1.2491 

NASA/TM—2013-218094 D–2
103.8398 1.8987 0.7977 15.9884 1.2530 

99.7208 1.8958 0.7841 16.9533 1.2567 

ZONE T=" 80% of Design Corrected Speed = 3009.1 RPM", I = 19.0 

153.5195 1.4133 0.7086 3.4810 1.1472 

151.2282 1.4527 0.7418 3.9538 1.1524 

148.8259 1.4898 0.7693 4.4533 1.1574 

146.0140 1.5299 0.7961 5.0429 1.1629 

143.8347 1.5585 0.8132 5.5035 1.1668 

141.6879 1.5845 0.8273 5.9606 1.1705 

136.8026 1.6357 0.8501 7.0126 1.1783 

132.0858 1.6754 0.8622 8.0445 1.1850 

127.9930 1.7029 0.8665 8.9529 1.1903 

123.1343 1.7283 0.8656 10.0471 1.1962 

118.8887 1.7448 0.8608 11.0174 1.2010 

114.7895 1.7566 0.8534 11.9669 1.2054 

110.2775 1.7656 0.8428 13.0264 1.2101 

106.3821 1.7704 0.8320 13.9532 1.2139 

102.2312 1.7731 0.8194 14.9531 1.2178 

97.7779 1.7735 0.8047 16.0399 1.2219 

93.9346 1.7721 0.7913 16.9895 1.2253 

89.7911 1.7686 0.7762 18.0251 1.2288 

88.0087 1.7665 0.7695 18.4744 1.2303 

ZONE T=" 70% of Design Corrected Speed = 2632.6 RPM", I = 20.0 

136.1186 1.2669 0.6602 3.4667 1.1063 

133.9698 1.2921 0.6919 3.9529 1.1102 

131.4253 1.3211 0.7258 4.5345 1.1145 

129.4638 1.3427 0.7491 4.9872 1.1177 

127.4614 1.3639 0.7704 5.4532 1.1208 

125.0000 1.3885 0.7930 6.0315 1.1244 

121.1299 1.4237 0.8213 6.9532 1.1298 

117.0002 1.4564 0.8425 7.9535 1.1351 

112.9435 1.4834 0.8554 8.9532 1.1400 

108.6316 1.5069 0.8618 10.0345 1.1448 

104.8861 1.5232 0.8623 10.9895 1.1487 

101.1634 1.5360 0.8589 11.9532 1.1525 

97.2890 1.5460 0.8520 12.9716 1.1562 

93.4649 1.5531 0.8425 13.9922 1.1597 

89.7911 1.5576 0.8314 14.9870 1.1630 

86.2617 1.5601 0.8192 15.9559 1.1660 

82.4566 1.5608 0.8048 17.0148 1.1692 

78.8194 1.5599 0.7899 18.0407 1.1721 

75.3427 1.5575 0.7747 19.0337 1.1749 

72.0193 1.5536 0.7591 19.9940 1.1774 

ZONE T=" 60% of Design Corrected Speed = 2257. RPM", I = 22.0 

117.7028 1.1757 0.6291 3.5438 1.0755 

115.9461 1.1902 0.6569 3.9922 1.0779 

114.1585 1.2048 0.6834 4.4529 1.0803 

111.9483 1.2226 0.7137 5.0288 1.0831 

110.2775 1.2358 0.7347 5.4688 1.0852 

108.4552 1.2497 0.7556 5.9532 1.0874 

104.7498 1.2766 0.7917 6.9532 1.0916 

101.1179 1.3006 0.8189 7.9529 1.0956 

97.2890 1.3228 0.8393 9.0280 1.0995 

93.9346 1.3396 0.8507 9.9879 1.1028 

90.6187 1.3536 0.8567 10.9534 1.1059 

NASA/TM—2013-218094 D–3
87.1308 1.3658 0.8579 11.9868 1.1090 

83.7060 1.3754 0.8548 13.0194 1.1120 

80.4157 1.3824 0.8483 14.0280 1.1147 

77.2548 1.3873 0.8395 15.0123 1.1172 

74.2182 1.3906 0.8290 15.9719 1.1196 

70.9444 1.3926 0.8157 17.0217 1.1221 

67.8150 1.3931 0.8016 18.0398 1.1244 

64.8237 1.3924 0.7867 19.0262 1.1266 

61.9643 1.3906 0.7714 19.9809 1.1286 

58.9348 1.3874 0.7536 21.0048 1.1306 

57.4761 1.3852 0.7444 21.5023 1.1316 

ZONE T=" 50% of Design Corrected Speed = 1880.5 RPM", I = 24.0 

99.2594 1.1100 0.5986 3.4637 1.0508 

97.6119 1.1195 0.6276 3.9534 1.0524 

95.8370 1.1298 0.6572 4.4873 1.0542 

94.3052 1.1386 0.6813 4.9535 1.0557 

92.5326 1.1488 0.7073 5.4992 1.0574 

91.0741 1.1570 0.7272 5.9534 1.0587 

89.3421 1.1666 0.7490 6.4986 1.0603 

87.9141 1.1743 0.7654 6.9531 1.0616 

84.5493 1.1914 0.7983 8.0419 1.0645 

81.6341 1.2051 0.8204 9.0055 1.0670 

78.8194 1.2169 0.8362 9.9539 1.0692 

75.7213 1.2284 0.8475 11.0185 1.0717 

73.0520 1.2368 0.8525 11.9530 1.0737 

70.2367 1.2443 0.8535 12.9562 1.0758 

67.4759 1.2503 0.8506 13.9573 1.0778 

64.7751 1.2549 0.8444 14.9533 1.0797 

61.9643 1.2584 0.8351 16.0072 1.0816 

59.4811 1.2605 0.8246 16.9529 1.0832 

56.8929 1.2617 0.8119 17.9529 1.0849 

54.1208 1.2620 0.7962 19.0400 1.0867 

51.7336 1.2614 0.7813 19.9894 1.0881 

49.2043 1.2598 0.7637 21.0082 1.0896 

46.7987 1.2572 0.7451 21.9893 1.0910 

45.1851 1.2548 0.7314 22.6539 1.0920 

ZONE T=" 40% of Design Corrected Speed = 1504. RPM", I = 25.0 

80.0137 1.0661 0.5805 3.4576 1.0319 

78.4253 1.0725 0.6130 4.0348 1.0331 

77.2548 1.0772 0.6359 4.4657 1.0339 

75.7213 1.0835 0.6644 5.0372 1.0350 

74.5911 1.0880 0.6842 5.4636 1.0358 

73.1105 1.0940 0.7088 6.0289 1.0368 

72.0121 1.0984 0.7258 6.4532 1.0376 

70.5897 1.1040 0.7463 7.0089 1.0385 

68.1558 1.1132 0.7772 7.9764 1.0402 

65.7516 1.1218 0.8024 8.9529 1.0417 

63.2192 1.1301 0.8230 10.0038 1.0434 

60.9785 1.1367 0.8362 10.9531 1.0447 

58.6402 1.1428 0.8452 11.9632 1.0462 

56.3352 1.1481 0.8493 12.9783 1.0476 

54.1208 1.1523 0.8493 13.9717 1.0488 

51.9714 1.1556 0.8457 14.9530 1.0501 

49.7001 1.1584 0.8386 16.0081 1.0513 

47.5078 1.1603 0.8288 17.0439 1.0526 

NASA/TM—2013-218094 D–4
45.6130 1.1614 0.8183 17.9529 1.0536 

43.4090 1.1620 0.8038 19.0260 1.0547 

41.4943 1.1620 0.7894 19.9719 1.0557 

39.4656 1.1614 0.7723 20.9874 1.0567 

37.5361 1.1601 0.7540 21.9660 1.0577 

35.5225 1.1580 0.7323 23.0000 1.0587 

33.6169 1.1550 0.7085 23.9903 1.0595 

NASA/TM—2013-218094 D–5

Appendix E: Fan-Core and LPC Performance along Engine Operating Line

Flow Rate (corrected, lbm/sec), Pressure Ratio, Efficiency, Rotor 1 Incidence 

(degrees), Temperature Ratio 

ZONE T="Vehicle Mach No. = .78, Altitude 35K ft, Thrust 100%", I=1.0 

203.6437 2.4061 0.8368 3.0010 1.3415 

ZONE T="Vehicle Mach No. = .78, Altitude 35K ft, Thrust 75.6%", I=1.0 

179.2984 2.3173 0.8664 5.4177 1.3140 

ZONE T="Vehicle Mach No. = .78, Altitude 35K ft, Thrust 72.9%", I=1.0 

176.0543 2.3024 0.8678 5.7753 1.3108 

ZONE T="Vehicle Mach No. = .78, Altitude 35K ft, Thrust 69.9%", I=1.0 

172.8357 2.2860 0.8688 6.1325 1.3074 

ZONE T="Vehicle Mach No. = .78, Altitude 39K ft, Thrust 100%", I=1.0 

203.7504 2.4040 0.8363 2.9818 1.3413 

ZONE T="Vehicle Mach No. = .78, Altitude 39K ft, Thrust 84%", I=1.0 

188.1720 2.3524 0.8599 4.4621 1.3226 

ZONE T="Vehicle Mach No. = .78, Altitude 39K ft, Thrust 79.8%", I=1.0 

183.8159 2.3356 0.8636 4.9209 1.3182 

ZONE T="Vehicle Mach No. = .78, Altitude 39K ft, Thrust 76.8%", I=1.0 

180.6934 2.3221 0.8656 5.2552 1.3151 

ZONE T="Vehicle Mach No. = .78, Altitude 39K ft, Thrust 10%", I=1.0 

79.2363 1.5569 0.7933 17.8248 1.1703 

ZONE T="Vehicle Mach No. = .73, Altitude 38K ft, Thrust 10%", I=1.0 

77.8263 1.5335 0.7949 17.8275 1.1638 

ZONE T="Vehicle Mach No. = .71, Altitude 37K ft, Thrust 10%", I=1.0 

77.3570 1.5253 0.7956 17.8175 1.1615 

ZONE T="Vehicle Mach No. = .67, Altitude 34K ft, Thrust 10%", I=1.0 

75.9212 1.4999 0.7980 17.7720 1.1542 

ZONE T="Vehicle Mach No. = .61, Altitude 30K ft, Thrust 10%", I=1.0 

73.9994 1.4614 0.8034 17.5884 1.1428 

ZONE T="Vehicle Mach No. = .55, Altitude 25K ft, Thrust 10%", I=1.0 

72.1560 1.4237 0.8094 17.3431 1.1315 

ZONE T="Vehicle Mach No. = .49, Altitude 20K ft, Thrust 10%", I=1.0 

70.0257 1.3849 0.8153 17.0975 1.1199 

ZONE T="Vehicle Mach No. = .45, Altitude 15K ft, Thrust 10%", I=1.0 

66.8582 1.3505 0.8157 17.2314 1.1102 

ZONE T="Vehicle Mach No. = .41, Altitude 10K ft, Thrust 10%", I=1.0 

63.5491 1.3112 0.8186 17.2075 1.0986 

ZONE T="Vehicle Mach No. = .20, Altitude 0K ft, Thrust 100%", I=1.0 

178.3165 2.2709 0.8662 5.3730 1.3059 

NASA/TM—2013-218094 E–1

Appendix F: Ice Particle Temperature and Static Air Temperature from Inlet through 

LPC

TITLE = "Temperature vs Particle Distance Traveled" 

VARIABLES = "x", "Particle Temperature" 

ZONE T=" Ice Particle Temperature", I = 2925.0 

 0.07984 416.6630 

 0.15968 416.4184 

 0.23952 416.2143 

 0.31936 416.0493 

 0.39920 415.9172 

 0.47904 415.8141 

 0.55888 415.7361 

 0.63872 415.6801 

 0.71856 415.6431 

 0.79840 415.6228 

 0.87824 415.6169 

 0.95808 415.6236 

 1.03792 415.6412 

 1.11776 415.6684 

 1.19761 415.7038 

 1.27744 415.7465 

 1.35729 415.7955 

 1.43713 415.8499 

 1.51697 415.9089 

 1.59681 415.9721 

 1.67665 416.0389 

 1.75649 416.1088 

 1.83633 416.1813 

 1.91617 416.2561 

 1.99601 416.3330 

 2.07585 416.4116 

 2.15569 416.4916 

 2.23553 416.5730 

 2.31537 416.6555 

 2.39521 416.7389 

 2.47505 416.8231 

 2.55489 416.9081 

 2.63473 416.9936 

 2.71457 417.0796 

 2.79441 417.1661 

 2.87425 417.2529 

 2.95409 417.3401 

 3.03393 417.4275 

 3.11377 417.5151 

 3.19361 417.6029 

 3.27345 417.6909 

 3.35329 417.7789 

 3.43313 417.8670 

 3.51297 417.9553 

 3.59281 418.0435 

 3.67266 418.1318 

 3.75250 418.2202 

 3.83233 418.3085 

 3.91218 418.3969 

 3.99202 418.4852 

 4.07186 418.5735 

 4.15170 418.6618 

 4.23154 418.7501 

 4.31138 418.8384 

 4.39122 418.9266 

 4.47106 419.0148 

NASA/TM—2013-218094 F–1
 4.55090 419.1029 

 4.63074 419.1910 

 4.71058 419.2791 

 4.79042 419.3671 

 4.87026 419.4551 

 4.95010 419.5431 

 5.02994 419.6310 

 5.10978 419.7188 

 5.18962 419.8066 

 5.26946 419.8943 

 5.34930 419.9820 

 5.42914 420.0696 

 5.50898 420.1571 

 5.58882 420.2447 

 5.66866 420.3321 

 5.74850 420.4196 

 5.82834 420.5069 

 5.90818 420.5942 

 5.98802 420.6815 

 6.06786 420.7687 

 6.14771 420.8558 

 6.22754 420.9429 

 6.30738 421.0300 

 6.38723 421.1170 

 6.46707 421.2039 

 6.54691 421.2908 

 6.62675 421.3777 

 6.70659 421.4644 

 6.78643 421.5512 

 6.86627 421.6379 

 6.94611 421.7246 

 7.02595 421.8112 

 7.10579 421.8978 

 7.18563 421.9843 

 7.26547 422.0707 

 7.34531 422.1572 

 7.42515 422.2436 

 7.50499 422.3299 

 7.58483 422.4162 

 7.66467 422.5024 

 7.74451 422.5886 

 7.82435 422.6747 

 7.90419 422.7608 

 7.98403 422.8469 

 8.06387 422.9329 

 8.14371 423.0189 

 8.22355 423.1048 

 8.30339 423.1907 

 8.38323 423.2766 

 8.46307 423.3623 

 8.54291 423.4481 

 8.62275 423.5338 

 8.70259 423.6195 

 8.78243 423.7051 

 8.86228 423.7907 

 8.94212 423.8763 

 9.02195 423.9618 

 9.10180 424.0472 

 9.18164 424.1327 

 9.26148 424.2181 

 9.34132 424.3034 

 9.42116 424.3887 

 9.50100 424.4740 

NASA/TM—2013-218094 F–2
 9.58084 424.5593 

 9.66068 424.6444 

 9.74052 424.7296 

 9.82036 424.8147 

 9.90020 424.8998 

 9.98004 424.9849 

 10.05988 425.0699 

 10.13972 425.1548 

 10.21956 425.2398 

 10.29940 425.3247 

 10.37924 425.4096 

 10.45909 425.4944 

 10.53893 425.5792 

 10.61877 425.6639 

 10.69861 425.7487 

 10.77845 425.8334 

 10.85829 425.9180 

 10.93813 426.0027 

 11.01797 426.0872 

 11.09781 426.1718 

 11.17765 426.2563 

 11.25749 426.3408 

 11.33734 426.4252 

 11.41718 426.5096 

 11.49702 426.5940 

 11.57686 426.6784 

 11.65670 426.7627 

 11.73654 426.8470 

 11.81638 426.9312 

 11.89622 427.0154 

 11.97606 427.0996 

 12.05590 427.1838 

 12.13575 427.2679 

 12.21559 427.3520 

 12.29543 427.4361 

 12.37527 427.5201 

 12.45511 427.6041 

 12.53495 427.6881 

 12.61479 427.7721 

 12.69463 427.8560 

 12.77447 427.9398 

 12.85431 428.0237 

 12.93415 428.1076 

 13.01400 428.1913 

 13.09384 428.2751 

 13.17368 428.3589 

 13.25352 428.4427 

 13.33336 428.5263 

 13.41320 428.6100 

 13.49304 428.6937 

 13.57288 428.7773 

 13.65272 428.8609 

 13.73256 428.9445 

 13.81240 429.0280 

 13.89224 429.1115 

 13.97209 429.1950 

 14.05193 429.2784 

 14.13177 429.3619 

 14.21161 429.4453 

 14.29145 429.5287 

 14.37129 429.6120 

 14.45113 429.6954 

 14.53097 429.7787 

NASA/TM—2013-218094 F–3
 14.61081 429.8619 

 14.69065 429.9452 

 14.77049 430.0284 

 14.85034 430.1116 

 14.93018 430.1948 

 15.01002 430.2779 

 15.08986 430.3611 

 15.16970 430.4442 

 15.24954 430.5273 

 15.32938 430.6103 

 15.40922 430.6933 

 15.48906 430.7764 

 15.56890 430.8594 

 15.64874 430.9423 

 15.72859 431.0253 

 15.80843 431.1082 

 15.88827 431.1911 

 15.96811 431.2740 

 16.04795 431.3569 

 16.12779 431.4397 

 16.20763 431.5225 

 16.28747 431.6053 

 16.36731 431.6881 

 16.44715 431.7709 

 16.52699 431.8536 

 16.60683 431.9363 

 16.68668 432.0190 

 16.76652 432.1017 

 16.84636 432.1844 

 16.92620 432.2670 

 17.00604 432.3497 

 17.08588 432.4323 

 17.16572 432.5148 

 17.24556 432.5974 

 17.32540 432.6799 

 17.40524 432.7625 

 17.48508 432.8450 

 17.56493 432.9275 

 17.64477 433.0100 

 17.72461 433.0924 

 17.80445 433.1749 

 17.88429 433.2573 

 17.96413 433.3397 

 18.04397 433.4221 

 18.12381 433.5045 

 18.20365 433.5868 

 18.28349 433.6692 

 18.36333 433.7515 

 18.44318 433.8338 

 18.52302 433.9161 

 18.60286 433.9983 

 18.68270 434.0806 

 18.76254 434.1628 

 18.84238 434.2451 

 18.92222 434.3272 

 19.00206 434.4095 

 19.08190 434.4916 

 19.16174 434.5738 

 19.24158 434.6559 

 19.32143 434.7381 

 19.40127 434.8202 

 19.48111 434.9023 

 19.56095 434.9844 

NASA/TM—2013-218094 F–4
 19.64079 435.0665 

 19.72063 435.1486 

 19.80047 435.2306 

 19.88031 435.3127 

 19.96015 435.3947 

 20.03999 435.4767 

 20.11983 435.5587 

 20.19967 435.6407 

 20.27951 435.7227 

 20.35935 435.8046 

 20.43919 435.8866 

 20.51903 435.9685 

 20.59887 436.0504 

 20.67871 436.1323 

 20.75855 436.2142 

 20.83839 436.2961 

 20.91823 436.3780 

 20.99807 436.4599 

 21.07791 436.5417 

 21.15775 436.6236 

 21.23759 436.7054 

 21.31742 436.7872 

 21.39726 436.8690 

 21.47710 436.9508 

 21.55694 437.0326 

 21.63678 437.1144 

 21.71662 437.1962 

 21.79646 437.2780 

 21.87630 437.3597 

 21.95614 437.4415 

 22.03598 437.5232 

 22.11582 437.6049 

 22.19566 437.6866 

 22.27550 437.7684 

 22.35534 437.8500 

 22.43518 437.9317 

 22.51502 438.0134 

 22.59486 438.0951 

 22.67470 438.1768 

 22.75454 438.2584 

 22.83438 438.3401 

 22.91422 438.4217 

 22.99406 438.5034 

 23.07390 438.5850 

 23.15374 438.6666 

 23.23358 438.7482 

 23.31342 438.8298 

 23.39326 438.9114 

 23.47310 438.9930 

 23.55294 439.0746 

 23.63278 439.1562 

 23.71262 439.2378 

 23.79246 439.3193 

 23.87230 439.4009 

 23.95214 439.4824 

 24.03197 439.5640 

 24.11181 439.6455 

 24.19165 439.7271 

 24.27149 439.8086 

 24.35133 439.8901 

 24.43117 439.9716 

 24.51101 440.0532 

 24.59085 440.1347 

NASA/TM—2013-218094 F–5
 24.67069 440.2162 

 24.75053 440.2977 

 24.83037 440.3792 

 24.91021 440.4607 

 24.99005 440.5422 

 25.06989 440.6237 

 25.14973 440.7052 

 25.22957 440.7867 

 25.30941 440.8681 

 25.38925 440.9496 

 25.46909 441.0311 

 25.54893 441.1125 

 25.62877 441.1940 

 25.70861 441.2755 

 25.78845 441.3569 

 25.86829 441.4384 

 25.94813 441.5199 

 26.02797 441.6013 

 26.10781 441.6828 

 26.18765 441.7643 

 26.26749 441.8457 

 26.34733 441.9272 

 26.42717 442.0086 

 26.50701 442.0900 

 26.58685 442.1715 

 26.66669 442.2529 

 26.74653 442.3344 

 26.82637 442.4158 

 26.90621 442.4973 

 26.98605 442.5787 

 27.06589 442.6602 

 27.14573 442.7416 

 27.22556 442.8231 

 27.30540 442.9045 

 27.38524 442.9860 

 27.46508 443.0674 

 27.54492 443.1489 

 27.62476 443.2304 

 27.70460 443.3119 

 27.78444 443.3933 

 27.86428 443.4748 

 27.94412 443.5563 

 28.02396 443.6378 

 28.10380 443.7192 

 28.18364 443.8007 

 28.26348 443.8822 

 28.34332 443.9637 

 28.42316 444.0452 

 28.50300 444.1267 

 28.58284 444.2082 

 28.66268 444.2896 

 28.74252 444.3712 

 28.82236 444.4526 

 28.90220 444.5341 

 28.98204 444.6157 

 29.06188 444.6972 

 29.14172 444.7787 

 29.22156 444.8603 

 29.30140 444.9418 

 29.38124 445.0233 

 29.46108 445.1049 

 29.54092 445.1864 

 29.62076 445.2680 

NASA/TM—2013-218094 F–6
 29.70060 445.3495 

 29.78044 445.4311 

 29.86028 445.5127 

 29.94011 445.5943 

 30.01995 445.6759 

 30.09979 445.7575 

 30.17963 445.8391 

 30.25947 445.9207 

 30.33931 446.0023 

 30.41915 446.0840 

 30.49899 446.1656 

 30.57883 446.2473 

 30.65867 446.3289 

 30.73851 446.4106 

 30.81835 446.4923 

 30.89819 446.5740 

 30.97803 446.6557 

 31.05787 446.7374 

 31.13771 446.8191 

 31.21755 446.9008 

 31.29739 446.9826 

 31.37723 447.0643 

 31.45707 447.1461 

 31.53691 447.2278 

 31.61675 447.3096 

 31.69659 447.3914 

 31.77643 447.4732 

 31.85627 447.5551 

 31.93611 447.6369 

 32.01595 447.7188 

 32.09579 447.8006 

 32.17563 447.8825 

 32.25547 447.9644 

 32.33531 448.0463 

 32.41515 448.1282 

 32.49499 448.2101 

 32.57483 448.2921 

 32.65467 448.3741 

 32.73450 448.4560 

 32.81435 448.5380 

 32.89418 448.6200 

 32.97403 448.7020 

 33.05386 448.7841 

 33.13371 448.8661 

 33.21354 448.9482 

 33.29338 449.0303 

 33.37322 449.1124 

 33.45306 449.1945 

 33.53290 449.2766 

 33.61274 449.3588 

 33.69258 449.4410 

 33.77242 449.5232 

 33.85226 449.6054 

 33.93210 449.6877 

 34.01194 449.7699 

 34.09178 449.8522 

 34.17162 449.9345 

 34.25146 450.0168 

 34.33130 450.0992 

 34.41114 450.1815 

 34.49098 450.2639 

 34.57082 450.3463 

 34.65066 450.4287 

NASA/TM—2013-218094 F–7
 34.73050 450.5112 

 34.81034 450.5936 

 34.89018 450.6761 

 34.97002 450.7586 

 35.04986 450.8411 

 35.12970 450.9236 

 35.20954 451.0062 

 35.28938 451.0888 

 35.36922 451.1714 

 35.44905 451.2541 

 35.52890 451.3368 

 35.60873 451.4195 

 35.68858 451.5022 

 35.76841 451.5850 

 35.84826 451.6678 

 35.92809 451.7506 

 36.00793 451.8334 

 36.08777 451.9163 

 36.16761 451.9992 

 36.24745 452.0821 

 36.32729 452.1651 

 36.40713 452.2481 

 36.48697 452.3311 

 36.56681 452.4142 

 36.64665 452.4973 

 36.72649 452.5803 

 36.80633 452.6635 

 36.88617 452.7466 

 36.96601 452.8299 

 37.04585 452.9131 

 37.12569 452.9964 

 37.20553 453.0797 

 37.28537 453.1630 

 37.36521 453.2464 

 37.44505 453.3298 

 37.52489 453.4133 

 37.60473 453.4967 

 37.68457 453.5803 

 37.76441 453.6638 

 37.84425 453.7475 

 37.92409 453.8311 

 38.00393 453.9148 

 38.08377 453.9985 

 38.16360 454.0822 

 38.24345 454.1660 

 38.32328 454.2498 

 38.40313 454.3337 

 38.48296 454.4177 

 38.56281 454.5016 

 38.64265 454.5856 

 38.72248 454.6696 

 38.80233 454.7538 

 38.88216 454.8379 

 38.96201 454.9221 

 39.04184 455.0063 

 39.12169 455.0906 

 39.20152 455.1749 

 39.28136 455.2592 

 39.36120 455.3437 

 39.44104 455.4281 

 39.52089 455.5126 

 39.60073 455.5972 

 39.68057 455.6818 

NASA/TM—2013-218094 F–8
 39.76041 455.7665 

 39.84026 455.8512 

 39.92010 455.9360 

 39.99994 456.0208 

 40.07360 456.0736 

 40.14721 456.0736 

 40.22081 456.1931 

 40.29442 456.2607 

 40.36802 456.3600 

 40.44163 456.4342 

 40.51523 456.5246 

 40.58884 456.6021 

 40.66244 456.6880 

 40.73605 456.7673 

 40.80965 456.8508 

 40.88326 456.9308 

 40.95686 457.0129 

 41.03046 457.0931 

 41.10407 457.1742 

 41.17767 457.2543 

 41.25128 457.3348 

 41.32489 457.4146 

 41.39849 457.4945 

 41.47210 457.5741 

 41.54570 457.6535 

 41.61930 457.7327 

 41.69291 457.8118 

 41.76651 457.8907 

 41.84012 457.9694 

 41.91372 458.0479 

 41.98733 458.1263 

 42.06093 458.2044 

 42.13454 458.2825 

 42.20814 458.3604 

 42.28175 458.4381 

 42.35535 458.5157 

 42.42896 458.5931 

 42.50256 458.6704 

 42.57616 458.7476 

 42.64977 458.8246 

 42.72337 458.9015 

 42.79698 458.9782 

 42.87058 459.0548 

 42.94419 459.1313 

 43.01779 459.2077 

 43.09140 459.2839 

 43.16500 459.3600 

 43.23861 459.4360 

 43.31221 459.5118 

 43.38581 459.5876 

 43.45942 459.6632 

 43.53302 459.7388 

 43.60663 459.8142 

 43.68024 459.8895 

 43.75384 459.9647 

 43.82745 460.0398 

 43.90105 460.1148 

 43.97466 460.1897 

 44.04826 460.2645 

 44.12186 460.3391 

 44.19547 460.4137 

 44.26907 460.4882 

 44.34268 460.5626 

NASA/TM—2013-218094 F–9
 44.41628 460.6370 

 44.48989 460.7112 

 44.56349 460.7853 

 44.63710 460.8593 

 44.71070 460.9333 

 44.78431 461.0071 

 44.85791 461.0809 

 44.93151 461.1546 

 45.00512 461.2282 

 45.07872 461.3017 

 45.15233 461.3752 

 45.22593 461.4485 

 45.29954 461.5218 

 45.37314 461.5950 

 45.44675 461.6681 

 45.52035 461.7412 

 45.59396 461.8141 

 45.66756 461.8870 

 45.74117 461.9598 

 45.81477 462.0326 

 45.88837 462.1052 

 45.96198 462.1779 

 46.03559 462.2504 

 46.10919 462.3229 

 46.18280 462.3953 

 46.25640 462.4676 

 46.33001 462.5398 

 46.40361 462.6120 

 46.47721 462.6841 

 46.55082 462.7562 

 46.62442 462.8282 

 46.69803 462.9001 

 46.77163 462.9719 

 46.84524 463.0437 

 46.91884 463.1155 

 46.99245 463.1871 

 47.06605 463.2587 

 47.13966 463.3303 

 47.21326 463.4017 

 47.28687 463.4731 

 47.36047 463.5445 

 47.43407 463.6158 

 47.45212 465.2026 

 47.47006 465.0741 

 47.48800 464.9553 

 47.50594 464.8462 

 47.52387 464.7455 

 47.54181 464.6525 

 47.55975 464.5662 

 47.57769 464.4858 

 47.59562 464.4109 

 47.61356 464.3408 

 47.63150 464.2749 

 47.64944 464.2129 

 47.66737 464.1543 

 47.68531 464.0987 

 47.70325 464.0458 

 47.72119 463.9954 

 47.73912 463.9471 

 47.75706 463.9007 

 47.77500 463.8561 

 47.79294 463.8130 

 47.81087 463.7714 

NASA/TM—2013-218094 F–10
 47.82881 463.7309 

 47.84675 463.6915 

 47.86469 463.6531 

 47.88263 463.6156 

 47.90056 463.5789 

 47.91850 463.5428 

 47.93644 463.5075 

 47.95438 463.4726 

 47.97231 463.4383 

 47.99025 463.4044 

 48.00819 463.3709 

 48.02613 463.3377 

 48.04406 463.3049 

 48.06200 463.2722 

 48.07994 463.2399 

 48.09788 463.2078 

 48.11581 463.1758 

 48.13375 463.1440 

 48.15169 463.1123 

 48.16963 463.0808 

 48.18757 463.0494 

 48.20551 463.0180 

 48.22344 462.9868 

 48.24138 462.9556 

 48.25932 462.9244 

 48.27726 462.8933 

 48.29519 462.8623 

 48.31313 462.8313 

 48.33107 462.8003 

 48.34901 462.7693 

 48.36694 462.7383 

 48.38488 462.7073 

 48.40282 462.6764 

 48.42076 462.6454 

 48.43869 462.6144 

 48.45663 462.5834 

 48.47457 462.5524 

 48.49251 462.5213 

 48.51044 462.4903 

 48.52839 462.4592 

 48.54632 462.4281 

 48.56426 462.3970 

 48.58220 462.3658 

 48.60014 462.3346 

 48.61807 462.3034 

 48.63601 462.2722 

 48.65395 462.2409 

 48.67189 462.2096 

 48.68982 462.1783 

 48.70776 462.1469 

 48.72570 462.1155 

 48.74364 462.0840 

 48.76157 462.0526 

 48.77951 462.0210 

 48.79745 461.9895 

 48.81539 461.9579 

 48.83332 461.9263 

 48.85126 461.8946 

 48.86920 461.8629 

 48.88714 461.8311 

 48.90508 461.7993 

 48.92301 461.7675 

 48.94095 461.7357 

NASA/TM—2013-218094 F–11
 48.95889 461.7037 

 48.97683 461.6718 

 48.99476 461.6398 

 49.01270 461.6078 

 49.03064 461.5757 

 49.04858 461.5437 

 49.06651 461.5115 

 49.08445 461.4793 

 49.10239 461.4471 

 49.12033 461.4149 

 49.13827 461.3825 

 49.15620 461.3502 

 49.17414 461.3178 

 49.19208 461.2854 

 49.21002 461.2529 

 49.22795 461.2204 

 49.24589 461.1879 

 49.25944 461.1688 

 49.27304 461.1559 

 49.28664 461.1484 

 49.30024 461.1459 

 49.31385 461.1482 

 49.32745 461.1550 

 49.34105 461.1659 

 49.35465 461.1808 

 49.36825 461.1994 

 49.38185 461.2215 

 49.39545 461.2470 

 49.40905 461.2755 

 49.42265 461.3070 

 49.43626 461.3412 

 49.44986 461.3781 

 49.46346 461.4173 

 49.47706 461.4588 

 49.49066 461.5025 

 49.50426 461.5482 

 49.51786 461.5959 

 49.53146 461.6452 

 49.54507 461.6963 

 49.55867 461.7489 

 49.57227 461.8030 

 49.58587 461.8585 

 49.59947 461.9153 

 49.61307 461.9733 

 49.62667 462.0324 

 49.64027 462.0927 

 49.65387 462.1539 

 49.66748 462.2161 

 49.68108 462.2791 

 49.69468 462.3430 

 49.70828 462.4077 

 49.72188 462.4731 

 49.73548 462.5391 

 49.74908 462.6058 

 49.76268 462.6731 

 49.77628 462.7409 

 49.78989 462.8092 

 49.80349 462.8781 

 49.81709 462.9473 

 49.83069 463.0170 

 49.84429 463.0871 

 49.85789 463.1576 

 49.87149 463.2284 

NASA/TM—2013-218094 F–12
 49.88509 463.2994 

 49.89869 463.3708 

 49.91230 463.4425 

 49.92590 463.5144 

 49.93950 463.5866 

 49.95310 463.6590 

 49.96670 463.7316 

 49.98030 463.8044 

 49.99390 463.8774 

 50.00750 463.9505 

 50.02110 464.0238 

 50.03471 464.0972 

 50.04831 464.1708 

 50.06191 464.2445 

 50.07551 464.3183 

 50.08911 464.3922 

 50.10271 464.4663 

 50.11631 464.5404 

 50.12991 464.6146 

 50.14351 464.6889 

 50.15712 464.7632 

 50.17072 464.8377 

 50.18432 464.9122 

 50.19792 464.9867 

 50.21152 465.0613 

 50.22512 465.1360 

 50.23872 465.2107 

 50.25232 465.2854 

 50.26593 465.3603 

 50.27953 465.4351 

 50.29313 465.5100 

 50.30673 465.5849 

 50.32033 465.6599 

 50.33393 465.7348 

 50.34753 465.8099 

 50.36113 465.8849 

 50.37473 465.9600 

 50.38834 466.0351 

 50.40194 466.1102 

 50.41554 466.1853 

 50.42914 466.2605 

 50.44274 466.3357 

 50.45634 466.4109 

 50.46994 466.4861 

 50.48354 466.5613 

 50.49714 466.6366 

 50.51075 466.7119 

 50.52435 466.7872 

 50.53795 466.8625 

 50.55155 466.9379 

 50.56515 467.0132 

 50.57875 467.0887 

 50.59235 467.1641 

 50.60595 467.2395 

 50.61955 467.3150 

 50.66056 467.4900 

 50.70137 467.6347 

 50.74218 467.7411 

 50.78298 467.8248 

 50.82379 467.8914 

 50.86460 467.9467 

 50.90541 467.9937 

 50.94622 468.0352 

NASA/TM—2013-218094 F–13
 50.98702 468.0727 

 51.02783 468.1075 

 51.06864 468.1404 

 51.10945 468.1719 

 51.15026 468.2026 

 51.19106 468.2326 

 51.23187 468.2622 

 51.27268 468.2914 

 51.31349 468.3205 

 51.35430 468.3493 

 51.39510 468.3780 

 51.43591 468.4067 

 51.47672 468.4353 

 51.51753 468.4638 

 51.55834 468.4923 

 51.59914 468.5208 

 51.63995 468.5491 

 51.68076 468.5775 

 51.72157 468.6059 

 51.76238 468.6342 

 51.80318 468.6625 

 51.84399 468.6907 

 51.88480 468.7189 

 51.92561 468.7471 

 51.96642 468.7753 

 52.00723 468.8035 

 52.04803 468.8316 

 52.08884 468.8597 

 52.12965 468.8878 

 52.17046 468.9159 

 52.21127 468.9439 

 52.25208 468.9719 

 52.29288 468.9998 

 52.33369 469.0278 

 52.37450 469.0558 

 52.41531 469.0837 

 52.45612 469.1116 

 52.49692 469.1394 

 52.53773 469.1673 

 52.57854 469.1951 

 52.61935 469.2229 

 52.66016 469.2507 

 52.70096 469.2784 

 52.74177 469.3062 

 52.78258 469.3338 

 52.82339 469.3615 

 52.86419 469.3892 

 52.90500 469.4168 

 52.94581 469.4445 

 52.98662 469.4720 

 53.02743 469.4996 

 53.06823 469.5272 

 53.10904 469.5547 

 53.14985 469.5822 

 53.19066 469.6096 

 53.23147 469.6371 

 53.27227 469.6646 

 53.31308 469.6920 

 53.35389 469.7194 

 53.39470 469.7468 

 53.43551 469.7741 

 53.47631 469.8015 

 53.51712 469.8288 

NASA/TM—2013-218094 F–14
 53.55793 469.8561 

 53.59874 469.8833 

 53.63955 469.9106 

 53.68036 469.9378 

 53.72116 469.9650 

 53.76197 469.9922 

 53.80278 470.0193 

 53.84359 470.0465 

 53.88440 470.0735 

 53.92521 470.1007 

 53.96601 470.1278 

 54.00682 470.1548 

 54.04763 470.1818 

 54.08844 470.2089 

 54.12925 470.2359 

 54.17005 470.2628 

 54.21086 470.2898 

 54.25167 470.3167 

 54.29248 470.3437 

 54.33329 470.3706 

 54.37409 470.3974 

 54.41490 470.4243 

 54.45571 470.4511 

 54.49652 470.4780 

 54.53733 470.5048 

 54.57813 470.5315 

 54.61894 470.5583 

 54.65975 470.5850 

 54.70056 470.6118 

 54.74137 470.6385 

 54.75445 470.6727 

 54.76741 470.6727 

 54.78036 471.0882 

 54.79332 471.4428 

 54.80628 471.7551 

 54.81924 472.0287 

 54.83220 472.2683 

 54.84516 472.4781 

 54.85812 472.6617 

 54.87107 472.8223 

 54.88403 472.9629 

 54.89699 473.0859 

 54.90995 473.1936 

 54.92290 473.2879 

 54.93586 473.3705 

 54.94882 473.4429 

 54.96178 473.5064 

 54.97474 473.5622 

 54.98770 473.6112 

 55.00066 473.6544 

 55.01361 473.6925 

 55.02657 473.7262 

 55.03953 473.7560 

 55.05249 473.7824 

 55.06544 473.8059 

 55.07840 473.8269 

 55.09136 473.8456 

 55.10432 473.8626 

 55.11728 473.8778 

 55.13024 473.8916 

 55.14320 473.9041 

 55.15615 473.9156 

 55.16911 473.9261 

NASA/TM—2013-218094 F–15
 55.18207 473.9359 

 55.19503 473.9449 

 55.20798 473.9532 

 55.22094 473.9611 

 55.23390 473.9684 

 55.24686 473.9754 

 55.25982 473.9821 

 55.27278 473.9884 

 55.28574 473.9944 

 55.29869 474.0003 

 55.31165 474.0060 

 55.32461 474.0114 

 55.33757 474.0168 

 55.35052 474.0220 

 55.36348 474.0270 

 55.37644 474.0320 

 55.38940 474.0369 

 55.40236 474.0417 

 55.41532 474.0465 

 55.42827 474.0513 

 55.44123 474.0559 

 55.45419 474.0605 

 55.46715 474.0652 

 55.48011 474.0697 

 55.49306 474.0743 

 55.50602 474.0788 

 55.51898 474.0833 

 55.53194 474.0878 

 55.54490 474.0923 

 55.55785 474.0967 

 55.57081 474.1012 

 55.58377 474.1057 

 55.59673 474.1101 

 55.60969 474.1145 

 55.62265 474.1190 

 55.63560 474.1234 

 55.64856 474.1278 

 55.66152 474.1322 

 55.67448 474.1366 

 55.68744 474.1410 

 55.70039 474.1454 

 55.71335 474.1498 

 55.72631 474.1542 

 55.73927 474.1586 

 55.75223 474.1630 

 55.76519 474.1674 

 55.77814 474.1718 

 55.79110 474.1762 

 55.80406 474.1806 

 55.81702 474.1850 

 55.82998 474.1894 

 55.84293 474.1938 

 55.85589 474.1982 

 55.86885 474.2026 

 55.88181 474.2070 

 55.89477 474.2114 

 55.90773 474.2159 

 55.92068 474.2202 

 55.93364 474.2247 

 55.94660 474.2291 

 55.95956 474.2335 

 55.97252 474.2380 

 55.98547 474.2424 

NASA/TM—2013-218094 F–16
 55.99843 474.2468 

 56.01139 474.2513 

 56.02435 474.2557 

 56.03731 474.2601 

 56.05027 474.2645 

 56.07415 474.2730 

 56.09792 474.2998 

 56.12170 474.3340 

 56.14547 474.3718 

 56.16925 474.4127 

 56.19302 474.4559 

 56.21680 474.5008 

 56.24058 474.5471 

 56.26435 474.5943 

 56.28813 474.6424 

 56.31190 474.6910 

 56.33568 474.7401 

 56.35946 474.7895 

 56.38324 474.8392 

 56.40701 474.8891 

 56.43079 474.9392 

 56.45456 474.9894 

 56.47834 475.0398 

 56.50211 475.0903 

 56.52589 475.1408 

 56.54967 475.1915 

 56.57344 475.2422 

 56.59722 475.2929 

 56.62099 475.3437 

 56.64477 475.3945 

 56.66855 475.4454 

 56.69233 475.4963 

 56.71610 475.5473 

 56.73988 475.5984 

 56.76365 475.6494 

 56.78743 475.7005 

 56.81121 475.7517 

 56.83498 475.8028 

 56.85876 475.8540 

 56.88253 475.9053 

 56.90631 475.9565 

 56.93008 476.0078 

 56.95386 476.0591 

 56.97764 476.1105 

 57.00142 476.1618 

 57.02519 476.2133 

 57.04897 476.2647 

 57.07274 476.3162 

 57.09652 476.3677 

 57.12030 476.4193 

 57.14407 476.4708 

 57.16785 476.5224 

 57.19162 476.5740 

 57.21540 476.6256 

 57.23918 476.6773 

 57.26295 476.7290 

 57.28673 476.7807 

 57.31050 476.8325 

 57.33428 476.8842 

 57.35806 476.9360 

 57.38183 476.9878 

 57.40561 477.0396 

 57.42939 477.0915 

NASA/TM—2013-218094 F–17
 57.45316 477.1433 

 57.47694 477.1952 

 57.50071 477.2471 

 57.52449 477.2990 

 57.54827 477.3509 

 57.57204 477.4029 

 57.59582 477.4548 

 57.61959 477.5068 

 57.64337 477.5589 

 57.66715 477.6109 

 57.69092 477.6629 

 57.71470 477.7150 

 57.73848 477.7671 

 57.76225 477.8191 

 57.78603 477.8712 

 57.80980 477.9233 

 57.83358 477.9755 

 57.85736 478.0276 

 57.88113 478.0798 

 57.90491 478.1320 

 57.92868 478.1841 

 57.95246 478.2363 

 57.97624 478.2886 

 58.00001 478.3408 

 58.02379 478.3931 

 58.04757 478.4453 

 58.07134 478.4975 

 58.09512 478.5498 

 58.11889 478.6021 

 58.14267 478.6544 

 58.16645 478.7067 

 58.19022 478.7590 

 58.21400 478.8113 

 58.23777 478.8636 

 58.26155 478.9160 

 58.28533 478.9684 

 58.30910 479.0207 

 58.33288 479.0731 

 58.35666 479.1255 

 58.38043 479.1779 

 58.40421 479.2303 

 58.42798 479.2827 

 58.45176 479.3351 

 58.45746 480.3622 

 58.46307 480.3237 

 58.46869 480.2871 

 58.47430 480.2523 

 58.47992 480.2193 

 58.48553 480.1878 

 58.49114 480.1580 

 58.49675 480.1297 

 58.50237 480.1027 

 58.50798 480.0771 

 58.51360 480.0528 

 58.51921 480.0296 

 58.52482 480.0077 

 58.53043 479.9867 

 58.53605 479.9669 

 58.54166 479.9480 

 58.54727 479.9300 

 58.55289 479.9129 

 58.55850 479.8966 

 58.56411 479.8812 

NASA/TM—2013-218094 F–18
 58.56973 479.8664 

 58.57534 479.8524 

 58.58095 479.8391 

 58.58656 479.8264 

 58.59218 479.8143 

 58.59779 479.8028 

 58.60340 479.7919 

 58.60902 479.7815 

 58.61463 479.7715 

 58.62024 479.7621 

 58.62586 479.7531 

 58.63147 479.7445 

 58.63708 479.7363 

 58.64270 479.7285 

 58.64831 479.7211 

 58.65392 479.7141 

 58.65953 479.7074 

 58.66515 479.7009 

 58.67076 479.6948 

 58.67638 479.6890 

 58.68199 479.6835 

 58.68760 479.6781 

 58.69321 479.6731 

 58.69883 479.6682 

 58.70444 479.6636 

 58.71006 479.6592 

 58.71567 479.6550 

 58.72128 479.6510 

 58.72689 479.6472 

 58.73251 479.6435 

 58.73812 479.6400 

 58.74373 479.6366 

 58.74935 479.6334 

 58.75496 479.6303 

 58.76057 479.6274 

 58.76619 479.6246 

 58.77180 479.6219 

 58.77741 479.6193 

 58.78302 479.6168 

 58.78864 479.6145 

 58.79425 479.6122 

 58.79987 479.6100 

 58.80548 479.6079 

 58.81109 479.6058 

 58.81670 479.6039 

 58.82232 479.6021 

 58.82793 479.6003 

 58.83355 479.5985 

 58.83916 479.5968 

 58.84477 479.5952 

 58.85038 479.5937 

 58.85600 479.5922 

 58.86161 479.5908 

 58.86722 479.5894 

 58.87284 479.5880 

 58.87845 479.5867 

 58.88406 479.5854 

 58.88968 479.5843 

 58.89529 479.5830 

 58.90090 479.5819 

 58.90652 479.5808 

 58.91213 479.5797 

 58.91774 479.5786 

NASA/TM—2013-218094 F–19
 58.92336 479.5776 

 58.92897 479.5766 

 58.93458 479.5756 

 58.94019 479.5747 

 58.94581 479.5738 

 58.95142 479.5729 

 58.95704 479.5720 

 58.96265 479.5712 

 58.96826 479.5703 

 58.97387 479.5695 

 58.97948 479.5688 

 58.98510 479.5680 

 58.99071 479.5672 

 58.99633 479.5665 

 59.00194 479.5657 

 59.00755 479.5650 

 59.01316 479.5643 

 59.01878 479.5636 

 59.02501 479.5627 

 59.03108 479.5645 

 59.03715 479.5675 

 59.04322 479.5716 

 59.04929 479.5768 

 59.05535 479.5830 

 59.06142 479.5902 

 59.06749 479.5983 

 59.07356 479.6073 

 59.07963 479.6172 

 59.08569 479.6278 

 59.09176 479.6393 

 59.09783 479.6514 

 59.10390 479.6642 

 59.10997 479.6776 

 59.11604 479.6917 

 59.12210 479.7065 

 59.12817 479.7217 

 59.13424 479.7376 

 59.14031 479.7539 

 59.14638 479.7707 

 59.15245 479.7879 

 59.15852 479.8056 

 59.16459 479.8238 

 59.17065 479.8423 

 59.17672 479.8612 

 59.18279 479.8804 

 59.18886 479.9001 

 59.19493 479.9200 

 59.20100 479.9403 

 59.20706 479.9608 

 59.21313 479.9816 

 59.21920 480.0027 

 59.22527 480.0240 

 59.23134 480.0456 

 59.23740 480.0674 

 59.24347 480.0894 

 59.24954 480.1117 

 59.25561 480.1341 

 59.26168 480.1567 

 59.26775 480.1795 

 59.27382 480.2025 

 59.27988 480.2256 

 59.28595 480.2489 

 59.29202 480.2723 

NASA/TM—2013-218094 F–20
 59.29809 480.2958 

 59.30416 480.3195 

 59.31023 480.3432 

 59.31630 480.3671 

 59.32236 480.3911 

 59.32843 480.4153 

 59.33450 480.4395 

 59.34057 480.4638 

 59.34664 480.4882 

 59.35271 480.5127 

 59.35877 480.5373 

 59.36484 480.5619 

 59.37091 480.5866 

 59.37698 480.6114 

 59.38305 480.6363 

 59.38911 480.6613 

 59.39518 480.6862 

 59.40125 480.7113 

 59.40732 480.7364 

 59.41339 480.7615 

 59.41946 480.7868 

 59.42553 480.8120 

 59.43159 480.8372 

 59.43766 480.8626 

 59.44373 480.8879 

 59.44980 480.9134 

 59.45587 480.9388 

 59.46194 480.9643 

 59.46801 480.9898 

 59.47408 481.0154 

 59.48014 481.0410 

 59.48621 481.0666 

 59.49228 481.0922 

 59.49835 481.1179 

 59.50441 481.1436 

 59.51048 481.1693 

 59.51655 481.1951 

 59.52262 481.2208 

 59.52869 481.2466 

 59.53476 481.2724 

 59.54082 481.2982 

 59.54689 481.3241 

 59.55296 481.3500 

 59.55903 481.3759 

 59.56510 481.4018 

 59.57117 481.4277 

 59.57724 481.4536 

 59.58331 481.4796 

 59.58937 481.5056 

 59.59544 481.5315 

 59.60151 481.5575 

 59.60758 481.5836 

 59.61365 481.6096 

 59.61972 481.6356 

 59.62578 481.6617 

 59.63185 481.6877 

 59.64998 481.7537 

 59.66818 481.8122 

 59.68638 481.8614 

 59.70458 481.9035 

 59.72278 481.9397 

 59.74098 481.9714 

 59.75918 481.9993 

NASA/TM—2013-218094 F–21
 59.77738 482.0241 

 59.79558 482.0466 

 59.81378 482.0672 

 59.83198 482.0862 

 59.85018 482.1040 

 59.86839 482.1207 

 59.88659 482.1367 

 59.90479 482.1520 

 59.92299 482.1669 

 59.94118 482.1812 

 59.95938 482.1954 

 59.97759 482.2092 

 59.99579 482.2228 

 60.01399 482.2362 

 60.03219 482.2495 

 60.05039 482.2627 

 60.06859 482.2758 

 60.08679 482.2888 

 60.10499 482.3018 

 60.12319 482.3147 

 60.14139 482.3276 

 60.15959 482.3405 

 60.17779 482.3534 

 60.19600 482.3661 

 60.21420 482.3790 

 60.23240 482.3918 

 60.25060 482.4045 

 60.26880 482.4173 

 60.28699 482.4301 

 60.30520 482.4428 

 60.32340 482.4555 

 60.34160 482.4683 

 60.35980 482.4810 

 60.37800 482.4938 

 60.39620 482.5065 

 60.41440 482.5193 

 60.43260 482.5320 

 60.45080 482.5447 

 60.46900 482.5574 

 60.48720 482.5702 

 60.50540 482.5829 

 60.52360 482.5956 

 60.54181 482.6083 

 60.56001 482.6210 

 60.57821 482.6337 

 60.59641 482.6464 

 60.61460 482.6591 

 60.63280 482.6718 

 60.65101 482.6845 

 60.66921 482.6972 

 60.68741 482.7099 

 60.70561 482.7226 

 60.72381 482.7352 

 60.74201 482.7479 

 60.76021 482.7606 

 60.77841 482.7733 

 60.79661 482.7860 

 60.81481 482.7987 

 60.83301 482.8114 

 60.85121 482.8241 

 60.86942 482.8368 

 60.88762 482.8495 

 60.90582 482.8621 

NASA/TM—2013-218094 F–22
 60.92402 482.8748 

 60.94221 482.8875 

 60.96041 482.9001 

 60.97862 482.9128 

 60.99682 482.9255 

 61.01502 482.9382 

 61.03322 482.9508 

 61.05142 482.9635 

 61.06962 482.9761 

 61.08782 482.9887 

 61.10602 483.0014 

 61.12422 483.0141 

 61.14242 483.0267 

 61.16062 483.0393 

 61.17882 483.0520 

 61.19702 483.0646 

 61.21523 483.0772 

 61.23343 483.0899 

 61.25163 483.1026 

 61.26982 483.1152 

 61.28802 483.1278 

 61.30622 483.1405 

 61.32443 483.1531 

 61.34263 483.1657 

 61.36083 483.1784 

 61.37903 483.1910 

 61.39723 483.2036 

 61.41543 483.2163 

 61.43363 483.2289 

 61.45183 483.2415 

 61.47003 483.2542 

 61.47612 483.2700 

 61.48197 483.2700 

 61.48782 483.4413 

 61.49368 483.5986 

 61.49953 483.7451 

 61.50538 483.8813 

 61.51123 484.0080 

 61.51709 484.1259 

 61.52294 484.2355 

 61.52879 484.3376 

 61.53465 484.4324 

 61.54050 484.5207 

 61.54635 484.6028 

 61.55220 484.6792 

 61.55805 484.7504 

 61.56391 484.8166 

 61.56976 484.8783 

 61.57561 484.9358 

 61.58146 484.9893 

 61.58731 485.0392 

 61.59317 485.0858 

 61.59902 485.1293 

 61.60487 485.1699 

 61.61073 485.2079 

 61.61658 485.2434 

 61.62243 485.2766 

 61.62828 485.3076 

 61.63414 485.3368 

 61.63999 485.3640 

 61.64584 485.3897 

 61.65170 485.4138 

 61.65755 485.4365 

NASA/TM—2013-218094 F–23
 61.66340 485.4579 

 61.66925 485.4780 

 61.67511 485.4970 

 61.68096 485.5150 

 61.68681 485.5319 

 61.69266 485.5480 

 61.69851 485.5633 

 61.70437 485.5778 

 61.71022 485.5916 

 61.71607 485.6047 

 61.72192 485.6172 

 61.72778 485.6292 

 61.73363 485.6407 

 61.73948 485.6517 

 61.74533 485.6622 

 61.75119 485.6724 

 61.75704 485.6822 

 61.76289 485.6916 

 61.76875 485.7007 

 61.77460 485.7096 

 61.78045 485.7181 

 61.78630 485.7265 

 61.79216 485.7346 

 61.79801 485.7424 

 61.80386 485.7501 

 61.80971 485.7576 

 61.81556 485.7650 

 61.82142 485.7722 

 61.82727 485.7792 

 61.83312 485.7861 

 61.83897 485.7930 

 61.84483 485.7997 

 61.85068 485.8062 

 61.85653 485.8127 

 61.86238 485.8191 

 61.86824 485.8254 

 61.87409 485.8317 

 61.87994 485.8378 

 61.88580 485.8439 

 61.89165 485.8500 

 61.89750 485.8560 

 61.90335 485.8619 

 61.90921 485.8679 

 61.91506 485.8737 

 61.92091 485.8796 

 61.92676 485.8854 

 61.93261 485.8912 

 61.93847 485.8969 

 61.94432 485.9026 

 61.95017 485.9084 

 61.95602 485.9140 

 61.96188 485.9197 

 61.96773 485.9253 

 61.97358 485.9309 

 61.97943 485.9365 

 61.98529 485.9421 

 61.99114 485.9476 

 61.99699 485.9532 

 62.00285 485.9587 

 62.00870 485.9643 

 62.01455 485.9698 

 62.02040 485.9753 

 62.02626 485.9808 

NASA/TM—2013-218094 F–24
 62.03211 485.9863 

 62.03796 485.9918 

 62.04381 485.9973 

 62.04967 486.0027 

 62.05552 486.0082 

 62.06137 486.0137 

 62.08459 486.0366 

 62.10780 486.0734 

 62.13102 486.1157 

 62.15423 486.1586 

 62.17744 486.2027 

 62.20065 486.2474 

 62.22387 486.2926 

 62.24708 486.3382 

 62.27029 486.3839 

 62.29351 486.4298 

 62.31672 486.4759 

 62.33993 486.5219 

 62.36314 486.5681 

 62.38636 486.6144 

 62.40957 486.6606 

 62.43278 486.7069 

 62.45599 486.7532 

 62.47921 486.7996 

 62.50242 486.8459 

 62.52563 486.8922 

 62.54885 486.9386 

 62.57206 486.9850 

 62.59527 487.0313 

 62.61848 487.0777 

 62.64170 487.1241 

 62.66491 487.1705 

 62.68813 487.2169 

 62.71134 487.2634 

 62.73455 487.3098 

 62.75776 487.3562 

 62.78098 487.4026 

 62.80419 487.4490 

 62.82740 487.4955 

 62.85062 487.5420 

 62.87383 487.5884 

 62.89704 487.6349 

 62.92025 487.6813 

 62.94347 487.7278 

 62.96668 487.7743 

 62.98989 487.8208 

 63.01311 487.8672 

 63.03632 487.9137 

 63.05953 487.9602 

 63.08274 488.0067 

 63.10596 488.0532 

 63.12917 488.0996 

 63.15239 488.1462 

 63.17560 488.1927 

 63.19881 488.2392 

 63.22202 488.2857 

 63.24524 488.3322 

 63.26845 488.3788 

 63.29166 488.4253 

 63.31488 488.4717 

 63.33809 488.5183 

 63.36130 488.5648 

 63.38451 488.6113 

NASA/TM—2013-218094 F–25
 63.40773 488.6579 

 63.43094 488.7044 

 63.45415 488.7509 

 63.47737 488.7975 

 63.50058 488.8440 

 63.52379 488.8905 

 63.54700 488.9370 

 63.57022 488.9836 

 63.59343 489.0301 

 63.61664 489.0766 

 63.63986 489.1231 

 63.66307 489.1696 

 63.68628 489.2161 

 63.70950 489.2627 

 63.73271 489.3092 

 63.75592 489.3557 

 63.77913 489.4022 

 63.80235 489.4487 

 63.82556 489.4952 

 63.84877 489.5417 

 63.87199 489.5882 

 63.89520 489.6348 

 63.91841 489.6813 

 63.94162 489.7278 

 63.96484 489.7743 

 63.98805 489.8208 

 64.01126 489.8673 

 64.03448 489.9138 

 64.05769 489.9603 

 64.08090 490.0068 

 64.10412 490.0533 

 64.12733 490.0997 

 64.15054 490.1462 

 64.17375 490.1927 

 64.19697 490.2392 

 64.22018 490.2856 

 64.24339 490.3321 

 64.26661 490.3786 

 64.28982 490.4251 

 64.31303 490.4716 

 64.33624 490.5180 

 64.35946 490.5645 

 64.38267 490.6109 

 64.40588 490.6574 

 64.41123 491.4302 

 64.41669 491.3915 

 64.42213 491.3554 

 64.42758 491.3219 

 64.43303 491.2906 

 64.43848 491.2616 

 64.44393 491.2345 

 64.44938 491.2093 

 64.45483 491.1859 

 64.46027 491.1642 

 64.46572 491.1440 

 64.47118 491.1253 

 64.47662 491.1079 

 64.48207 491.0918 

 64.48752 491.0769 

 64.49297 491.0631 

 64.49841 491.0504 

 64.50387 491.0385 

 64.50932 491.0277 

NASA/TM—2013-218094 F–26
 64.51476 491.0176 

 64.52021 491.0084 

 64.52566 490.9999 

 64.53111 490.9921 

 64.53656 490.9850 

 64.54201 490.9785 

 64.54745 490.9725 

 64.55290 490.9671 

 64.55836 490.9622 

 64.56380 490.9577 

 64.56925 490.9537 

 64.57470 490.9502 

 64.58015 490.9470 

 64.58560 490.9441 

 64.59105 490.9416 

 64.59650 490.9394 

 64.60194 490.9375 

 64.60739 490.9359 

 64.61285 490.9346 

 64.61829 490.9335 

 64.62374 490.9326 

 64.62919 490.9319 

 64.63464 490.9314 

 64.64009 490.9312 

 64.64554 490.9311 

 64.65099 490.9311 

 64.65643 490.9313 

 64.66188 490.9316 

 64.66734 490.9322 

 64.67278 490.9327 

 64.67823 490.9335 

 64.68368 490.9343 

 64.68913 490.9352 

 64.69458 490.9363 

 64.70003 490.9374 

 64.70547 490.9386 

 64.71092 490.9398 

 64.71637 490.9412 

 64.72182 490.9426 

 64.72727 490.9441 

 64.73272 490.9456 

 64.73817 490.9473 

 64.74361 490.9489 

 64.74907 490.9506 

 64.75452 490.9524 

 64.75996 490.9542 

 64.76541 490.9560 

 64.77086 490.9579 

 64.77631 490.9598 

 64.78176 490.9617 

 64.78721 490.9637 

 64.79266 490.9657 

 64.79810 490.9677 

 64.80356 490.9697 

 64.80901 490.9718 

 64.81445 490.9739 

 64.81990 490.9760 

 64.82535 490.9782 

 64.83080 490.9803 

 64.83625 490.9825 

 64.84170 490.9847 

 64.84715 490.9869 

 64.85259 490.9891 

NASA/TM—2013-218094 F–27
 64.85805 490.9914 

 64.86349 490.9936 

 64.86894 490.9959 

 64.87439 490.9981 

 64.87984 491.0004 

 64.88529 491.0027 

 64.89074 491.0050 

 64.89619 491.0074 

 64.90163 491.0096 

 64.90708 491.0120 

 64.91254 491.0143 

 64.91798 491.0166 

 64.92343 491.0189 

 64.92888 491.0212 

 64.93433 491.0236 

 64.93978 491.0260 

 64.94523 491.0283 

 64.95068 491.0307 

 64.95612 491.0331 

 64.96181 491.0350 

 64.96768 491.0396 

 64.97356 491.0451 

 64.97942 491.0515 

 64.98530 491.0585 

 64.99117 491.0663 

 64.99704 491.0748 

 65.00291 491.0839 

 65.00878 491.0937 

 65.01466 491.1039 

 65.02052 491.1147 

 65.02640 491.1259 

 65.03226 491.1376 

 65.03814 491.1498 

 65.04401 491.1623 

 65.04988 491.1752 

 65.05576 491.1884 

 65.06162 491.2020 

 65.06750 491.2159 

 65.07336 491.2300 

 65.07924 491.2444 

 65.08511 491.2590 

 65.09098 491.2739 

 65.09686 491.2890 

 65.10272 491.3043 

 65.10860 491.3197 

 65.11446 491.3354 

 65.12034 491.3512 

 65.12621 491.3672 

 65.13208 491.3832 

 65.13795 491.3994 

 65.14382 491.4158 

 65.14970 491.4323 

 65.15556 491.4489 

 65.16144 491.4656 

 65.16730 491.4823 

 65.17318 491.4992 

 65.17905 491.5162 

 65.18492 491.5332 

 65.19080 491.5503 

 65.19666 491.5675 

 65.20254 491.5847 

 65.20840 491.6021 

 65.21428 491.6194 

NASA/TM—2013-218094 F–28
 65.22015 491.6368 

 65.22602 491.6543 

 65.23190 491.6699 

 65.23776 491.6699 

 65.24364 491.6699 

 65.24950 491.6699 

 65.25538 491.6699 

 65.26125 491.6699 

 65.26712 491.6699 

 65.27299 491.6699 

 65.27886 491.6699 

 65.28474 491.6699 

 65.29060 491.6699 

 65.29648 491.6699 

 65.30235 491.6699 

 65.30822 491.6699 

 65.31409 491.6699 

 65.31996 491.6699 

 65.32584 491.6699 

 65.33170 491.6699 

 65.33758 491.6699 

 65.34344 491.6699 

 65.34932 491.6699 

 65.35519 491.6699 

 65.36106 491.6699 

 65.36693 491.6699 

 65.37280 491.6699 

 65.37868 491.6699 

 65.38454 491.6699 

 65.39042 491.6699 

 65.39629 491.6699 

 65.40216 491.6699 

 65.40803 491.6699 

 65.41390 491.6699 

 65.41978 491.6699 

 65.42564 491.6699 

 65.43152 491.6699 

 65.43739 491.6699 

 65.44326 491.6699 

 65.44913 491.6699 

 65.45500 491.6699 

 65.46087 491.6699 

 65.46674 491.6699 

 65.47262 491.6699 

 65.47849 491.6699 

 65.48436 491.6699 

 65.49023 491.6699 

 65.49610 491.6699 

 65.50197 491.6699 

 65.50784 491.6699 

 65.51372 491.6699 

 65.51958 491.6699 

 65.52546 491.6699 

 65.53133 491.6699 

 65.53720 491.6699 

 65.54307 491.6699 

 65.54894 491.6699 

 65.56672 491.6699 

 65.58434 491.6699 

 65.60195 491.6699 

 65.61957 491.6699 

 65.63719 491.6699 

 65.65481 491.6699 

NASA/TM—2013-218094 F–29
 65.67242 491.6699 

 65.69005 491.6699 

 65.70766 491.6699 

 65.72528 491.6699 

 65.74290 491.6699 

 65.76052 491.6699 

 65.77814 491.6699 

 65.79575 491.6699 

 65.81338 491.6699 

 65.83099 491.6699 

 65.84861 491.6699 

 65.86623 491.6699 

 65.88385 491.6699 

 65.90147 491.6699 

 65.91909 491.6699 

 65.93671 491.6699 

 65.95432 491.6699 

 65.97194 491.6699 

 65.98956 491.6699 

 66.00718 491.6699 

 66.02480 491.6699 

 66.04242 491.6699 

 66.06004 491.6699 

 66.07765 491.6699 

 66.09528 491.6699 

 66.11289 491.6699 

 66.13051 491.6699 

 66.14812 491.6699 

 66.16575 491.6699 

 66.18336 491.6699 

 66.20098 491.6699 

 66.21861 491.6699 

 66.23622 491.6699 

 66.25384 491.6699 

 66.27146 491.6699 

 66.28908 491.6699 

 66.30669 491.6699 

 66.32431 491.6699 

 66.34193 491.6699 

 66.35955 491.6699 

 66.37717 491.6699 

 66.39479 491.6699 

 66.41241 491.6699 

 66.43002 491.6699 

 66.44765 491.6699 

 66.46526 491.6699 

 66.48288 491.6699 

 66.50050 491.6699 

 66.51812 491.6699 

 66.53574 491.6699 

 66.55335 491.6699 

 66.57098 491.6699 

 66.58859 491.6699 

 66.60621 491.6699 

 66.62383 491.6699 

 66.64145 491.6699 

 66.65907 491.6699 

 66.67668 491.6699 

 66.69431 491.6699 

 66.71192 491.6699 

 66.72954 491.6699 

 66.74716 491.6699 

 66.76478 491.6699 

NASA/TM—2013-218094 F–30
 66.78239 491.6699 

 66.80002 491.6699 

 66.81763 491.6699 

 66.83525 491.6699 

 66.85287 491.6699 

 66.87049 491.6699 

 66.88811 491.6699 

 66.90572 491.6699 

 66.92335 491.6699 

 66.94096 491.6699 

 66.95858 491.6699 

 66.97620 491.6699 

 66.99382 491.6699 

 67.01144 491.6699 

 67.02906 491.6699 

 67.04668 491.6699 

 67.06429 491.6699 

 67.08191 491.6699 

 67.09953 491.6699 

 67.11715 491.6699 

 67.13477 491.6699 

 67.15239 491.6699 

 67.17001 491.6699 

 67.18762 491.6699 

 67.20525 491.6699 

 67.22286 491.6699 

 67.24048 491.6699 

 67.25809 491.6699 

 67.27572 491.6699 

 67.29333 491.6699 

 67.31095 491.6699 

 67.32858 491.6699 

 67.33422 491.6699 

 67.33987 491.6699 

 67.34552 491.6699 

 67.35117 491.6699 

 67.35682 491.6699 

 67.36247 491.6699 

 67.36813 491.6699 

 67.37377 491.6699 

 67.37943 491.6699 

 67.38508 491.6699 

 67.39072 491.6699 

 67.39638 491.6699 

 67.40202 491.6699 

 67.40768 491.6699 

 67.41333 491.6699 

 67.41898 491.6699 

 67.42463 491.6699 

 67.43028 491.6699 

 67.43593 491.6699 

 67.44158 491.6699 

 67.44724 491.6699 

 67.45288 491.6699 

 67.45853 491.6699 

 67.46419 491.6699 

 67.46983 491.6699 

 67.47549 491.6699 

 67.48114 491.6699 

 67.48679 491.6699 

 67.49244 491.6699 

 67.49809 491.6699 

 67.50374 491.6699 

NASA/TM—2013-218094 F–31
 67.50939 491.6699 

 67.51504 491.6699 

 67.52069 491.6699 

 67.52634 491.6699 

 67.53199 491.6699 

 67.53764 491.6699 

 67.54330 491.6699 

 67.54894 491.6699 

 67.55460 491.6699 

 67.56025 491.6699 

 67.56590 491.6699 

 67.57155 491.6699 

 67.57720 491.6699 

 67.58285 491.6699 

 67.58850 491.6699 

 67.59415 491.6699 

 67.59980 491.6699 

 67.60545 491.6699 

 67.61111 491.6699 

 67.61675 491.6699 

 67.62241 491.6699 

 67.62805 491.6699 

 67.63371 491.6699 

 67.63936 491.6699 

 67.64500 491.6699 

 67.65066 491.6699 

 67.65631 491.6699 

 67.66196 491.6699 

 67.66761 491.6699 

 67.67326 491.6699 

 67.67891 491.6699 

 67.68456 491.6699 

 67.69022 491.6699 

 67.69586 491.6699 

 67.70152 491.6699 

 67.70717 491.6699 

 67.71281 491.6699 

 67.71847 491.6699 

 67.72412 491.6699 

 67.72977 491.6699 

 67.73542 491.6699 

 67.74107 491.6699 

 67.74672 491.6699 

 67.75237 491.6699 

 67.75802 491.6699 

 67.76367 491.6699 

 67.76933 491.6699 

 67.77497 491.6699 

 67.78062 491.6699 

 67.78628 491.6699 

 67.79192 491.6699 

 67.79758 491.6699 

 67.80323 491.6699 

 67.80888 491.6699 

 67.81453 491.6699 

 67.82018 491.6699 

 67.82583 491.6699 

 67.83148 491.6699 

 67.83713 491.6699 

 67.84278 491.6699 

 67.84843 491.6699 

 67.85408 491.6699 

 67.85973 491.6699 

NASA/TM—2013-218094 F–32
 67.86539 491.6699 

 67.87103 491.6699 

 67.87669 491.6699 

 67.88234 491.6699 

 67.88799 491.6699 

 67.89364 491.6699 

 67.89929 491.6699 

 67.92163 491.6699 

 67.94381 491.6699 

 67.96599 491.6699 

 67.98816 491.6699 

 68.01034 491.6699 

 68.03252 491.6699 

 68.05469 491.6699 

 68.07687 491.6699 

 68.09904 491.6699 

 68.12122 491.6699 

 68.14339 491.6699 

 68.16557 491.6699 

 68.18774 491.6699 

 68.20992 491.6699 

 68.23209 491.6699 

 68.25427 491.6699 

 68.27644 491.6699 

 68.29862 491.6699 

 68.32080 491.6699 

 68.34297 491.6699 

 68.36515 491.6699 

 68.38732 491.6699 

 68.40950 491.6699 

 68.43168 491.6699 

 68.45385 491.6699 

 68.47603 491.6699 

 68.49821 491.6699 

 68.52038 491.6699 

 68.54256 491.6699 

 68.56473 491.6699 

 68.58691 491.6699 

 68.60909 491.6699 

 68.63126 491.6699 

 68.65343 491.6699 

 68.67561 491.6699 

 68.69778 491.6699 

 68.71996 491.6699 

 68.74213 491.6699 

 68.76431 491.6699 

 68.78649 491.6699 

 68.80866 491.6699 

 68.83084 491.6699 

 68.85301 491.6699 

 68.87519 491.6699 

 68.89737 491.6699 

 68.91954 491.6699 

 68.94172 491.6699 

 68.96390 491.6699 

 68.98607 491.6699 

 69.00825 491.6699 

 69.03042 491.6699 

 69.05260 491.6699 

 69.07478 491.6699 

 69.09695 491.6699 

 69.11913 491.6699 

 69.14130 491.6699 

NASA/TM—2013-218094 F–33
 69.16348 491.6699 

 69.18565 491.6699 

 69.20782 491.6699 

 69.23000 491.6699 

 69.25218 491.6699 

 69.27435 491.6699 

 69.29653 491.6699 

 69.31870 491.6699 

 69.34088 491.6699 

 69.36306 491.6699 

 69.38523 491.6699 

 69.40741 491.6699 

 69.42959 491.6699 

 69.45176 491.6699 

 69.47394 491.6699 

 69.49611 491.6699 

 69.51829 491.6699 

 69.54047 491.6699 

 69.56264 491.6699 

 69.58482 491.6699 

 69.60699 491.6699 

 69.62917 491.6699 

 69.65134 491.6699 

 69.67352 491.6699 

 69.69569 491.6699 

 69.71787 491.6699 

 69.74004 491.6699 

 69.76222 491.6699 

 69.78439 491.6699 

 69.80657 491.6699 

 69.82875 491.6699 

 69.85092 491.6699 

 69.87310 491.6699 

 69.89528 491.6699 

 69.91745 491.6699 

 69.93963 491.6699 

 69.96180 491.6699 

 69.98398 491.6699 

 70.00616 491.6699 

 70.02833 491.6699 

 70.05051 491.6699 

 70.07268 491.6699 

 70.09486 491.6699 

 70.11703 491.6699 

 70.13921 491.6699 

 70.14417 491.6699 

 70.14937 491.6699 

 70.15456 491.6699 

 70.15974 491.6699 

 70.16494 491.6699 

 70.17013 491.6699 

 70.17532 491.6699 

 70.18051 491.6699 

 70.18570 491.6699 

 70.19089 491.6699 

 70.19608 491.6699 

 70.20127 491.6699 

 70.20647 491.6699 

 70.21165 491.6699 

 70.21684 491.6699 

 70.22204 491.6699 

 70.22723 491.6699 

 70.23241 491.6699 

NASA/TM—2013-218094 F–34
 70.23761 491.6699 

 70.24280 491.6699 

 70.24799 491.6699 

 70.25318 491.6699 

 70.25837 491.6699 

 70.26357 491.6699 

 70.26875 491.6699 

 70.27394 491.6699 

 70.27914 491.6699 

 70.28432 491.6699 

 70.28951 491.6699 

 70.29471 491.6699 

 70.29990 491.6699 

 70.30508 491.6699 

 70.31028 491.6699 

 70.31547 491.6699 

 70.32066 491.6699 

 70.32585 491.6699 

 70.33104 491.6699 

 70.33624 491.6699 

 70.34142 491.6699 

 70.34661 491.6699 

 70.35181 491.6699 

 70.35699 491.6699 

 70.36218 491.6699 

 70.36738 491.6699 

 70.37257 491.6699 

 70.37776 491.6699 

 70.38295 491.6699 

 70.38814 491.6699 

 70.39333 491.6699 

 70.39852 491.6699 

 70.40371 491.6699 

 70.40891 491.6699 

 70.41409 491.6699 

 70.41928 491.6699 

 70.42448 491.6699 

 70.42966 491.6699 

 70.43486 491.6699 

 70.44005 491.6699 

 70.44524 491.6699 

 70.45043 491.6699 

 70.45562 491.6699 

 70.46081 491.6699 

 70.46600 491.6699 

 70.47119 491.6699 

 70.47638 491.6699 

 70.48158 491.6699 

 70.48676 491.6699 

 70.49196 491.6699 

 70.49715 491.6699 

 70.50233 491.6699 

 70.50753 491.6699 

 70.51272 491.6699 

 70.51791 491.6699 

 70.52310 491.6699 

 70.52829 491.6699 

 70.53348 491.6699 

 70.53867 491.6699 

 70.54386 491.6699 

 70.54906 491.6699 

 70.55424 491.6699 

 70.55943 491.6699 

NASA/TM—2013-218094 F–35
 70.56463 491.6699 

 70.56982 491.6699 

 70.57500 491.6699 

 70.58020 491.6699 

 70.58539 491.6699 

 70.59058 491.6699 

 70.59577 491.6699 

 70.60096 491.6699 

 70.60616 491.6699 

 70.61134 491.6699 

 70.61653 491.6699 

 70.62173 491.6699 

 70.62691 491.6699 

 70.63210 491.6699 

 70.63730 491.6699 

 70.64249 491.6699 

 70.64768 491.6699 

 70.65287 491.6699 

 70.65806 491.6699 

 70.66325 491.6699 

 70.66892 491.6699 

 70.67455 491.6699 

 70.68016 491.6699 

 70.68578 491.6699 

 70.69140 491.6699 

 70.69701 491.6699 

 70.70263 491.6699 

 70.70825 491.6699 

 70.71387 491.6699 

 70.71948 491.6699 

 70.72511 491.6699 

 70.73072 491.6699 

 70.73634 491.6699 

 70.74196 491.6699 

 70.74757 491.6699 

 70.75319 491.6699 

 70.75881 491.6699 

 70.76443 491.6699 

 70.77005 491.6699 

 70.77567 491.6699 

 70.78128 491.6699 

 70.78690 491.6699 

 70.79252 491.6699 

 70.79813 491.6699 

 70.80376 491.6699 

 70.80937 491.6699 

 70.81499 491.6699 

 70.82061 491.6699 

 70.82623 491.6699 

 70.83184 491.6699 

 70.83746 491.6699 

 70.84308 491.6699 

 70.84869 491.6699 

 70.85432 491.6699 

 70.85993 491.6699 

 70.86555 491.6699 

 70.87117 491.6699 

 70.87679 491.6699 

 70.88240 491.6699 

 70.88802 491.6699 

 70.89364 491.6699 

 70.89925 491.6699 

 70.90488 491.6699 

NASA/TM—2013-218094 F–36
 70.91049 491.6699 

 70.91611 491.6699 

 70.92173 491.6699 

 70.92735 491.6699 

 70.93296 491.6699 

 70.93858 491.6699 

 70.94420 491.6699 

 70.94982 491.6699 

 70.95544 491.6699 

 70.96105 491.6699 

 70.96667 491.6699 

 70.97229 491.6699 

 70.97791 491.6699 

 70.98353 491.6699 

 70.98914 491.6699 

 70.99476 491.6699 

 71.00038 491.6699 

 71.00600 491.6699 

 71.01161 491.6699 

 71.01723 491.6699 

 71.02285 491.6699 

 71.02847 491.6699 

 71.03409 491.6699 

 71.03970 491.6699 

 71.04532 491.6699 

 71.05094 491.6699 

 71.05656 491.6699 

 71.06217 491.6699 

 71.06779 491.6699 

 71.07341 491.6699 

 71.07903 491.6699 

 71.08465 491.6699 

 71.09026 491.6699 

 71.09588 491.6699 

 71.10150 491.6699 

 71.10712 491.6699 

 71.11273 491.6699 

 71.11835 491.6699 

 71.12397 491.6699 

 71.12959 491.6699 

 71.13521 491.6699 

 71.14082 491.6699 

 71.14645 491.6699 

 71.15206 491.6699 

 71.15768 491.6699 

 71.16330 491.6699 

 71.16891 491.6699 

 71.17453 491.6699 

 71.18015 491.6699 

 71.18577 491.6699 

 71.19138 491.6699 

 71.19701 491.6699 

 71.20262 491.6699 

 71.20824 491.6699 

 71.21386 491.6699 

 71.21947 491.6699 

 71.22509 491.6699 

 71.23071 491.6699 

 71.24777 491.6699 

 71.26463 491.6699 

 71.28149 491.6699 

 71.29835 491.6699 

 71.31521 491.6699 

NASA/TM—2013-218094 F–37
 71.33207 491.6699 

 71.34892 491.6699 

 71.36578 491.6699 

 71.38264 491.6699 

 71.39950 491.6699 

 71.41636 491.6699 

 71.43322 491.6699 

 71.45007 491.6699 

 71.46693 491.6699 

 71.48379 491.6699 

 71.50065 491.6699 

 71.51751 491.6699 

 71.53436 491.6699 

 71.55122 491.6699 

 71.56808 491.6699 

 71.58494 491.6699 

 71.60180 491.6699 

 71.61866 491.6699 

 71.63551 491.6699 

 71.65237 491.6699 

 71.66924 491.6699 

 71.68609 491.6699 

 71.70295 491.6699 

 71.71980 491.6699 

 71.73666 491.6699 

 71.75352 491.6699 

 71.77038 491.6699 

 71.78724 491.6699 

 71.80410 491.6699 

 71.82095 491.6699 

 71.83781 491.6699 

 71.85468 491.6699 

 71.87153 491.6699 

 71.88839 491.6699 

 71.90525 491.6699 

 71.92210 491.6699 

 71.93896 491.6699 

 71.95583 491.6699 

 71.97268 491.6699 

 71.98954 491.6699 

 72.00639 491.6699 

 72.02325 491.6699 

 72.04012 491.6699 

 72.05697 491.6699 

 72.07383 491.6699 

 72.09069 491.6699 

 72.10754 491.6699 

 72.12440 491.6699 

 72.14127 491.6699 

 72.15812 491.6699 

 72.17498 491.6699 

 72.19184 491.6699 

 72.20869 491.6699 

 72.22556 491.6699 

 72.24242 491.6699 

 72.25927 491.6699 

 72.27613 491.6699 

 72.29298 491.6699 

 72.30984 491.6699 

 72.32671 491.6699 

 72.34356 491.6699 

 72.36042 491.6699 

 72.37728 491.6699 

NASA/TM—2013-218094 F–38
 72.39413 491.6699 

 72.41100 491.6699 

 72.42786 491.6699 

 72.44471 491.6699 

 72.46157 491.6699 

 72.47843 491.7829 

 72.49529 492.6719 

 72.51215 493.4771 

 72.52900 494.2052 

 72.54586 494.8625 

 72.56272 495.4550 

 72.57957 495.9886 

 72.59644 496.4685 

 72.61330 496.8998 

 72.63015 497.2871 

 72.64701 497.6347 

 72.66387 497.9467 

 72.68073 498.2264 

 72.69759 498.4773 

 72.71445 498.7023 

 72.73130 498.9043 

 72.74816 499.0855 

 72.76502 499.2484 

 72.78188 499.3947 

 72.79874 499.5264 

 72.81559 499.6451 

 72.83245 499.7521 

 72.84931 499.8489 

 72.86617 499.9366 

 72.88303 500.0161 

 72.89989 500.0884 

 72.91674 500.1544 

 72.93360 500.2147 

 72.93916 500.2484 

 72.94455 500.3764 

 72.94995 500.5193 

 72.95535 500.6556 

 72.96074 500.7869 

 72.96614 500.9130 

 72.97153 501.0342 

 72.97694 501.1508 

 72.98233 501.2628 

 72.98773 501.3705 

 72.99313 501.4739 

 72.99852 501.5733 

 73.00392 501.6688 

 73.00932 501.7604 

 73.01472 501.8485 

 73.02011 501.9331 

 73.02551 502.0143 

 73.03091 502.0923 

 73.03630 502.1673 

 73.04170 502.2392 

 73.04710 502.3082 

 73.05250 502.3745 

 73.05789 502.4381 

 73.06329 502.4992 

 73.06869 502.5578 

 73.07408 502.6141 

 73.07948 502.6681 

 73.08488 502.7199 

 73.09028 502.7696 

 73.09567 502.8173 

NASA/TM—2013-218094 F–39
 73.10107 502.8631 

 73.10647 502.9070 

 73.11187 502.9492 

 73.11726 502.9896 

 73.12266 503.0284 

 73.12806 503.0656 

 73.13345 503.1013 

 73.13885 503.1356 

 73.14425 503.1685 

 73.14965 503.2000 

 73.15504 503.2303 

 73.16044 503.2594 

 73.16584 503.2872 

 73.17123 503.3140 

 73.17664 503.3396 

 73.18203 503.3642 

 73.18743 503.3878 

 73.19283 503.4105 

 73.19822 503.4323 

 73.20362 503.4532 

 73.20901 503.4732 

 73.21442 503.4924 

 73.21981 503.5109 

 73.22521 503.5286 

 73.23061 503.5456 

 73.23600 503.5619 

 73.24140 503.5775 

 73.24680 503.5926 

 73.25220 503.6070 

 73.25759 503.6208 

 73.26299 503.6342 

 73.26839 503.6469 

 73.27378 503.6592 

 73.27918 503.6710 

 73.28458 503.6823 

 73.28998 503.6932 

 73.29537 503.7036 

 73.30077 503.7137 

 73.30617 503.7234 

 73.31156 503.7326 

 73.31696 503.7416 

 73.32236 503.7502 

 73.32776 503.7584 

 73.33315 503.7664 

 73.33855 503.7740 

 73.34395 503.7814 

 73.34934 503.7885 

 73.35474 503.7953 

 73.36014 503.8018 

 73.36554 503.8082 

 73.37093 503.8143 

 73.37634 503.8202 

 73.38173 503.8258 

 73.38712 503.8313 

 73.39252 503.8366 

 73.39792 503.8417 

 73.40332 503.8466 

 73.40871 503.8513 

 73.41412 503.8559 

 73.41951 503.8603 

 73.42491 503.8646 

 73.43031 503.8687 

 73.43570 503.8727 

NASA/TM—2013-218094 F–40
 73.44110 503.8766 

 73.44650 503.8803 

 73.45190 503.8839 

 73.45729 503.8875 

 73.46269 503.8908 

 73.46809 503.8941 

 73.47348 503.8973 

 73.47888 503.9004 

 73.49987 503.9085 

 73.52092 503.9265 

 73.54196 503.9482 

 73.56301 503.9716 

 73.58405 503.9968 

 73.60509 504.0232 

 73.62614 504.0508 

 73.64719 504.0793 

 73.66823 504.1085 

 73.68928 504.1383 

 73.71032 504.1686 

 73.73136 504.1994 

 73.75241 504.2305 

 73.77345 504.2619 

 73.79450 504.2935 

 73.81554 504.3252 

 73.83659 504.3571 

 73.85764 504.3891 

 73.87868 504.4213 

 73.89972 504.4535 

 73.92077 504.4857 

 73.94181 504.5181 

 73.96285 504.5505 

 73.98390 504.5829 

 74.00494 504.6153 

 74.02599 504.6477 

 74.04704 504.6801 

 74.06808 504.7125 

 74.08913 504.7449 

 74.11017 504.7773 

 74.13121 504.8098 

 74.15226 504.8422 

 74.17330 504.8746 

 74.19435 504.9070 

 74.21539 504.9393 

 74.23643 504.9717 

 74.25748 505.0040 

 74.27853 505.0363 

 74.29957 505.0686 

 74.32062 505.1010 

 74.34166 505.1332 

 74.36270 505.1654 

 74.38375 505.1977 

 74.40479 505.2299 

 74.42584 505.2621 

 74.44688 505.2943 

 74.46793 505.3265 

 74.48898 505.3586 

 74.51002 505.3907 

 74.53106 505.4229 

 74.55211 505.4550 

 74.57315 505.4871 

 74.59419 505.5192 

 74.61524 505.5512 

 74.63628 505.5833 

NASA/TM—2013-218094 F–41
 74.65733 505.6153 

 74.67838 505.6473 

 74.69942 505.6793 

 74.72047 505.7112 

 74.74151 505.7432 

 74.76255 505.7751 

 74.78360 505.8070 

 74.80464 505.8390 

 74.82569 505.8708 

 74.84673 505.9027 

 74.86777 505.9345 

 74.88882 505.9664 

 74.90987 505.9982 

 74.93091 506.0300 

 74.95196 506.0618 

 74.97300 506.0936 

 74.99404 506.1253 

 75.01509 506.1570 

 75.03613 506.1888 

 75.05718 506.2205 

 75.07822 506.2521 

 75.09927 506.2838 

 75.12032 506.3155 

 75.14136 506.3471 

 75.16240 506.3788 

 75.18345 506.4103 

 75.20449 506.4419 

 75.22553 506.4735 

 75.24658 506.5051 

 75.26762 506.5366 

 75.28867 506.5682 

 75.30972 506.5997 

 75.33076 506.6312 

 75.35181 506.6628 

 75.37285 506.6942 

 75.39389 506.7257 

 75.41494 506.7571 

 75.43598 506.7885 

 75.45703 506.8200 

 75.47807 506.8514 

 75.49911 506.8828 

 75.52016 506.9142 

 75.54121 506.9456 

 75.56225 506.9769 

 75.58330 507.0083 

 75.60434 507.0396 

 75.60910 507.6951 

 75.61401 507.6783 

 75.61890 507.6619 

 75.62380 507.6459 

 75.62870 507.6303 

 75.63361 507.6151 

 75.63850 507.6003 

 75.64340 507.5858 

 75.64830 507.5716 

 75.65320 507.5578 

 75.65810 507.5443 

 75.66300 507.5310 

 75.66790 507.5180 

 75.67280 507.5053 

 75.67770 507.4930 

 75.68260 507.4808 

 75.68750 507.4689 

NASA/TM—2013-218094 F–42
 75.69240 507.4572 

 75.69730 507.4458 

 75.70220 507.4346 

 75.70710 507.4236 

 75.71200 507.4128 

 75.71690 507.4023 

 75.72180 507.3919 

 75.72670 507.3817 

 75.73160 507.3716 

 75.73650 507.3618 

 75.74140 507.3521 

 75.74630 507.3425 

 75.75120 507.3331 

 75.75610 507.3239 

 75.76099 507.3148 

 75.76590 507.3058 

 75.77080 507.2970 

 75.77570 507.2883 

 75.78059 507.2798 

 75.78550 507.2713 

 75.79040 507.2629 

 75.79530 507.2547 

 75.80019 507.2466 

 75.80509 507.2386 

 75.81000 507.2307 

 75.81490 507.2228 

 75.81979 507.2150 

 75.82469 507.2073 

 75.82960 507.1998 

 75.83450 507.1922 

 75.83939 507.1848 

 75.84429 507.1775 

 75.84919 507.1702 

 75.85410 507.1630 

 75.85899 507.1558 

 75.86389 507.1487 

 75.86879 507.1417 

 75.87370 507.1347 

 75.87859 507.1278 

 75.88349 507.1209 

 75.88839 507.1141 

 75.89329 507.1074 

 75.89819 507.1007 

 75.90309 507.0940 

 75.90799 507.0874 

 75.91289 507.0808 

 75.91779 507.0743 

 75.92269 507.0678 

 75.92759 507.0614 

 75.93249 507.0550 

 75.93739 507.0486 

 75.94229 507.0422 

 75.94719 507.0359 

 75.95209 507.0296 

 75.95699 507.0234 

 75.96189 507.0172 

 75.96679 507.0110 

 75.97169 507.0048 

 75.97659 506.9986 

 75.98149 506.9925 

 75.98639 506.9864 

 75.99129 506.9803 

 75.99619 506.9742 

NASA/TM—2013-218094 F–43
 76.00108 506.9682 

 76.00599 506.9621 

 76.01089 506.9561 

 76.01579 506.9502 

 76.02068 506.9442 

 76.02559 506.9382 

 76.03049 506.9323 

 76.03539 506.9263 

 76.04028 506.9204 

 76.04518 506.9145 

 76.05009 506.9086 

 76.05499 506.9027 

 76.05988 506.8968 

 76.06478 506.8909 

 76.06969 506.8851 

 76.07458 506.8792 

 76.07948 506.8734 

 76.08438 506.8676 

 76.08928 506.8618 

 76.09418 506.8560 

 76.09908 506.8501 

 76.10417 506.8448 

 76.10944 506.8402 

 76.11472 506.8359 

 76.12000 506.8318 

 76.12527 506.8279 

 76.13055 506.8243 

 76.13582 506.8209 

 76.14110 506.8177 

 76.14637 506.8148 

 76.15165 506.8120 

 76.15692 506.8094 

 76.16220 506.8069 

 76.16747 506.8047 

 76.17274 506.8027 

 76.17802 506.8008 

 76.18330 506.7991 

 76.18858 506.7975 

 76.19385 506.7961 

 76.19913 506.7948 

 76.20440 506.7937 

 76.20967 506.7926 

 76.21495 506.7917 

 76.22022 506.7910 

 76.22550 506.7903 

 76.23077 506.7898 

 76.23605 506.7893 

 76.24133 506.7890 

 76.24660 506.7888 

 76.25188 506.7887 

 76.25715 506.7887 

 76.26243 506.7887 

 76.26770 506.7889 

 76.27298 506.7891 

 76.27825 506.7894 

 76.28353 506.7898 

 76.28880 506.7903 

 76.29408 506.7909 

 76.29935 506.7915 

 76.30463 506.7921 

 76.30991 506.7929 

 76.31518 506.7937 

 76.32046 506.7946 

NASA/TM—2013-218094 F–44
 76.32573 506.7955 

 76.33101 506.7965 

 76.33628 506.7975 

 76.34155 506.7986 

 76.34683 506.7998 

 76.35210 506.8010 

 76.35738 506.8022 

 76.36266 506.8034 

 76.36794 506.8047 

 76.37321 506.8061 

 76.37848 506.8075 

 76.38376 506.8089 

 76.38903 506.8104 

 76.39431 506.8119 

 76.39958 506.8134 

 76.40486 506.8150 

 76.41013 506.8166 

 76.41541 506.8183 

 76.42068 506.8199 

 76.42596 506.8216 

 76.43124 506.8233 

 76.43651 506.8251 

 76.44179 506.8268 

 76.44706 506.8286 

 76.45234 506.8305 

 76.45761 506.8323 

 76.46288 506.8342 

 76.46816 506.8361 

 76.47343 506.8380 

 76.47871 506.8399 

 76.48399 506.8419 

 76.48927 506.8439 

 76.49454 506.8459 

 76.49982 506.8479 

 76.50509 506.8499 

 76.51036 506.8519 

 76.51564 506.8540 

 76.52091 506.8560 

 76.52619 506.8582 

 76.53146 506.8602 

 76.53674 506.8624 

 76.54202 506.8645 

 76.54729 506.8667 

 76.55257 506.8688 

 76.55784 506.8709 

 76.56312 506.8731 

 76.56839 506.8753 

 76.57367 506.8775 

 76.57894 506.8797 

 76.58422 506.8819 

 76.58949 506.8842 

 76.59476 506.8864 

 76.60004 506.8887 

 76.60532 506.8909 

 76.61060 506.8932 

 76.61587 506.8954 

 76.62115 506.8978 

 76.62642 506.9001 

 76.63169 506.9024 

 76.64760 506.9069 

 76.66342 506.9112 

 76.67924 506.9160 

 76.69508 506.9217 

NASA/TM—2013-218094 F–45
 76.71090 506.9280 

 76.72672 506.9348 

 76.74255 506.9421 

 76.75838 506.9498 

 76.77420 506.9579 

 76.79002 506.9662 

 76.80585 506.9749 

 76.82168 506.9839 

 76.83750 506.9931 

 76.85333 507.0024 

 76.86916 507.0119 

 76.88498 507.0216 

 76.90081 507.0313 

 76.91663 507.0412 

 76.93246 507.0512 

 76.94829 507.0613 

 76.96411 507.0714 

 76.97993 507.0815 

 76.99576 507.0918 

 77.01159 507.1021 

 77.02741 507.1124 

 77.04324 507.1227 

 77.05907 507.1331 

 77.07489 507.1435 

 77.09071 507.1538 

 77.10654 507.1642 

 77.12237 507.1747 

 77.13819 507.1851 

 77.15402 507.1955 

 77.16985 507.2060 

 77.18567 507.2164 

 77.20149 507.2268 

 77.21732 507.2373 

 77.23315 507.2477 

 77.24897 507.2581 

 77.26480 507.2686 

 77.28062 507.2789 

 77.29645 507.2893 

 77.31228 507.2997 

 77.32810 507.3101 

 77.34393 507.3205 

 77.35976 507.3308 

 77.37558 507.3412 

 77.39140 507.3515 

 77.40723 507.3618 

 77.42306 507.3721 

 77.43888 507.3825 

 77.45470 507.3928 

 77.47054 507.4031 

 77.48636 507.4133 

 77.50218 507.4236 

 77.51801 507.4339 

 77.53384 507.4442 

 77.54966 507.4544 

 77.56549 507.4646 

 77.58131 507.4748 

 77.59714 507.4850 

 77.61297 507.4952 

 77.62879 507.5054 

 77.64462 507.5156 

 77.66045 507.5257 

 77.67627 507.5359 

 77.69209 507.5460 

NASA/TM—2013-218094 F–46
 77.70792 507.5561 

 77.72375 507.5662 

 77.73957 507.5763 

 77.75539 507.5864 

 77.77122 507.5964 

 77.78705 507.6065 

 77.80287 507.6165 

 77.81870 507.6266 

 77.83453 507.6366 

 77.85035 507.6466 

 77.86618 507.6566 

 77.88200 507.6666 

 77.89783 507.6766 

 77.91365 507.6865 

 77.92948 507.6965 

 77.94530 507.7064 

 77.96113 507.7163 

 77.97696 507.7262 

 77.99278 507.7361 

 78.00861 507.7460 

 78.02444 507.7559 

 78.04026 507.7657 

 78.05608 507.7756 

 78.07191 507.7854 

 78.08774 507.7952 

 78.10356 507.8051 

 78.11939 507.8148 

 78.13522 507.8246 

 78.15104 507.8344 

 78.16686 507.8442 

 78.18269 507.8539 

 78.19852 507.8637 

 78.21434 507.8734 

 78.23017 507.8831 

VARIABLES = "x", "Air Static Temperature" 

ZONE T=" Static Air Temperature", I = 26.0 

 0.00000 416.9700 

 40.07360 458.9067 

 47.45212 467.8723 

 49.25944 462.0252 

 50.66056 473.7310 

 54.75445 475.5438 

 56.07415 476.0240 

 58.45746 485.5237 

 59.02501 485.0961 

 59.64998 489.7584 

 61.47612 490.6278 

 62.08459 491.3479 

 64.41123 500.0971 

 64.96181 500.1538 

 65.56672 503.5971 

 67.33422 504.7017 

 67.92163 505.4839 

 70.14417 513.0594 

 70.66892 513.6744 

 71.24777 515.8846 

 72.93916 516.7426 

 73.49987 515.5519 

 75.60910 521.0090 

 76.10417 517.9590 

 76.64760 519.1533 

 78.23017 517.4634 

NASA/TM—2013-218094 F–47
VARIABLES = "x", "y" 

ZONE T=" Location of Fan Leading Edge", I = 2.0 

 40.07360 400.0 

 40.07360 465.0 

NASA/TM—2013-218094 F–48
Appendix G: NPSS cycle analysis for the altitude cruise conditions at 35000 feet 

 5μm, ISA +18R

************************************************************************************************************************************ 

Date:05/10/13 Time:10:57:24 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 25/ 39/ 1/23 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 449.58 Stator 1 exit: 468.32 Stator 2 inlet: 490.14 Stator 2 exit: 497.71 

 Stator 3 inlet: 526.40 Stator 3 exit: 534.65 Stator 4 inlet: 561.45 Stator 4 exit: 569.32 

 Stator 5 inlet: 590.12 Stator 5 exit: 597.80 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.12 

Fan Bypass Relative Humidity 0.16 

LPC Inlet Relative Humidity 2.30 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 481.58 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 442.76 

Additional Water at LPC Exit 0.0024944 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 475.41 8115.0 0.5989 4859.81 5.3095 776.30 31.972 1.684 100.000 2819.2 2646.6 1840.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 475.41 5.170 462.10 -19.92 0.0000 1275.57 3.458 411.85 3891.4 0.7800 1.40081 0.0000308 475.40 0.015 0.0000

FS1 Inlet.Fl_O 475.41 5.170 462.10 -19.92 0.0000 1275.57 3.840 424.39 4168.2 0.6657 1.40081 0.0000308 475.40 0.015 0.0000

FS12 Splitter.Fl_02 400.06 5.167 462.10 -19.92 0.0000 1073.94 3.865 425.24 3531.8 0.6575 1.40081 0.0000308 400.05 0.012 0.0000

FS2 Splitter.Fl_01 75.35 5.167 462.10 -19.92 0.0000 202.27 4.451 442.76 830.5 0.4667 1.40081 0.0000308 75.35 0.002 0.0000

FS14 Fan.Fl_O 400.06 8.747 544.48 -0.16 0.0000 688.68 7.261 516.27 2606.7 0.5226 1.39985 0.0000308 400.05 0.012 0.0000

FS23 LPC.Fl_O 75.35 12.789 626.45 19.54 0.0000 95.15 11.232 603.69 412.6 0.4349 1.39816 0.0000308 75.35 0.002 0.0000

FS24 VaporIN.Fl_O 75.54 12.789 629.44 5.95 0.0000 95.62 11.211 606.28 412.6 0.4381 1.39773 0.0025252 75.35 0.190 0.0025

FS25 Bleed2.Fl_O 75.54 12.789 629.44 5.95 0.0000 95.62 11.211 606.28 412.6 0.4381 1.39773 0.0025252 75.35 0.190 0.0025

FS3 HPC.Fl_O 71.87 165.293 1382.63 194.27 0.0000 10.43 148.980 1345.30 49.7 0.3938 1.35654 0.0025252 71.69 0.181 0.0025

FS36 Bleed3.Fl_O 55.70 165.293 1382.63 194.27 0.0000 8.09 155.819 1361.32 49.3 0.2960 1.35654 0.0025252 55.56 0.140 0.0025

FS4 Burner.Fl_O 57.05 161.486 2819.23 164.33 0.0243 12.10 152.540 2783.42 74.6 0.3006 1.28422 0.0025252 55.56 0.140 0.0316

FS45 HPT.Fl_O 76.00 37.751 1849.17 -14.27 0.0181 55.87 33.999 1802.64 265.4 0.4006 1.32053 0.0025252 74.46 0.188 0.0244

FS49 LPT.Fl_O 76.89 8.687 1325.60 -154.42 0.0179 207.93 7.493 1275.85 860.2 0.4724 1.34763 0.0025252 75.35 0.190 0.0241

FS5 TEGV.Fl_O 76.89 8.687 1325.66 -154.42 0.0179 207.94 7.493 1275.91 860.2 0.4724 1.34763 0.0025252 75.35 0.190 0.0241

FS8 Core_Nozz.Fl_O 76.89 8.687 1325.79 -154.42 0.0179 207.95 4.646 1125.68 613.4 1.0000 1.34762 0.0025252 75.35 0.190 0.0241

FS17 FanDuctLkg.Fl_O 400.06 8.747 544.48 -0.16 0.0000 688.68 7.261 516.27 2606.7 0.5226 1.39985 0.0000308 400.05 0.012 0.0000

FS171 Bleed15.Fl_O 400.06 8.747 544.48 -0.16 0.0000 688.68 7.056 512.06 2481.9 0.5625 1.39985 0.0000308 400.05 0.012 0.0000

FS172 FanDuct.Fl_O 400.06 8.747 544.48 -0.16 0.0000 688.68 7.056 512.06 2481.9 0.5625 1.39985 0.0000308 400.05 0.012 0.0000

FS173 Byp_Nozz.Fl_O 400.06 8.747 544.48 -0.16 0.0000 688.68 4.619 453.63 2006.9 1.0000 1.39985 0.0000308 400.05 0.012 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.94 1.693 0.9109 4121.004 1.1783 0.9173 -11181.7 38.37 23.45

LPC 202.27 2.475 0.8306 4121.004 1.3557 0.8506 -4206.4 2.96 2.22

HPC 95.62 12.924 0.8588 10318.107 2.1966 0.8979 -19637.7 26.74 25.93

HPT 12.10 4.278 0.9118 214.076 1.3463 0.8911 19637.7 

LPT 55.87 4.346 0.9156 90.456 1.3915 0.8986 15388.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.81 1.677 0.9128 4081.711 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.14 2.728 0.8329 1.088 0.0000 1.2248 0.8538 0.9972 0.0003

HPC 86.96 12.363 0.8677 10043.034 13.4277 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.187 0.9118 1.287 4.1869 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.516 0.9224 1.018 3.5163 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–1
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3891.36 11470.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7797 1013.96 100.11 37.751

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8838 1013.96 100.11 8.687

TEGV 0.0000 0.4724 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 976.16 90.69 46.340

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1207.79 149.07 107.342

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 976.16 90.69 46.340

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1382.63 194.27 165.293

Splitter 5.3095 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 976.16 90.69 46.340

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11366.7 9073.8 19637.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 629.44 5.95 12.789

LP_Shaft 3889.8 20778.2 15388.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.6247 1382.63 194.27 161.486

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.5468 1382.63 194.27 90.710

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1382.63 194.27 165.293

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1382.63 194.27 165.293

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1382.63 194.27 165.293

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 544.48 -0.16 8.747

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 544.48 -0.16 8.747

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 544.48 -0.16 8.747

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 544.48 -0.16 8.747

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2819.23 0.9995 0.0230 1.34995 0.02430 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.512 0.9810 1.0000 0.9800 613.40 1.000 1589.9 4528.2

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1023.5 15057.6

NASA/TM—2013-218094 G–2
************************************************************************************************************************************ 

Date:05/10/13 Time:10:57:57 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 459.18 Stator 1 exit: 475.50 Stator 2 inlet: 495.41 Stator 2 exit: 503.84 

 Stator 3 inlet: 527.44 Stator 3 exit: 535.81 Stator 4 inlet: 558.04 Stator 4 exit: 565.66 

 Stator 5 inlet: 583.45 Stator 5 exit: 590.65 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.59 

Fan Bypass Relative Humidity 0.24 

LPC Inlet Relative Humidity 1.84 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 412.05 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.64 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 447.94 

Additional Water at LPC Exit 0.0031004 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 439.10 6109.6 0.5930 3623.22 5.6163 776.30 26.730 1.342 75.600 2550.2 2398.0 1660.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 439.10 5.170 462.10 -19.92 0.0000 1178.15 3.458 411.85 3594.2 0.7800 1.40081 0.0000308 439.09 0.014 0.0000

FS1 Inlet.Fl_O 439.10 5.170 462.10 -19.92 0.0000 1178.15 4.119 433.00 4168.2 0.5790 1.40081 0.0000308 439.09 0.014 0.0000

FS12 Splitter.Fl_02 372.74 5.167 462.10 -19.92 0.0000 1000.58 4.110 432.79 3531.8 0.5812 1.40081 0.0000308 372.73 0.011 0.0000

FS2 Splitter.Fl_01 66.37 5.167 462.10 -19.92 0.0000 178.16 4.635 447.94 830.5 0.3970 1.40081 0.0000308 66.37 0.002 0.0000

FS14 Fan.Fl_O 372.74 8.047 530.89 -3.43 0.0000 688.70 6.680 503.37 2606.7 0.5226 1.40006 0.0000308 372.73 0.011 0.0000

FS23 LPC.Fl_O 66.37 12.409 613.63 16.45 0.0000 85.49 11.228 596.38 412.6 0.3809 1.39848 0.0000308 66.37 0.002 0.0000

FS24 VaporIN.Fl_O 66.57 12.409 617.41 -0.42 0.0000 86.02 11.208 599.78 412.6 0.3842 1.39795 0.0031313 66.37 0.208 0.0031

FS25 Bleed2.Fl_O 66.57 12.409 617.41 -0.42 0.0000 86.02 11.208 599.78 412.6 0.3842 1.39795 0.0031313 66.37 0.208 0.0031

FS3 HPC.Fl_O 63.34 138.194 1299.37 169.25 0.0000 10.66 123.862 1262.06 49.7 0.4037 1.36141 0.0031313 63.15 0.198 0.0031

FS36 Bleed3.Fl_O 49.09 138.194 1299.37 169.25 0.0000 8.26 129.894 1278.16 49.3 0.3028 1.36141 0.0031313 48.94 0.153 0.0031

FS4 Burner.Fl_O 50.10 135.011 2550.20 144.50 0.0206 12.09 127.512 2516.99 74.6 0.2992 1.29428 0.0031313 48.94 0.153 0.0278

FS45 HPT.Fl_O 66.80 31.395 1668.42 -17.41 0.0153 56.08 28.245 1625.05 265.4 0.4010 1.33048 0.0031313 65.59 0.205 0.0217

FS49 LPT.Fl_O 67.58 7.216 1189.32 -142.92 0.0152 208.42 6.220 1143.51 860.2 0.4719 1.35789 0.0031313 66.37 0.208 0.0215

FS5 TEGV.Fl_O 67.58 7.216 1189.39 -142.92 0.0152 208.42 6.220 1143.58 860.2 0.4719 1.35789 0.0031313 66.37 0.208 0.0215

FS8 Core_Nozz.Fl_O 67.58 7.216 1189.52 -142.92 0.0152 208.43 3.848 1005.77 613.4 1.0000 1.35788 0.0031313 66.37 0.208 0.0215

FS17 FanDuctLkg.Fl_O 372.74 8.047 530.89 -3.43 0.0000 688.70 6.680 503.37 2606.7 0.5226 1.40006 0.0000308 372.73 0.011 0.0000

FS171 Bleed15.Fl_O 372.74 8.047 530.89 -3.43 0.0000 688.70 6.491 499.26 2481.9 0.5625 1.40006 0.0000308 372.73 0.011 0.0000

FS172 FanDuct.Fl_O 372.74 8.047 530.89 -3.43 0.0000 688.70 6.491 499.26 2481.9 0.5625 1.40006 0.0000308 372.73 0.011 0.0000

FS173 Byp_Nozz.Fl_O 372.74 8.047 530.89 -3.43 0.0000 688.70 4.250 442.28 2006.9 1.0000 1.40006 0.0000308 372.73 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1000.58 1.557 0.9070 3844.865 1.1489 0.9127 -8698.1 62.23 29.30

LPC 178.16 2.401 0.8671 3844.865 1.3279 0.8823 -3415.4 3.99 3.15

HPC 86.02 11.137 0.8615 10038.885 2.1045 0.8982 -15593.4 33.66 32.34

HPT 12.09 4.300 0.9079 216.890 1.3559 0.8883 15593.4 

LPT 56.08 4.351 0.9115 88.848 1.4001 0.8942 12113.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1162.58 1.544 0.9089 3808.205 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.26 2.433 0.8208 1.016 0.0000 1.2436 0.9782 1.0564 0.0003

HPC 78.24 10.659 0.8704 9771.255 12.8223 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.209 0.9079 1.303 4.2089 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9182 0.999 3.5203 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–3
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.18 10594.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4499 964.65 84.41 31.395

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7789 964.65 84.41 7.216

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 930.43 75.93 40.081

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1140.44 128.53 90.395

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 930.43 75.93 40.081

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1299.37 169.25 138.194

Splitter 5.6163 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 930.43 75.93 40.081

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10952.8 7477.4 15593.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 617.41 -0.42 12.409

LP_Shaft 3629.1 17530.8 12113.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.6013 1299.37 169.25 135.011

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.6513 1299.37 169.25 75.743

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1299.37 169.25 138.194 

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1299.37 169.25 138.194

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1299.37 169.25 138.194

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 530.89 -3.43 8.047

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 530.89 -3.43 8.047

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 530.89 -3.43 8.047

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 530.89 -3.43 8.047

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2550.18 0.9995 0.0230 1.00645 0.02057 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.087 0.9813 1.0000 0.9800 613.40 1.000 1508.4 3407.2

Byp_Nozz 2.327 0.9815 1.0000 0.9800 2006.86 1.000 1010.7 13297.3

NASA/TM—2013-218094 G–4
************************************************************************************************************************************ 

Date:05/10/13 Time:10:58:30 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 460.10 Stator 1 exit: 476.18 Stator 2 inlet: 495.88 Stator 2 exit: 504.33 

 Stator 3 inlet: 527.46 Stator 3 exit: 535.82 Stator 4 inlet: 557.60 Stator 4 exit: 565.18 

 Stator 5 inlet: 582.66 Stator 5 exit: 589.81 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.47 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 1.80 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 403.58 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.66 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.52 

Additional Water at LPC Exit 0.0032020 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 434.86 5882.0 0.5936 3491.78 5.6684 776.30 26.108 1.304 72.700 2520.7 2370.8 1641.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 434.86 5.170 462.10 -19.92 0.0000 1166.77 3.458 411.85 3559.4 0.7800 1.40081 0.0000308 434.85 0.013 0.0000

FS1 Inlet.Fl_O 434.86 5.170 462.10 -19.92 0.0000 1166.77 4.147 433.83 4168.2 0.5701 1.40081 0.0000308 434.85 0.013 0.0000

FS12 Splitter.Fl_02 369.65 5.167 462.10 -19.92 0.0000 992.29 4.134 433.51 3531.8 0.5735 1.40081 0.0000308 369.64 0.011 0.0000

FS2 Splitter.Fl_01 65.21 5.167 462.10 -19.92 0.0000 175.06 4.656 448.52 830.5 0.3886 1.40081 0.0000308 65.21 0.002 0.0000

FS14 Fan.Fl_O 369.65 7.968 529.26 -3.82 0.0000 688.70 6.614 501.83 2606.7 0.5226 1.40008 0.0000308 369.64 0.011 0.0000

FS23 LPC.Fl_O 65.21 12.337 612.22 16.11 0.0000 84.40 11.196 595.52 412.6 0.3750 1.39852 0.0000308 65.21 0.002 0.0000

FS24 VaporIN.Fl_O 65.42 12.337 616.12 -1.31 0.0000 84.94 11.177 599.04 412.6 0.3784 1.39796 0.0032329 65.21 0.211 0.0032

FS25 Bleed2.Fl_O 65.42 12.337 616.12 -1.31 0.0000 84.94 11.177 599.04 412.6 0.3784 1.39796 0.0032329 65.21 0.211 0.0032

FS3 HPC.Fl_O 62.25 134.976 1290.20 166.31 0.0000 10.69 120.894 1252.88 49.7 0.4049 1.36195 0.0032329 62.05 0.201 0.0032

FS36 Bleed3.Fl_O 48.24 134.976 1290.20 166.31 0.0000 8.28 126.823 1268.99 49.3 0.3036 1.36195 0.0032329 48.09 0.155 0.0032

FS4 Burner.Fl_O 49.21 131.868 2520.75 142.11 0.0202 12.09 124.542 2487.82 74.6 0.2991 1.29540 0.0032329 48.09 0.155 0.0275

FS45 HPT.Fl_O 65.63 30.645 1648.68 -17.96 0.0151 56.11 27.566 1605.67 265.4 0.4011 1.33163 0.0032329 64.45 0.208 0.0214

FS49 LPT.Fl_O 66.39 7.043 1174.70 -141.85 0.0149 208.47 6.070 1129.33 860.2 0.4719 1.35901 0.0032329 65.21 0.211 0.0212

FS5 TEGV.Fl_O 66.39 7.043 1174.77 -141.85 0.0149 208.48 6.070 1129.39 860.2 0.4719 1.35900 0.0032329 65.21 0.211 0.0212

FS8 Core_Nozz.Fl_O 66.39 7.043 1174.90 -141.85 0.0149 208.49 3.754 992.96 613.4 1.0000 1.35899 0.0032329 65.21 0.211 0.0212

FS17 FanDuctLkg.Fl_O 369.65 7.968 529.26 -3.82 0.0000 688.70 6.614 501.83 2606.7 0.5226 1.40008 0.0000308 369.64 0.011 0.0000

FS171 Bleed15.Fl_O 369.65 7.968 529.26 -3.82 0.0000 688.70 6.427 497.73 2481.9 0.5625 1.40008 0.0000308 369.64 0.011 0.0000

FS172 FanDuct.Fl_O 369.65 7.968 529.26 -3.82 0.0000 688.70 6.427 497.73 2481.9 0.5625 1.40008 0.0000308 369.64 0.011 0.0000

FS173 Byp_Nozz.Fl_O 369.65 7.968 529.26 -3.82 0.0000 688.70 4.208 440.92 2006.9 1.0000 1.40008 0.0000308 369.64 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 992.29 1.542 0.9070 3813.867 1.1453 0.9125 -8421.9 67.00 30.02

LPC 175.06 2.387 0.8688 3813.867 1.3249 0.8837 -3324.5 4.27 3.36

HPC 84.94 10.941 0.8615 10008.285 2.0941 0.8981 -15138.7 34.50 33.12

HPT 12.09 4.303 0.9073 217.262 1.3571 0.8881 15138.7 

LPT 56.11 4.351 0.9108 88.658 1.4008 0.8933 11746.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.95 1.530 0.9089 3777.502 0.0584 0.8607 1.0235 0.9980 0.9905

LPC 141.26 2.401 0.8202 1.007 0.0000 1.2391 0.9905 1.0592 0.0003

HPC 77.25 10.472 0.8704 9741.471 12.7535 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.212 0.9073 1.306 4.2116 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9176 0.997 3.5203 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–5
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3559.44 10492.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4075 959.25 82.50 30.645

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7654 959.25 82.50 7.043

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.42 74.12 39.318

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1133.04 126.08 88.373

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.42 74.12 39.318

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1290.20 166.31 134.976

Splitter 5.6684 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.42 74.12 39.318

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10908.1 7289.1 15138.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 616.12 -1.31 12.337

LP_Shaft 3599.9 17137.8 11746.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4698 1290.20 166.31 131.868

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5362 1290.20 166.31 73.968

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1290.20 166.31 134.976

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1290.20 166.31 134.976

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1290.20 166.31 134.976

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.26 -3.82 7.968

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.26 -3.82 7.968

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.26 -3.82 7.968

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.26 -3.82 7.968

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2520.72 0.9995 0.0230 0.96994 0.02017 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.037 0.9811 1.0000 0.9800 613.40 1.000 1499.3 3275.7

Byp_Nozz 2.304 0.9815 1.0000 0.9800 2006.86 1.000 1009.1 13098.8

NASA/TM—2013-218094 G–6
************************************************************************************************************************************ 

Date:05/10/13 Time:10:59:04 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 460.95 Stator 1 exit: 476.77 Stator 2 inlet: 496.25 Stator 2 exit: 504.70 

 Stator 3 inlet: 527.37 Stator 3 exit: 535.69 Stator 4 inlet: 557.03 Stator 4 exit: 564.57 

 Stator 5 inlet: 581.74 Stator 5 exit: 588.81 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.37 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 1.76 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 395.28 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.68 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 449.07 

Additional Water at LPC Exit 0.0032874 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 430.80 5664.3 0.5943 3366.42 5.7242 776.30 25.501 1.267 69.900 2492.3 2344.6 1622.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 430.80 5.170 462.10 -19.92 0.0000 1155.86 3.458 411.85 3526.2 0.7800 1.40081 0.0000308 430.78 0.013 0.0000

FS1 Inlet.Fl_O 430.80 5.170 462.10 -19.92 0.0000 1155.86 4.172 434.60 4168.2 0.5618 1.40081 0.0000308 430.78 0.013 0.0000

FS12 Splitter.Fl_02 366.73 5.167 462.10 -19.92 0.0000 984.46 4.156 434.18 3531.8 0.5664 1.40081 0.0000308 366.72 0.011 0.0000

FS2 Splitter.Fl_01 64.07 5.167 462.10 -19.92 0.0000 171.98 4.676 449.07 830.5 0.3804 1.40081 0.0000308 64.06 0.002 0.0000

FS14 Fan.Fl_O 366.73 7.893 527.69 -4.19 0.0000 688.70 6.552 500.34 2606.7 0.5226 1.40010 0.0000308 366.72 0.011 0.0000

FS23 LPC.Fl_O 64.07 12.253 610.66 15.74 0.0000 83.37 11.151 594.47 412.6 0.3696 1.39855 0.0000308 64.06 0.002 0.0000

FS24 VaporIN.Fl_O 64.28 12.253 614.68 -2.14 0.0000 83.92 11.132 598.11 412.6 0.3730 1.39799 0.0033183 64.06 0.213 0.0033

FS25 Bleed2.Fl_O 64.28 12.253 614.68 -2.14 0.0000 83.92 11.132 598.11 412.6 0.3730 1.39799 0.0033183 64.06 0.213 0.0033

FS3 HPC.Fl_O 61.16 131.839 1281.18 163.50 0.0000 10.71 118.009 1243.87 49.7 0.4060 1.36250 0.0033183 60.96 0.202 0.0033

FS36 Bleed3.Fl_O 47.40 131.839 1281.18 163.50 0.0000 8.30 123.834 1259.98 49.3 0.3043 1.36250 0.0033183 47.24 0.157 0.0033

FS4 Burner.Fl_O 48.33 128.803 2492.34 139.82 0.0198 12.09 121.646 2459.69 74.6 0.2989 1.29650 0.0033183 47.24 0.157 0.0271

FS45 HPT.Fl_O 64.46 29.914 1629.81 -18.47 0.0148 56.14 26.905 1587.15 265.4 0.4012 1.33274 0.0033183 63.32 0.210 0.0212

FS49 LPT.Fl_O 65.21 6.876 1160.77 -140.80 0.0146 208.52 5.925 1115.83 860.2 0.4718 1.36007 0.0033183 64.06 0.213 0.0210

FS5 TEGV.Fl_O 65.21 6.876 1160.84 -140.80 0.0146 208.52 5.925 1115.89 860.2 0.4718 1.36007 0.0033183 64.06 0.213 0.0210

FS8 Core_Nozz.Fl_O 65.21 6.876 1160.97 -140.80 0.0146 208.53 3.664 980.78 613.4 1.0000 1.36006 0.0033183 64.06 0.213 0.0210

FS17 FanDuctLkg.Fl_O 366.73 7.893 527.69 -4.19 0.0000 688.70 6.552 500.34 2606.7 0.5226 1.40010 0.0000308 366.72 0.011 0.0000

FS171 Bleed15.Fl_O 366.73 7.893 527.69 -4.19 0.0000 688.70 6.367 496.25 2481.9 0.5625 1.40010 0.0000308 366.72 0.011 0.0000

FS172 FanDuct.Fl_O 366.73 7.893 527.69 -4.19 0.0000 688.70 6.367 496.25 2481.9 0.5625 1.40010 0.0000308 366.72 0.011 0.0000

FS173 Byp_Nozz.Fl_O 366.73 7.893 527.69 -4.19 0.0000 688.70 4.168 439.61 2006.9 1.0000 1.40010 0.0000308 366.72 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 984.46 1.528 0.9073 3782.622 1.1419 0.9127 -8159.8 73.33 30.72

LPC 171.98 2.371 0.8701 3782.622 1.3215 0.8848 -3232.3 4.55 3.56

HPC 83.92 10.759 0.8615 9979.760 2.0843 0.8979 -14699.2 35.30 33.86

HPT 12.09 4.306 0.9067 217.619 1.3581 0.8875 14699.2 

LPT 56.14 4.351 0.9101 88.439 1.4015 0.8925 11392.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1143.84 1.515 0.9092 3746.555 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.25 2.369 0.8196 0.999 0.0000 1.2351 1.0017 1.0617 0.0003

HPC 76.33 10.300 0.8704 9713.706 12.6887 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.214 0.9067 1.308 4.2142 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9169 0.995 3.5201 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–7
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.18 10394.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3654 953.86 80.68 29.914

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7520 953.86 80.68 6.876

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 920.41 72.40 38.562

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1125.71 123.75 86.396

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 920.41 72.40 38.562

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1281.18 163.50 131.839

Splitter 5.7242 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 920.41 72.40 38.562

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10864.3 7106.0 14699.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 614.68 -2.14 12.253

LP_Shaft 3570.4 16758.5 11392.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3392 1281.18 163.50 128.803

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4220 1281.18 163.50 72.238

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1281.18 163.50 131.839

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1281.18 163.50 131.839

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1281.18 163.50 131.839

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 527.69 -4.19 7.893

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 527.69 -4.19 7.893

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 527.69 -4.19 7.893

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 527.69 -4.19 7.893

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2492.31 0.9995 0.0230 0.93512 0.01979 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.988 0.9808 1.0000 0.9800 613.40 1.000 1490.6 3147.7

Byp_Nozz 2.283 0.9815 1.0000 0.9800 2006.86 1.000 1007.6 12911.0

NASA/TM—2013-218094 G–8
5μm, ISA +36R

************************************************************************************************************************************ 

Date:05/10/13 Time:11:35:50 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 25/ 53/ 2/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 469.84 Stator 1 exit: 489.48 Stator 2 inlet: 512.47 Stator 2 exit: 520.65 

 Stator 3 inlet: 550.49 Stator 3 exit: 559.30 Stator 4 inlet: 587.15 Stator 4 exit: 595.57 

 Stator 5 inlet: 617.26 Stator 5 exit: 625.38 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.35 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 2.51 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 490.02 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.46 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 462.27 

Additional Water at LPC Exit 0.0048230 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 465.19 8140.7 0.6138 4996.55 5.3274 793.07 31.907 1.687 100.000 2926.9 2748.9 1918.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 465.19 5.170 482.28 -15.41 0.0000 1275.13 3.458 429.85 3890.2 0.7800 1.40064 0.0000871 465.15 0.041 0.0001

FS1 Inlet.Fl_O 465.19 5.170 482.28 -15.41 0.0000 1275.13 3.841 442.98 4168.2 0.6653 1.40064 0.0000871 465.15 0.041 0.0001

FS12 Splitter.Fl_02 391.67 5.167 482.28 -15.41 0.0000 1074.15 3.864 443.78 3531.8 0.6579 1.40064 0.0000871 391.64 0.034 0.0001

FS2 Splitter.Fl_01 73.52 5.167 482.28 -15.41 0.0000 201.63 4.456 462.27 830.5 0.4648 1.40064 0.0000871 73.51 0.006 0.0001

FS14 Fan.Fl_O 391.67 8.749 568.25 5.22 0.0000 688.62 7.263 538.83 2606.7 0.5227 1.39944 0.0000871 391.64 0.034 0.0001

FS23 LPC.Fl_O 73.52 12.916 655.07 26.11 0.0000 94.01 11.387 632.00 412.6 0.4284 1.39736 0.0000871 73.51 0.006 0.0001

FS24 VaporIN.Fl_O 73.88 12.916 660.53 -0.14 0.0000 94.85 11.349 636.69 412.6 0.4343 1.39650 0.0049101 73.51 0.361 0.0049

FS25 Bleed2.Fl_O 73.88 12.916 660.53 -0.14 0.0000 94.85 11.349 636.69 412.6 0.4343 1.39650 0.0049101 73.51 0.361 0.0049

FS3 HPC.Fl_O 70.29 164.951 1439.80 196.08 0.0000 10.43 148.634 1401.12 49.7 0.3948 1.35290 0.0049101 69.95 0.343 0.0049

FS36 Bleed3.Fl_O 54.48 164.951 1439.80 196.08 0.0000 8.09 155.477 1417.71 49.3 0.2967 1.35290 0.0049101 54.21 0.266 0.0049

FS4 Burner.Fl_O 55.86 161.152 2926.92 164.50 0.0256 12.10 152.235 2890.13 74.6 0.3013 1.27998 0.0049101 54.21 0.266 0.0354

FS45 HPT.Fl_O 74.40 37.752 1927.83 -21.33 0.0191 55.84 33.999 1879.76 265.4 0.4014 1.31629 0.0049101 72.65 0.357 0.0278

FS49 LPT.Fl_O 75.26 8.712 1386.35 -167.87 0.0189 207.55 7.518 1334.94 860.2 0.4726 1.34306 0.0049101 73.51 0.361 0.0275

FS5 TEGV.Fl_O 75.26 8.712 1386.41 -167.87 0.0189 207.56 7.518 1335.00 860.2 0.4726 1.34306 0.0049101 73.51 0.361 0.0275

FS8 Core_Nozz.Fl_O 75.26 8.712 1386.54 -167.87 0.0189 207.57 4.666 1179.53 613.4 1.0000 1.34305 0.0049101 73.51 0.361 0.0276

FS17 FanDuctLkg.Fl_O 391.67 8.749 568.25 5.22 0.0000 688.62 7.263 538.83 2606.7 0.5227 1.39944 0.0000871 391.64 0.034 0.0001

FS171 Bleed15.Fl_O 391.67 8.749 568.25 5.22 0.0000 688.62 7.058 534.44 2481.9 0.5626 1.39944 0.0000871 391.64 0.034 0.0001

FS172 FanDuct.Fl_O 391.67 8.749 568.25 5.22 0.0000 688.62 7.058 534.44 2481.9 0.5626 1.39944 0.0000871 391.64 0.034 0.0001

FS173 Byp_Nozz.Fl_O 391.67 8.749 568.25 5.22 0.0000 688.62 4.621 473.48 2006.9 1.0000 1.39944 0.0000871 391.64 0.034 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1074.15 1.693 0.9110 4121.876 1.1783 0.9173 -11431.7 38.28 23.43

LPC 201.63 2.500 0.8340 4121.876 1.3583 0.8538 -4318.8 2.96 2.22

HPC 94.85 12.771 0.8590 10286.780 2.1798 0.8977 -20011.4 27.32 26.49

HPT 12.10 4.269 0.9122 214.572 1.3415 0.8903 20011.4 

LPT 55.84 4.333 0.9169 90.524 1.3871 0.9007 15750.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1248.05 1.677 0.9128 4082.574 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.22 2.729 0.8330 1.089 0.0000 1.2204 0.8676 1.0013 0.0003

HPC 86.27 12.216 0.8679 10012.541 13.3720 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.178 0.9121 1.290 4.1781 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.507 0.9237 1.018 3.5069 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–9
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3890.21 11466.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7186 1058.91 97.97 37.752

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8643 1058.91 97.97 8.712

TEGV 0.0000 0.4726 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1019.81 88.16 46.364

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1259.22 148.98 107.178

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1019.81 88.16 46.364

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1439.80 196.08 164.951

Splitter 5.3274 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1019.81 88.16 46.364

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11608.6 9053.8 20011.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 660.53 -0.14 12.916

LP_Shaft 3974.6 20812.8 15750.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.4350 1439.80 196.08 161.152

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.3809 1439.80 196.08 90.567

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1439.80 196.08 164.951

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1439.80 196.08 164.951

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1439.80 196.08 164.951

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 568.25 5.22 8.749

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 568.25 5.22 8.749

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 568.25 5.22 8.749

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 568.25 5.22 8.749

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2926.92 0.9995 0.0230 1.38793 0.02560 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.519 0.9810 1.0000 0.9800 613.40 1.000 1626.0 4544.8

Byp_Nozz 2.530 0.9811 1.0000 0.9800 2006.86 1.000 1045.7 15062.6

NASA/TM—2013-218094 G–10
************************************************************************************************************************************ 

Date:05/10/13 Time:11:36:21 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 31/ 1/15 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 479.71 Stator 1 exit: 496.80 Stator 2 inlet: 517.72 Stator 2 exit: 526.64 

 Stator 3 inlet: 551.23 Stator 3 exit: 560.06 Stator 4 inlet: 583.21 Stator 4 exit: 591.31 

 Stator 5 inlet: 609.85 Stator 5 exit: 617.42 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.84 

Fan Bypass Relative Humidity 0.30 

LPC Inlet Relative Humidity 2.04 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 418.70 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.64 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.67 

Additional Water at LPC Exit 0.0057213 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 429.74 6136.7 0.6071 3725.42 5.6454 793.07 26.665 1.344 75.600 2652.3 2494.9 1733.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 429.74 5.170 482.28 -15.41 0.0000 1177.95 3.458 429.85 3593.7 0.7800 1.40064 0.0000871 429.70 0.037 0.0001

FS1 Inlet.Fl_O 429.74 5.170 482.28 -15.41 0.0000 1177.95 4.119 451.93 4168.2 0.5789 1.40064 0.0000871 429.70 0.037 0.0001

FS12 Splitter.Fl_02 365.07 5.167 482.28 -15.41 0.0000 1001.19 4.108 451.64 3531.8 0.5818 1.40064 0.0000871 365.04 0.032 0.0001

FS2 Splitter.Fl_01 64.67 5.167 482.28 -15.41 0.0000 177.35 4.641 467.67 830.5 0.3948 1.40064 0.0000871 64.66 0.006 0.0001

FS14 Fan.Fl_O 365.07 8.053 554.16 1.84 0.0000 688.65 6.685 525.46 2606.7 0.5226 1.39969 0.0000871 365.04 0.032 0.0001

FS23 LPC.Fl_O 64.67 12.480 641.48 22.83 0.0000 84.69 11.317 623.86 412.6 0.3767 1.39774 0.0000871 64.66 0.006 0.0001

FS24 VaporIN.Fl_O 65.04 12.480 648.09 -8.26 0.0000 85.61 11.283 629.79 412.6 0.3825 1.39675 0.0058084 64.66 0.376 0.0058

FS25 Bleed2.Fl_O 65.04 12.480 648.09 -8.26 0.0000 85.61 11.283 629.79 412.6 0.3825 1.39675 0.0058084 64.66 0.376 0.0058

FS3 HPC.Fl_O 61.88 137.851 1355.53 169.01 0.0000 10.67 123.512 1316.79 49.7 0.4048 1.35759 0.0058084 61.53 0.357 0.0058

FS36 Bleed3.Fl_O 47.96 137.851 1355.53 169.01 0.0000 8.27 129.550 1333.52 49.3 0.3036 1.35759 0.0058084 47.68 0.277 0.0058

FS4 Burner.Fl_O 48.99 134.677 2652.25 142.95 0.0217 12.09 127.197 2618.07 74.6 0.2999 1.29008 0.0058084 47.68 0.277 0.0317

FS45 HPT.Fl_O 65.31 31.373 1741.54 -26.03 0.0162 56.06 28.223 1696.70 265.4 0.4019 1.32609 0.0058084 63.90 0.371 0.0252

FS49 LPT.Fl_O 66.07 7.232 1245.33 -157.52 0.0160 208.04 6.236 1197.89 860.2 0.4721 1.35345 0.0058084 64.66 0.376 0.0250

FS5 TEGV.Fl_O 66.07 7.232 1245.40 -157.52 0.0160 208.04 6.236 1197.95 860.2 0.4721 1.35345 0.0058084 64.66 0.376 0.0250

FS8 Core_Nozz.Fl_O 66.07 7.232 1245.53 -157.52 0.0160 208.06 3.861 1055.02 613.4 1.0000 1.35344 0.0058084 64.66 0.376 0.0250

FS17 FanDuctLkg.Fl_O 365.07 8.053 554.16 1.84 0.0000 688.65 6.685 525.46 2606.7 0.5226 1.39969 0.0000871 365.04 0.032 0.0001

FS171 Bleed15.Fl_O 365.07 8.053 554.16 1.84 0.0000 688.65 6.496 521.17 2481.9 0.5626 1.39969 0.0000871 365.04 0.032 0.0001

FS172 FanDuct.Fl_O 365.07 8.053 554.16 1.84 0.0000 688.65 6.496 521.17 2481.9 0.5626 1.39969 0.0000871 365.04 0.032 0.0001

FS173 Byp_Nozz.Fl_O 365.07 8.053 554.16 1.84 0.0000 688.65 4.253 461.71 2006.9 1.0000 1.39969 0.0000871 365.04 0.032 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1001.19 1.558 0.9071 3847.235 1.1491 0.9127 -8907.1 62.06 29.24

LPC 177.35 2.415 0.8671 3847.235 1.3301 0.8824 -3499.0 3.97 3.14

HPC 85.61 11.046 0.8615 10026.648 2.0916 0.8980 -15916.1 34.17 32.82

HPT 12.09 4.293 0.9089 217.630 1.3518 0.8892 15916.2 

LPT 56.06 4.338 0.9132 88.896 1.3957 0.8964 12406.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1163.29 1.546 0.9089 3810.552 0.0590 0.8607 1.0235 0.9980 0.9905

LPC 143.42 2.435 0.8209 1.016 0.0000 1.2365 0.9861 1.0563 0.0003

HPC 77.86 10.573 0.8704 9759.344 12.7792 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.202 0.9089 1.308 4.2016 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.511 0.9200 1.000 3.5106 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–11
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3593.73 10592.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3933 1008.84 80.38 31.373

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7609 1008.84 80.38 7.232

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 973.34 71.51 40.062

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1191.00 126.47 90.210

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 973.34 71.51 40.062

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1355.53 169.01 137.851

Splitter 5.6454 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 973.34 71.51 40.062

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11208.0 7458.4 15916.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 648.09 -8.26 12.480

LP_Shaft 3709.8 17563.8 12406.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4259 1355.53 169.01 134.677

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4978 1355.53 169.01 75.587

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1355.53 169.01 137.851

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1355.53 169.01 137.851

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1355.53 169.01 137.851

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 554.16 1.84 8.053

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 554.16 1.84 8.053

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 554.16 1.84 8.053

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 554.16 1.84 8.053

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2652.24 0.9995 0.0230 1.03484 0.02170 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.091 0.9813 1.0000 0.9800 613.40 1.000 1543.8 3417.6

Byp_Nozz 2.329 0.9815 1.0000 0.9800 2006.86 1.000 1032.6 13311.9

NASA/TM—2013-218094 G–12
************************************************************************************************************************************ 

Date:05/10/13 Time:11:36:52 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 31/ 1/15 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 480.66 Stator 1 exit: 497.49 Stator 2 inlet: 518.18 Stator 2 exit: 527.12 

 Stator 3 inlet: 551.22 Stator 3 exit: 560.02 Stator 4 inlet: 582.71 Stator 4 exit: 590.77 

 Stator 5 inlet: 608.99 Stator 5 exit: 616.49 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.72 

Fan Bypass Relative Humidity 0.31 

LPC Inlet Relative Humidity 1.99 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 410.02 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.66 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 468.27 

Additional Water at LPC Exit 0.0058490 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 425.58 5909.0 0.6075 3589.93 5.6990 793.07 26.043 1.306 72.700 2622.0 2466.9 1713.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 425.58 5.170 482.28 -15.41 0.0000 1166.55 3.458 429.85 3559.0 0.7800 1.40064 0.0000871 425.54 0.037 0.0001

FS1 Inlet.Fl_O 425.58 5.170 482.28 -15.41 0.0000 1166.55 4.147 452.79 4168.2 0.5700 1.40064 0.0000871 425.54 0.037 0.0001

FS12 Splitter.Fl_02 362.05 5.167 482.28 -15.41 0.0000 992.91 4.132 452.39 3531.8 0.5741 1.40064 0.0000871 362.02 0.032 0.0001

FS2 Splitter.Fl_01 63.53 5.167 482.28 -15.41 0.0000 174.23 4.661 468.27 830.5 0.3864 1.40064 0.0000871 63.52 0.006 0.0001

FS14 Fan.Fl_O 362.05 7.974 552.47 1.43 0.0000 688.66 6.619 523.86 2606.7 0.5226 1.39972 0.0000871 362.02 0.032 0.0001

FS23 LPC.Fl_O 63.53 12.404 639.98 22.47 0.0000 83.61 11.281 622.92 412.6 0.3709 1.39779 0.0000871 63.52 0.006 0.0001

FS24 VaporIN.Fl_O 63.90 12.404 646.75 -9.31 0.0000 84.54 11.248 629.02 412.6 0.3768 1.39677 0.0059361 63.52 0.377 0.0059

FS25 Bleed2.Fl_O 63.90 12.404 646.75 -9.31 0.0000 84.54 11.248 629.02 412.6 0.3768 1.39677 0.0059361 63.52 0.377 0.0059

FS3 HPC.Fl_O 60.80 134.635 1346.14 165.85 0.0000 10.69 120.549 1307.39 49.7 0.4060 1.35813 0.0059361 60.44 0.359 0.0059

FS36 Bleed3.Fl_O 47.12 134.635 1346.14 165.85 0.0000 8.29 126.482 1324.13 49.3 0.3044 1.35813 0.0059361 46.84 0.278 0.0059

FS4 Burner.Fl_O 48.12 131.534 2622.01 140.37 0.0213 12.09 124.230 2588.10 74.6 0.2997 1.29121 0.0059361 46.84 0.278 0.0313

FS45 HPT.Fl_O 64.15 30.622 1721.32 -26.72 0.0159 56.08 27.542 1676.78 265.4 0.4020 1.32721 0.0059361 62.78 0.373 0.0250

FS49 LPT.Fl_O 64.90 7.059 1230.27 -156.54 0.0157 208.08 6.086 1183.27 860.2 0.4721 1.35458 0.0059361 63.52 0.377 0.0248

FS5 TEGV.Fl_O 64.90 7.059 1230.34 -156.54 0.0157 208.09 6.086 1183.34 860.2 0.4721 1.35458 0.0059361 63.52 0.377 0.0248

FS8 Core_Nozz.Fl_O 64.90 7.059 1230.47 -156.54 0.0157 208.10 3.768 1041.79 613.4 1.0000 1.35457 0.0059361 63.52 0.377 0.0248

FS17 FanDuctLkg.Fl_O 362.05 7.974 552.47 1.43 0.0000 688.66 6.619 523.86 2606.7 0.5226 1.39972 0.0000871 362.02 0.032 0.0001

FS171 Bleed15.Fl_O 362.05 7.974 552.47 1.43 0.0000 688.66 6.432 519.59 2481.9 0.5626 1.39972 0.0000871 362.02 0.032 0.0001

FS172 FanDuct.Fl_O 362.05 7.974 552.47 1.43 0.0000 688.66 6.432 519.59 2481.9 0.5626 1.39972 0.0000871 362.02 0.032 0.0001

FS173 Byp_Nozz.Fl_O 362.05 7.974 552.47 1.43 0.0000 688.66 4.211 460.30 2006.9 1.0000 1.39972 0.0000871 362.02 0.032 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 992.91 1.543 0.9070 3816.307 1.1456 0.9125 -8626.0 66.53 29.96

LPC 174.23 2.400 0.8685 3816.307 1.3270 0.8835 -3405.0 4.24 3.34

HPC 84.54 10.854 0.8615 9996.637 2.0814 0.8978 -15452.3 35.00 33.60

HPT 12.09 4.295 0.9084 218.001 1.3529 0.8888 15452.3 

LPT 56.08 4.338 0.9125 88.698 1.3965 0.8956 12031.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1153.67 1.531 0.9088 3779.919 0.0584 0.8607 1.0235 0.9980 0.9905

LPC 141.42 2.403 0.8202 1.008 0.0000 1.2319 0.9980 1.0588 0.0003

HPC 76.89 10.390 0.8705 9730.134 12.7112 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.204 0.9084 1.310 4.2041 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.511 0.9193 0.998 3.5106 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–13
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3558.95 10490.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 

HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3515 1003.29 78.27 30.622

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7476 1003.29 78.27 7.059

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 968.20 69.52 39.295

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1183.41 123.82 88.187

 

WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 968.20 69.52 39.295

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1346.14 165.85 134.635

Splitter 5.6990 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 968.20 69.52 39.295

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11162.9 7270.2 15452.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 646.75 -9.31 12.404

LP_Shaft 3680.0 17170.8 12031.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.2962 1346.14 165.85 131.534

 

HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.3843 1346.14 165.85 73.813

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1346.14 165.85 134.635

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1346.14 165.85 134.635

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1346.14 165.85 134.635

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 552.47 1.43 7.974

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 552.47 1.43 7.974

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 552.47 1.43 7.974

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 552.47 1.43 7.974

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2621.99 0.9995 0.0230 0.99720 0.02129 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.041 0.9811 1.0000 0.9800 613.40 1.000 1534.7 3285.5

Byp_Nozz 2.306 0.9815 1.0000 0.9800 2006.86 1.000 1031.0 13113.7

NASA/TM—2013-218094 G–14
************************************************************************************************************************************ 

Date:05/10/13 Time:11:37:23 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 481.53 Stator 1 exit: 498.10 Stator 2 inlet: 518.55 Stator 2 exit: 527.48 

 Stator 3 inlet: 551.10 Stator 3 exit: 559.86 Stator 4 inlet: 582.10 Stator 4 exit: 590.10 

 Stator 5 inlet: 607.99 Stator 5 exit: 615.43 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.62 

Fan Bypass Relative Humidity 0.33 

LPC Inlet Relative Humidity 1.95 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 401.52 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.68 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 468.84 

Additional Water at LPC Exit 0.0059723 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 421.59 5690.4 0.6082 3460.64 5.7560 793.07 25.434 1.269 69.900 2592.8 2439.9 1694.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 421.59 5.170 482.28 -15.41 0.0000 1155.62 3.458 429.85 3525.6 0.7800 1.40064 0.0000871 421.55 0.037 0.0001

FS1 Inlet.Fl_O 421.59 5.170 482.28 -15.41 0.0000 1155.62 4.173 453.60 4168.2 0.5617 1.40064 0.0000871 421.55 0.037 0.0001

FS12 Splitter.Fl_02 359.19 5.167 482.28 -15.41 0.0000 985.07 4.154 453.09 3531.8 0.5670 1.40064 0.0000871 359.16 0.031 0.0001

FS2 Splitter.Fl_01 62.40 5.167 482.28 -15.41 0.0000 171.14 4.681 468.84 830.5 0.3782 1.40064 0.0000871 62.40 0.005 0.0001

FS14 Fan.Fl_O 359.19 7.899 550.83 1.04 0.0000 688.66 6.557 522.30 2606.7 0.5226 1.39974 0.0000871 359.16 0.031 0.0001

FS23 LPC.Fl_O 62.40 12.317 638.37 22.09 0.0000 82.60 11.231 621.82 412.6 0.3656 1.39783 0.0000871 62.40 0.005 0.0001

FS24 VaporIN.Fl_O 62.77 12.317 645.30 -10.36 0.0000 83.55 11.199 628.09 412.6 0.3715 1.39679 0.0060594 62.40 0.378 0.0060

FS25 Bleed2.Fl_O 62.77 12.317 645.30 -10.36 0.0000 83.55 11.199 628.09 412.6 0.3715 1.39679 0.0060594 62.40 0.378 0.0060

FS3 HPC.Fl_O 59.73 131.488 1336.96 162.78 0.0000 10.72 117.652 1298.21 49.7 0.4072 1.35866 0.0060594 59.37 0.360 0.0060

FS36 Bleed3.Fl_O 46.29 131.488 1336.96 162.78 0.0000 8.31 123.483 1314.94 49.3 0.3052 1.35866 0.0060594 46.01 0.279 0.0060

FS4 Burner.Fl_O 47.25 128.460 2592.80 137.84 0.0209 12.09 121.323 2559.17 74.6 0.2996 1.29231 0.0060594 46.01 0.279 0.0310

FS45 HPT.Fl_O 63.00 29.887 1701.78 -27.43 0.0156 56.11 26.877 1657.60 265.4 0.4021 1.32831 0.0060594 61.67 0.374 0.0247

FS49 LPT.Fl_O 63.74 6.890 1215.78 -155.62 0.0154 208.13 5.940 1169.21 860.2 0.4720 1.35567 0.0060594 62.40 0.378 0.0245

FS5 TEGV.Fl_O 63.74 6.890 1215.85 -155.62 0.0154 208.14 5.940 1169.28 860.2 0.4720 1.35566 0.0060594 62.40 0.378 0.0245

FS8 Core_Nozz.Fl_O 63.74 6.890 1215.98 -155.62 0.0154 208.15 3.676 1029.07 613.4 1.0000 1.35565 0.0060594 62.40 0.378 0.0245

FS17 FanDuctLkg.Fl_O 359.19 7.899 550.83 1.04 0.0000 688.66 6.557 522.30 2606.7 0.5226 1.39974 0.0000871 359.16 0.031 0.0001

FS171 Bleed15.Fl_O 359.19 7.899 550.83 1.04 0.0000 688.66 6.372 518.04 2481.9 0.5626 1.39974 0.0000871 359.16 0.031 0.0001

FS172 FanDuct.Fl_O 359.19 7.899 550.83 1.04 0.0000 688.66 6.372 518.04 2481.9 0.5626 1.39974 0.0000871 359.16 0.031 0.0001

FS173 Byp_Nozz.Fl_O 359.19 7.899 550.83 1.04 0.0000 688.66 4.172 458.94 2006.9 1.0000 1.39974 0.0000871 359.16 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 985.07 1.529 0.9073 3785.224 1.1422 0.9127 -8357.7 72.77 30.66

LPC 171.14 2.384 0.8695 3785.224 1.3237 0.8843 -3310.5 4.53 3.55

HPC 83.55 10.676 0.8616 9968.416 2.0718 0.8977 -15004.3 35.81 34.34

HPT 12.09 4.298 0.9079 218.363 1.3539 0.8884 15004.3 

LPT 56.11 4.338 0.9119 88.479 1.3972 0.8947 11668.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1144.55 1.517 0.9091 3749.132 0.0579 0.8607 1.0235 0.9980 0.9905

LPC 139.41 2.371 0.8196 1.000 0.0000 1.2275 1.0090 1.0608 0.0003

HPC 75.98 10.220 0.8705 9702.665 12.6468 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.207 0.9078 1.312 4.2068 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.510 0.9186 0.995 3.5104 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–15
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3525.61 10392.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 

HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3101 997.80 76.21 29.887

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7345 997.80 76.21 6.890

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.09 67.55 38.534

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1175.95 121.22 86.203

 

WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.09 67.55 38.534

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1336.96 162.78 131.488

Splitter 5.7560 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.09 67.55 38.534

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11118.9 7087.4 15004.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 645.30 -10.36 12.317

LP_Shaft 3650.0 16789.8 11668.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.1676 1336.96 162.78 128.460

 

HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.2718 1336.96 162.78 72.076

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1336.96 162.78 131.488

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1336.96 162.78 131.488

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1336.96 162.78 131.488

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 550.83 1.04 7.899

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 550.83 1.04 7.899

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 550.83 1.04 7.899

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 550.83 1.04 7.899

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2592.78 0.9995 0.0230 0.96129 0.02089 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.992 0.9809 1.0000 0.9800 613.40 1.000 1525.9 3156.7

Byp_Nozz 2.284 0.9815 1.0000 0.9800 2006.86 1.000 1029.5 12925.7

NASA/TM—2013-218094 G–16
10μm, ISA +18R

************************************************************************************************************************************ 

Date:05/13/13 Time:07:00:59 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 26/ 40/ 1/24 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 449.14 Stator 1 exit: 467.80 Stator 2 inlet: 489.45 Stator 2 exit: 496.80 

 Stator 3 inlet: 525.56 Stator 3 exit: 533.65 Stator 4 inlet: 560.59 Stator 4 exit: 568.37 

 Stator 5 inlet: 589.23 Stator 5 exit: 596.81 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.11 

Fan Bypass Relative Humidity 0.16 

LPC Inlet Relative Humidity 2.31 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 483.02 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 442.65 

Additional Water at LPC Exit 0.0005921 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 475.55 8103.9 0.5996 4859.48 5.2966 776.30 31.984 1.684 100.000 2818.7 2645.8 1838.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 475.55 5.170 462.10 -19.92 0.0000 1275.94 3.458 411.85 3892.5 0.7800 1.40081 0.0000308 475.53 0.015 0.0000

FS1 Inlet.Fl_O 475.55 5.170 462.10 -19.92 0.0000 1275.94 3.839 424.35 4168.2 0.6661 1.40081 0.0000308 475.53 0.015 0.0000

FS12 Splitter.Fl_02 400.02 5.167 462.10 -19.92 0.0000 1073.83 3.865 425.25 3531.8 0.6574 1.40081 0.0000308 400.01 0.012 0.0000

FS2 Splitter.Fl_01 75.52 5.167 462.10 -19.92 0.0000 202.74 4.446 442.65 830.5 0.4682 1.40081 0.0000308 75.52 0.002 0.0000

FS14 Fan.Fl_O 400.02 8.746 544.46 -0.17 0.0000 688.68 7.260 516.25 2606.7 0.5226 1.39985 0.0000308 400.01 0.012 0.0000

FS23 LPC.Fl_O 75.52 12.696 625.54 19.32 0.0000 96.01 11.117 602.32 412.6 0.4399 1.39818 0.0000308 75.52 0.002 0.0000

FS24 VaporIN.Fl_O 75.57 12.696 626.30 16.10 0.0000 96.12 11.112 602.96 412.6 0.4407 1.39808 0.0006230 75.52 0.047 0.0006

FS25 Bleed2.Fl_O 75.57 12.696 626.30 16.10 0.0000 96.12 11.112 602.96 412.6 0.4407 1.39808 0.0006230 75.52 0.047 0.0006

FS3 HPC.Fl_O 71.90 165.353 1379.91 204.14 0.0000 10.42 149.090 1342.75 49.7 0.3930 1.35701 0.0006230 71.86 0.045 0.0006

FS36 Bleed3.Fl_O 55.73 165.353 1379.91 204.14 0.0000 8.08 155.906 1358.69 49.3 0.2955 1.35701 0.0006230 55.69 0.035 0.0006

FS4 Burner.Fl_O 57.08 161.545 2818.73 173.93 0.0242 12.10 152.607 2782.95 74.6 0.3004 1.28459 0.0006230 55.69 0.035 0.0297

FS45 HPT.Fl_O 76.03 37.754 1847.79 -4.33 0.0181 55.86 34.006 1801.32 265.4 0.4003 1.32089 0.0006230 74.64 0.046 0.0225

FS49 LPT.Fl_O 76.92 8.680 1323.99 -144.26 0.0179 208.07 7.487 1274.25 860.2 0.4723 1.34801 0.0006230 75.52 0.047 0.0223

FS5 TEGV.Fl_O 76.92 8.680 1324.05 -144.26 0.0179 208.07 7.487 1274.32 860.2 0.4723 1.34800 0.0006230 75.52 0.047 0.0223

FS8 Core_Nozz.Fl_O 76.92 8.680 1324.18 -144.26 0.0179 208.08 4.642 1124.14 613.4 1.0000 1.34799 0.0006230 75.52 0.047 0.0223

FS17 FanDuctLkg.Fl_O 400.02 8.746 544.46 -0.17 0.0000 688.68 7.260 516.25 2606.7 0.5226 1.39985 0.0000308 400.01 0.012 0.0000

FS171 Bleed15.Fl_O 400.02 8.746 544.46 -0.17 0.0000 688.68 7.055 512.04 2481.9 0.5625 1.39985 0.0000308 400.01 0.012 0.0000

FS172 FanDuct.Fl_O 400.02 8.746 544.46 -0.17 0.0000 688.68 7.055 512.04 2481.9 0.5625 1.39985 0.0000308 400.01 0.012 0.0000

FS173 Byp_Nozz.Fl_O 400.02 8.746 544.46 -0.17 0.0000 688.68 4.619 453.61 2006.9 1.0000 1.39985 0.0000308 400.01 0.012 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.83 1.693 0.9109 4120.603 1.1782 0.9173 -11178.1 38.40 23.46

LPC 202.74 2.457 0.8276 4120.603 1.3537 0.8478 -4193.0 2.96 2.22

HPC 96.12 13.024 0.8586 10338.629 2.2033 0.8979 -19617.5 26.39 25.59

HPT 12.10 4.279 0.9118 213.984 1.3467 0.8911 19617.5 

LPT 55.86 4.349 0.9155 90.481 1.3922 0.8986 15371.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.69 1.677 0.9128 4081.314 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.10 2.727 0.8329 1.088 0.0000 1.2279 0.8436 0.9936 0.0003

HPC 87.42 12.457 0.8675 10063.008 13.4618 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.188 0.9118 1.286 4.1881 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.519 0.9223 1.018 3.5192 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–17
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.49 11474.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7809 1011.00 110.12 37.754

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8842 1011.00 110.12 8.680

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 973.18 100.72 46.281

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1204.95 159.01 107.344

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 973.18 100.72 46.281

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1379.91 204.14 165.353

Splitter 5.2966 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 973.18 100.72 46.281

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11360.8 9069.2 19617.5 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 626.30 16.10 12.696

LP_Shaft 3889.4 20756.6 15371.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.6285 1379.91 204.14 161.545

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.5501 1379.91 204.14 90.736

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.91 204.14 165.353

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.91 204.14 165.353

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.91 204.14 165.353

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 544.46 -0.17 8.746

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 544.46 -0.17 8.746

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 544.46 -0.17 8.746

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 544.46 -0.17 8.746

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2818.73 0.9995 0.0230 1.34986 0.02424 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.510 0.9810 1.0000 0.9800 613.40 1.000 1588.1 4522.9

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1023.5 15055.1

NASA/TM—2013-218094 G–18
************************************************************************************************************************************ 

Date:05/13/13 Time:07:01:34 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 458.76 Stator 1 exit: 475.02 Stator 2 inlet: 494.78 Stator 2 exit: 503.08 

 Stator 3 inlet: 526.68 Stator 3 exit: 534.96 Stator 4 inlet: 557.27 Stator 4 exit: 564.84 

 Stator 5 inlet: 582.66 Stator 5 exit: 589.79 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.58 

Fan Bypass Relative Humidity 0.24 

LPC Inlet Relative Humidity 1.85 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 414.05 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 447.81 

Additional Water at LPC Exit 0.0007012 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 439.16 6089.2 0.5939 3616.23 5.5902 776.30 26.743 1.342 75.600 2544.9 2393.3 1656.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 439.16 5.170 462.10 -19.92 0.0000 1178.30 3.458 411.85 3594.6 0.7800 1.40081 0.0000308 439.15 0.014 0.0000

FS1 Inlet.Fl_O 439.16 5.170 462.10 -19.92 0.0000 1178.30 4.118 432.99 4168.2 0.5791 1.40081 0.0000308 439.15 0.014 0.0000

FS12 Splitter.Fl_02 372.52 5.167 462.10 -19.92 0.0000 1000.00 4.112 432.84 3531.8 0.5806 1.40081 0.0000308 372.51 0.011 0.0000

FS2 Splitter.Fl_01 66.64 5.167 462.10 -19.92 0.0000 178.88 4.630 447.81 830.5 0.3990 1.40081 0.0000308 66.64 0.002 0.0000

FS14 Fan.Fl_O 372.52 8.041 530.78 -3.45 0.0000 688.70 6.675 503.27 2606.7 0.5226 1.40006 0.0000308 372.51 0.011 0.0000

FS23 LPC.Fl_O 66.64 12.339 612.64 16.22 0.0000 86.26 11.141 595.06 412.6 0.3850 1.39851 0.0000308 66.64 0.002 0.0000

FS24 VaporIN.Fl_O 66.68 12.339 613.54 12.40 0.0000 86.38 11.136 595.86 412.6 0.3858 1.39838 0.0007320 66.64 0.049 0.0007

FS25 Bleed2.Fl_O 66.68 12.339 613.54 12.40 0.0000 86.38 11.136 595.86 412.6 0.3858 1.39838 0.0007320 66.64 0.049 0.0007

FS3 HPC.Fl_O 63.45 138.259 1294.64 181.41 0.0000 10.66 123.964 1257.53 49.7 0.4029 1.36209 0.0007320 63.40 0.046 0.0007

FS36 Bleed3.Fl_O 49.17 138.259 1294.64 181.41 0.0000 8.26 129.978 1273.53 49.3 0.3022 1.36209 0.0007320 49.14 0.036 0.0007

FS4 Burner.Fl_O 50.18 135.075 2544.87 156.49 0.0204 12.09 127.582 2511.72 74.6 0.2989 1.29491 0.0007320 49.14 0.036 0.0254

FS45 HPT.Fl_O 66.91 31.402 1663.71 -4.74 0.0153 56.08 28.257 1620.49 265.4 0.4006 1.33111 0.0007320 65.86 0.048 0.0192

FS49 LPT.Fl_O 67.69 7.208 1185.12 -129.76 0.0151 208.60 6.213 1139.40 860.2 0.4719 1.35854 0.0007320 66.64 0.049 0.0190

FS5 TEGV.Fl_O 67.69 7.208 1185.18 -129.76 0.0151 208.60 6.213 1139.46 860.2 0.4719 1.35854 0.0007320 66.64 0.049 0.0190

FS8 Core_Nozz.Fl_O 67.69 7.208 1185.32 -129.76 0.0151 208.62 3.843 1001.94 613.4 1.0000 1.35853 0.0007320 66.64 0.049 0.0190

FS17 FanDuctLkg.Fl_O 372.52 8.041 530.78 -3.45 0.0000 688.70 6.675 503.27 2606.7 0.5226 1.40006 0.0000308 372.51 0.011 0.0000

FS171 Bleed15.Fl_O 372.52 8.041 530.78 -3.45 0.0000 688.70 6.487 499.16 2481.9 0.5625 1.40006 0.0000308 372.51 0.011 0.0000

FS172 FanDuct.Fl_O 372.52 8.041 530.78 -3.45 0.0000 688.70 6.487 499.16 2481.9 0.5625 1.40006 0.0000308 372.51 0.011 0.0000

FS173 Byp_Nozz.Fl_O 372.52 8.041 530.78 -3.45 0.0000 688.70 4.247 442.19 2006.9 1.0000 1.40006 0.0000308 372.51 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1000.00 1.556 0.9070 3842.664 1.1486 0.9126 -8679.2 62.39 29.35

LPC 178.88 2.388 0.8665 3842.664 1.3258 0.8817 -3406.9 4.01 3.17

HPC 86.38 11.205 0.8614 10048.977 2.1101 0.8983 -15559.2 33.35 32.05

HPT 12.09 4.301 0.9079 216.653 1.3566 0.8882 15559.2 

LPT 56.08 4.356 0.9114 88.923 1.4011 0.8940 12086.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.90 1.543 0.9088 3806.024 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.12 2.430 0.8208 1.015 0.0000 1.2499 0.9703 1.0557 0.0003

HPC 78.56 10.724 0.8704 9781.078 12.8486 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.210 0.9079 1.302 4.2099 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.524 0.9182 1.000 3.5244 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–19
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.62 10596.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4540 960.29 96.90 31.402

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7802 960.29 96.90 7.208

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 926.10 88.45 40.042

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1135.87 140.85 90.409

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 926.10 88.45 40.042

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1294.64 181.41 138.259

Splitter 5.5902 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 926.10 88.45 40.042

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10929.4 7476.9 15559.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 613.54 12.40 12.339

LP_Shaft 3627.0 17501.2 12086.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.6141 1294.64 181.41 135.075

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.6625 1294.64 181.41 75.774

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1294.64 181.41 138.259

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1294.64 181.41 138.259

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1294.64 181.41 138.259

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 530.78 -3.45 8.041

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 530.78 -3.45 8.041

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 530.78 -3.45 8.041

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 530.78 -3.45 8.041

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2544.85 0.9995 0.0230 1.00451 0.02044 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.085 0.9813 1.0000 0.9800 613.40 1.000 1504.8 3401.9

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1010.6 13283.5

NASA/TM—2013-218094 G–20
************************************************************************************************************************************ 

Date:05/13/13 Time:07:02:31 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 29/ 57/ 2/26 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 459.69 Stator 1 exit: 475.70 Stator 2 inlet: 495.26 Stator 2 exit: 503.59 

 Stator 3 inlet: 526.72 Stator 3 exit: 534.99 Stator 4 inlet: 556.85 Stator 4 exit: 564.39 

 Stator 5 inlet: 581.90 Stator 5 exit: 588.97 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.46 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 1.81 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 405.65 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.38 

Additional Water at LPC Exit 0.0007169 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 434.92 5860.9 0.5944 3483.94 5.6404 776.30 26.121 1.304 72.700 2514.7 2364.8 1636.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 434.92 5.170 462.10 -19.92 0.0000 1166.92 3.458 411.85 3559.9 0.7800 1.40081 0.0000308 434.90 0.013 0.0000

FS1 Inlet.Fl_O 434.92 5.170 462.10 -19.92 0.0000 1166.92 4.146 433.82 4168.2 0.5702 1.40081 0.0000308 434.90 0.013 0.0000

FS12 Splitter.Fl_02 369.42 5.167 462.10 -19.92 0.0000 991.69 4.136 433.57 3531.8 0.5729 1.40081 0.0000308 369.41 0.011 0.0000

FS2 Splitter.Fl_01 65.50 5.167 462.10 -19.92 0.0000 175.82 4.651 448.38 830.5 0.3907 1.40081 0.0000308 65.49 0.002 0.0000

FS14 Fan.Fl_O 369.42 7.962 529.14 -3.85 0.0000 688.70 6.609 501.71 2606.7 0.5226 1.40008 0.0000308 369.41 0.011 0.0000

FS23 LPC.Fl_O 65.50 12.273 611.23 15.88 0.0000 85.14 11.116 594.22 412.6 0.3790 1.39854 0.0000308 65.49 0.002 0.0000

FS24 VaporIN.Fl_O 65.54 12.273 612.15 11.97 0.0000 85.26 11.111 595.04 412.6 0.3797 1.39842 0.0007477 65.49 0.049 0.0007

FS25 Bleed2.Fl_O 65.54 12.273 612.15 11.97 0.0000 85.26 11.111 595.04 412.6 0.3797 1.39842 0.0007477 65.49 0.049 0.0007

FS3 HPC.Fl_O 62.36 135.046 1285.16 178.88 0.0000 10.68 121.002 1248.06 49.7 0.4041 1.36267 0.0007477 62.32 0.047 0.0007

FS36 Bleed3.Fl_O 48.33 135.046 1285.16 178.88 0.0000 8.28 126.913 1264.06 49.3 0.3030 1.36267 0.0007477 48.30 0.036 0.0007

FS4 Burner.Fl_O 49.30 131.936 2514.71 154.51 0.0200 12.09 124.616 2481.86 74.6 0.2987 1.29608 0.0007477 48.30 0.036 0.0249

FS45 HPT.Fl_O 65.74 30.655 1643.61 -4.82 0.0150 56.11 27.581 1600.75 265.4 0.4006 1.33230 0.0007477 64.73 0.048 0.0189

FS49 LPT.Fl_O 66.51 7.036 1170.20 -128.19 0.0148 208.66 6.064 1124.92 860.2 0.4718 1.35969 0.0007477 65.49 0.049 0.0187

FS5 TEGV.Fl_O 66.51 7.036 1170.27 -128.19 0.0148 208.66 6.064 1124.99 860.2 0.4718 1.35969 0.0007477 65.49 0.049 0.0187

FS8 Core_Nozz.Fl_O 66.51 7.036 1170.40 -128.19 0.0148 208.67 3.750 988.88 613.4 1.0000 1.35968 0.0007477 65.49 0.049 0.0187

FS17 FanDuctLkg.Fl_O 369.42 7.962 529.14 -3.85 0.0000 688.70 6.609 501.71 2606.7 0.5226 1.40008 0.0000308 369.41 0.011 0.0000

FS171 Bleed15.Fl_O 369.42 7.962 529.14 -3.85 0.0000 688.70 6.423 497.62 2481.9 0.5625 1.40008 0.0000308 369.41 0.011 0.0000

FS172 FanDuct.Fl_O 369.42 7.962 529.14 -3.85 0.0000 688.70 6.423 497.62 2481.9 0.5625 1.40008 0.0000308 369.41 0.011 0.0000

FS173 Byp_Nozz.Fl_O 369.42 7.962 529.14 -3.85 0.0000 688.70 4.205 440.82 2006.9 1.0000 1.40008 0.0000308 369.41 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.69 1.541 0.9070 3811.543 1.1451 0.9125 -8401.7 67.45 30.07

LPC 175.82 2.375 0.8686 3811.543 1.3227 0.8835 -3317.0 4.29 3.37

HPC 85.26 11.004 0.8615 10017.646 2.0994 0.8982 -15101.9 34.20 32.84

HPT 12.09 4.304 0.9073 217.022 1.3577 0.8878 15101.9 

LPT 56.11 4.357 0.9107 88.741 1.4019 0.8932 11718.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.24 1.528 0.9089 3775.200 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.11 2.398 0.8201 1.007 0.0000 1.2459 0.9834 1.0591 0.0003

HPC 77.55 10.532 0.8704 9750.582 12.7785 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.212 0.9073 1.304 4.2124 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9175 0.998 3.5247 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–21
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3559.91 10493.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4120 954.68 95.42 30.655

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7668 954.68 95.42 7.036

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 920.90 87.08 39.283

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1128.21 138.82 88.392

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 920.90 87.08 39.283

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1285.16 178.88 135.046

Splitter 5.6404 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 920.90 87.08 39.283

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10883.0 7288.2 15101.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.15 11.97 12.273

LP_Shaft 3597.7 17107.8 11718.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4836 1285.16 178.88 131.936

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5483 1285.16 178.88 74.003

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1285.16 178.88 135.046

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1285.16 178.88 135.046

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1285.16 178.88 135.046

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.14 -3.85 7.962

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.14 -3.85 7.962

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.14 -3.85 7.962

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.14 -3.85 7.962

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2514.69 0.9995 0.0230 0.96776 0.02004 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.035 0.9811 1.0000 0.9800 613.40 1.000 1495.5 3270.5

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1009.0 13084.3

NASA/TM—2013-218094 G–22
************************************************************************************************************************************ 

Date:05/13/13 Time:07:03:22 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 38/ 52/ 1/36 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 460.53 Stator 1 exit: 476.29 Stator 2 inlet: 495.63 Stator 2 exit: 503.96 

 Stator 3 inlet: 526.63 Stator 3 exit: 534.86 Stator 4 inlet: 556.28 Stator 4 exit: 563.77 

 Stator 5 inlet: 580.96 Stator 5 exit: 587.97 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.36 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 1.77 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 397.39 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.93 

Additional Water at LPC Exit 0.0007329 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 430.85 5642.7 0.5952 3358.54 5.6945 776.30 25.516 1.267 69.900 2486.0 2338.4 1617.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 430.85 5.170 462.10 -19.92 0.0000 1156.02 3.458 411.85 3526.6 0.7800 1.40081 0.0000308 430.84 0.013 0.0000

FS1 Inlet.Fl_O 430.85 5.170 462.10 -19.92 0.0000 1156.02 4.172 434.59 4168.2 0.5619 1.40081 0.0000308 430.84 0.013 0.0000

FS12 Splitter.Fl_02 366.49 5.167 462.10 -19.92 0.0000 983.83 4.158 434.23 3531.8 0.5658 1.40081 0.0000308 366.48 0.011 0.0000

FS2 Splitter.Fl_01 64.36 5.167 462.10 -19.92 0.0000 172.77 4.671 448.93 830.5 0.3825 1.40081 0.0000308 64.36 0.002 0.0000

FS14 Fan.Fl_O 366.49 7.887 527.56 -4.22 0.0000 688.70 6.547 500.21 2606.7 0.5226 1.40011 0.0000308 366.48 0.011 0.0000

FS23 LPC.Fl_O 64.36 12.191 609.67 15.50 0.0000 84.12 11.072 593.17 412.6 0.3735 1.39858 0.0000308 64.36 0.002 0.0000

FS24 VaporIN.Fl_O 64.41 12.191 610.61 11.51 0.0000 84.24 11.067 594.02 412.6 0.3743 1.39845 0.0007638 64.36 0.049 0.0008

FS25 Bleed2.Fl_O 64.41 12.191 610.61 11.51 0.0000 84.24 11.067 594.02 412.6 0.3743 1.39845 0.0007638 64.36 0.049 0.0008

FS3 HPC.Fl_O 61.28 131.915 1275.96 176.42 0.0000 10.71 118.122 1238.88 49.7 0.4052 1.36324 0.0007638 61.24 0.047 0.0008

FS36 Bleed3.Fl_O 47.49 131.915 1275.96 176.42 0.0000 8.30 123.930 1254.88 49.3 0.3038 1.36324 0.0007638 47.46 0.036 0.0008

FS4 Burner.Fl_O 48.43 128.877 2485.98 152.56 0.0197 12.09 121.727 2453.40 74.6 0.2986 1.29720 0.0007638 47.46 0.036 0.0245

FS45 HPT.Fl_O 64.59 29.924 1624.40 -4.95 0.0147 56.13 26.921 1581.89 265.4 0.4006 1.33343 0.0007638 63.60 0.049 0.0186

FS49 LPT.Fl_O 65.34 6.869 1156.01 -126.74 0.0145 208.70 5.919 1111.17 860.2 0.4718 1.36079 0.0007638 64.36 0.049 0.0184

FS5 TEGV.Fl_O 65.34 6.869 1156.07 -126.74 0.0145 208.71 5.919 1111.23 860.2 0.4718 1.36078 0.0007638 64.36 0.049 0.0184

FS8 Core_Nozz.Fl_O 65.34 6.869 1156.21 -126.74 0.0145 208.72 3.659 976.47 613.4 1.0000 1.36077 0.0007638 64.36 0.049 0.0184

FS17 FanDuctLkg.Fl_O 366.49 7.887 527.56 -4.22 0.0000 688.70 6.547 500.21 2606.7 0.5226 1.40011 0.0000308 366.48 0.011 0.0000

FS171 Bleed15.Fl_O 366.49 7.887 527.56 -4.22 0.0000 688.70 6.362 496.13 2481.9 0.5625 1.40011 0.0000308 366.48 0.011 0.0000

FS172 FanDuct.Fl_O 366.49 7.887 527.56 -4.22 0.0000 688.70 6.362 496.13 2481.9 0.5625 1.40011 0.0000308 366.48 0.011 0.0000

FS173 Byp_Nozz.Fl_O 366.49 7.887 527.56 -4.22 0.0000 688.70 4.165 439.51 2006.9 1.0000 1.40011 0.0000308 366.48 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.83 1.526 0.9074 3779.983 1.1417 0.9127 -8138.6 73.89 30.77

LPC 172.77 2.359 0.8701 3779.983 1.3194 0.8847 -3225.3 4.57 3.57

HPC 84.24 10.821 0.8615 9988.985 2.0897 0.8980 -14662.7 34.99 33.57 

HPT 12.09 4.307 0.9067 217.374 1.3589 0.8875 14662.7 

LPT 56.13 4.357 0.9100 88.525 1.4026 0.8924 11363.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1143.11 1.514 0.9092 3743.941 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.08 2.366 0.8195 0.998 0.0000 1.2422 0.9946 1.0618 0.0003

HPC 76.62 10.358 0.8704 9722.686 12.7138 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.215 0.9067 1.306 4.2152 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9168 0.996 3.5246 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–23
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.65 10395.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3702 949.14 93.96 29.924

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7536 949.14 93.96 6.869

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 915.75 85.72 38.530

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1120.73 136.84 86.420

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 915.75 85.72 38.530

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1275.96 176.42 131.915

Splitter 5.6945 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 915.75 85.72 38.530

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10838.2 7105.4 14662.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 610.61 11.51 12.191

LP_Shaft 3567.9 16728.2 11363.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3539 1275.96 176.42 128.877

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4349 1275.96 176.42 72.276

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1275.96 176.42 131.915

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1275.96 176.42 131.915

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1275.96 176.42 131.915

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 527.56 -4.22 7.887

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 527.56 -4.22 7.887

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 527.56 -4.22 7.887

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 527.56 -4.22 7.887

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2485.96 0.9995 0.0230 0.93293 0.01966 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.986 0.9808 1.0000 0.9800 613.40 1.000 1486.6 3142.6

Byp_Nozz 2.281 0.9815 1.0000 0.9800 2006.86 1.000 1007.5 12895.9

NASA/TM—2013-218094 G–24
 10μm, ISA +36R

************************************************************************************************************************************ 

Date:05/13/13 Time:07:21:31 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 26/ 40/ 1/24 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 468.91 Stator 1 exit: 488.41 Stator 2 inlet: 511.07 Stator 2 exit: 518.82 

 Stator 3 inlet: 548.81 Stator 3 exit: 557.31 Stator 4 inlet: 585.38 Stator 4 exit: 593.55 

 Stator 5 inlet: 615.30 Stator 5 exit: 623.25 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.34 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 2.53 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 492.99 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 462.02 

Additional Water at LPC Exit 0.0008426 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 465.46 8117.3 0.6152 4994.10 5.3011 793.07 31.924 1.687 100.000 2926.1 2747.5 1915.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 465.46 5.170 482.28 -15.41 0.0000 1275.86 3.458 429.85 3892.4 0.7800 1.40064 0.0000871 465.42 0.041 0.0001

FS1 Inlet.Fl_O 465.46 5.170 482.28 -15.41 0.0000 1275.86 3.839 442.90 4168.2 0.6661 1.40064 0.0000871 465.42 0.041 0.0001

FS12 Splitter.Fl_02 391.59 5.167 482.28 -15.41 0.0000 1073.92 3.865 443.81 3531.8 0.6576 1.40064 0.0000871 391.55 0.034 0.0001

FS2 Splitter.Fl_01 73.87 5.167 482.28 -15.41 0.0000 202.58 4.448 462.02 830.5 0.4677 1.40064 0.0000871 73.86 0.006 0.0001

FS14 Fan.Fl_O 391.59 8.747 568.21 5.21 0.0000 688.62 7.261 538.79 2606.7 0.5227 1.39944 0.0000871 391.55 0.034 0.0001

FS23 LPC.Fl_O 73.87 12.732 653.08 25.63 0.0000 95.68 11.161 629.06 412.6 0.4381 1.39741 0.0000871 73.86 0.006 0.0001

FS24 VaporIN.Fl_O 73.93 12.732 654.09 21.04 0.0000 95.83 11.154 629.93 412.6 0.4392 1.39726 0.0009297 73.86 0.069 0.0009

FS25 Bleed2.Fl_O 73.93 12.732 654.09 21.04 0.0000 95.83 11.154 629.93 412.6 0.4392 1.39726 0.0009297 73.86 0.069 0.0009

FS3 HPC.Fl_O 70.35 165.042 1434.36 216.67 0.0000 10.42 148.825 1396.01 49.7 0.3932 1.35386 0.0009297 70.28 0.065 0.0009

FS36 Bleed3.Fl_O 54.52 165.042 1434.36 216.67 0.0000 8.07 155.622 1412.46 49.3 0.2957 1.35386 0.0009297 54.47 0.051 0.0009

FS4 Burner.Fl_O 55.90 161.241 2926.10 184.53 0.0255 12.10 152.342 2889.33 74.6 0.3008 1.28075 0.0009297 54.47 0.051 0.0315

FS45 HPT.Fl_O 74.45 37.751 1925.14 -0.59 0.0190 55.84 34.008 1877.19 265.4 0.4008 1.31704 0.0009297 73.00 0.068 0.0239

FS49 LPT.Fl_O 75.32 8.697 1383.15 -146.66 0.0188 207.83 7.504 1331.76 860.2 0.4725 1.34383 0.0009297 73.86 0.069 0.0236

FS5 TEGV.Fl_O 75.32 8.697 1383.21 -146.66 0.0188 207.83 7.504 1331.82 860.2 0.4725 1.34382 0.0009297 73.86 0.069 0.0236

FS8 Core_Nozz.Fl_O 75.32 8.697 1383.34 -146.66 0.0188 207.84 4.657 1176.42 613.4 1.0000 1.34381 0.0009297 73.86 0.069 0.0236

FS17 FanDuctLkg.Fl_O 391.59 8.747 568.21 5.21 0.0000 688.62 7.261 538.79 2606.7 0.5227 1.39944 0.0000871 391.55 0.034 0.0001

FS171 Bleed15.Fl_O 391.59 8.747 568.21 5.21 0.0000 688.62 7.056 534.40 2481.9 0.5626 1.39944 0.0000871 391.55 0.034 0.0001

FS172 FanDuct.Fl_O 391.59 8.747 568.21 5.21 0.0000 688.62 7.056 534.40 2481.9 0.5626 1.39944 0.0000871 391.55 0.034 0.0001 

FS173 Byp_Nozz.Fl_O 391.59 8.747 568.21 5.21 0.0000 688.62 4.620 473.45 2006.9 1.0000 1.39944 0.0000871 391.55 0.034 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.92 1.693 0.9109 4120.978 1.1782 0.9173 -11423.5 38.36 23.45

LPC 202.58 2.464 0.8288 4120.978 1.3542 0.8489 -4289.1 2.96 2.22

HPC 95.83 12.963 0.8587 10326.703 2.1929 0.8978 -19967.3 26.63 25.82

HPT 12.10 4.271 0.9122 214.382 1.3424 0.8901 19967.3 

LPT 55.84 4.341 0.9168 90.567 1.3884 0.9006 15712.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.78 1.677 0.9128 4081.685 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.14 2.728 0.8329 1.088 0.0000 1.2268 0.8474 0.9950 0.0003

HPC 87.16 12.399 0.8676 10051.400 13.4384 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1805 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.513 0.9236 1.019 3.5126 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–25
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.43 11473.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7207 1052.92 118.85 37.751

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8650 1052.92 118.85 8.697 

TEGV 0.0000 0.4725 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1013.77 109.07 46.240

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1253.52 169.72 107.164

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1013.77 109.07 46.240

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1434.36 216.67 165.042

Splitter 5.3011 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1013.77 109.07 46.240

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11596.7 9043.2 19967.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 654.09 21.04 12.732

LP_Shaft 3973.8 20766.9 15712.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.4414 1434.36 216.67 161.241

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.3864 1434.36 216.67 90.605

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1434.36 216.67 165.042

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1434.36 216.67 165.042

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1434.36 216.67 165.042

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 568.21 5.21 8.747

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 568.21 5.21 8.747

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 568.21 5.21 8.747

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 568.21 5.21 8.747

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2926.10 0.9995 0.0230 1.38725 0.02547 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.515 0.9810 1.0000 0.9800 613.40 1.000 1622.4 4533.4

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1045.6 15057.1

NASA/TM—2013-218094 G–26
************************************************************************************************************************************ 

Date:05/13/13 Time:07:22:04 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 478.88 Stator 1 exit: 495.86 Stator 2 inlet: 516.51 Stator 2 exit: 525.19 

 Stator 3 inlet: 549.81 Stator 3 exit: 558.46 Stator 4 inlet: 581.72 Stator 4 exit: 589.63 

 Stator 5 inlet: 608.21 Stator 5 exit: 615.66 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.82 

Fan Bypass Relative Humidity 0.30 

LPC Inlet Relative Humidity 2.06 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 422.59 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.40 

Additional Water at LPC Exit 0.0009991 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 429.85 6098.2 0.6086 3711.55 5.5955 793.07 26.691 1.344 75.600 2642.5 2485.1 1724.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 429.85 5.170 482.28 -15.41 0.0000 1178.26 3.458 429.85 3594.7 0.7800 1.40064 0.0000871 429.81 0.037 0.0001

FS1 Inlet.Fl_O 429.85 5.170 482.28 -15.41 0.0000 1178.26 4.118 451.90 4168.2 0.5791 1.40064 0.0000871 429.81 0.037 0.0001

FS12 Splitter.Fl_02 364.68 5.167 482.28 -15.41 0.0000 1000.11 4.111 451.74 3531.8 0.5808 1.40064 0.0000871 364.64 0.032 0.0001

FS2 Splitter.Fl_01 65.17 5.167 482.28 -15.41 0.0000 178.73 4.631 467.40 830.5 0.3986 1.40064 0.0000871 65.17 0.006 0.0001

FS14 Fan.Fl_O 364.68 8.043 553.95 1.78 0.0000 688.65 6.676 525.26 2606.7 0.5226 1.39969 0.0000871 364.64 0.032 0.0001

FS23 LPC.Fl_O 65.17 12.353 639.47 22.35 0.0000 86.09 11.158 621.22 412.6 0.3842 1.39780 0.0000871 65.17 0.006 0.0001

FS24 VaporIN.Fl_O 65.24 12.353 640.68 16.91 0.0000 86.26 11.152 622.30 412.6 0.3853 1.39762 0.0010862 65.17 0.071 0.0011

FS25 Bleed2.Fl_O 65.24 12.353 640.68 16.91 0.0000 86.26 11.152 622.30 412.6 0.3853 1.39762 0.0010862 65.17 0.071 0.0011

FS3 HPC.Fl_O 62.07 137.988 1346.69 192.91 0.0000 10.65 123.721 1308.35 49.7 0.4033 1.35889 0.0010862 62.01 0.067 0.0011

FS36 Bleed3.Fl_O 48.11 137.988 1346.69 192.91 0.0000 8.26 129.724 1324.88 49.3 0.3026 1.35889 0.0010862 48.05 0.052 0.0011

FS4 Burner.Fl_O 49.14 134.810 2642.46 166.48 0.0215 12.09 127.343 2608.38 74.6 0.2993 1.29130 0.0010862 48.05 0.052 0.0269

FS45 HPT.Fl_O 65.51 31.389 1732.68 -1.18 0.0160 56.06 28.246 1688.06 265.4 0.4010 1.32729 0.0010862 64.40 0.070 0.0205

FS49 LPT.Fl_O 66.27 7.218 1237.33 -131.71 0.0158 208.38 6.223 1190.06 860.2 0.4721 1.35470 0.0010862 65.17 0.071 0.0203

FS5 TEGV.Fl_O 66.27 7.218 1237.40 -131.71 0.0158 208.39 6.223 1190.12 860.2 0.4721 1.35469 0.0010862 65.17 0.071 0.0203

FS8 Core_Nozz.Fl_O 66.27 7.218 1237.53 -131.71 0.0158 208.40 3.852 1047.70 613.4 1.0000 1.35468 0.0010862 65.17 0.071 0.0203

FS17 FanDuctLkg.Fl_O 364.68 8.043 553.95 1.78 0.0000 688.65 6.676 525.26 2606.7 0.5226 1.39969 0.0000871 364.64 0.032 0.0001

FS171 Bleed15.Fl_O 364.68 8.043 553.95 1.78 0.0000 688.65 6.488 520.97 2481.9 0.5626 1.39969 0.0000871 364.64 0.032 0.0001

FS172 FanDuct.Fl_O 364.68 8.043 553.95 1.78 0.0000 688.65 6.488 520.97 2481.9 0.5626 1.39969 0.0000871 364.64 0.032 0.0001

FS173 Byp_Nozz.Fl_O 364.68 8.043 553.95 1.78 0.0000 688.65 4.248 461.54 2006.9 1.0000 1.39969 0.0000871 364.64 0.032 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1000.11 1.556 0.9070 3843.155 1.1486 0.9126 -8871.2 62.35 29.33

LPC 178.73 2.391 0.8667 3843.155 1.3259 0.8819 -3481.8 4.00 3.16

HPC 86.26 11.170 0.8615 10045.180 2.1020 0.8982 -15851.7 33.59 32.28

HPT 12.09 4.295 0.9089 217.184 1.3532 0.8892 15851.8 

LPT 56.06 4.348 0.9130 89.029 1.3976 0.8960 12352.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1162.03 1.544 0.9088 3806.511 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.15 2.431 0.8208 1.015 0.0000 1.2485 0.9719 1.0559 0.0003

HPC 78.45 10.691 0.8704 9777.382 12.8276 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.204 0.9089 1.305 4.2036 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.518 0.9197 1.001 3.5184 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–27
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.66 10595.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4008 1000.61 104.91 31.389

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7633 1000.61 104.91 7.218

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.18 96.11 39.993

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1182.44 150.67 90.246

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.18 96.11 39.993

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1346.69 192.91 137.988

Splitter 5.5955 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.18 96.11 39.993 

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11164.3 7457.3 15851.8 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 640.68 16.91 12.353

LP_Shaft 3705.9 17507.1 12352.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4489 1346.69 192.91 134.810

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5179 1346.69 192.91 75.653

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1346.69 192.91 137.988

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1346.69 192.91 137.988

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1346.69 192.91 137.988

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.95 1.78 8.043

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.95 1.78 8.043

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.95 1.78 8.043

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.95 1.78 8.043

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2642.44 0.9995 0.0230 1.03099 0.02145 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.087 0.9813 1.0000 0.9800 613.40 1.000 1536.9 3407.6

Byp_Nozz 2.326 0.9815 1.0000 0.9800 2006.86 1.000 1032.4 13286.2

NASA/TM—2013-218094 G–28
************************************************************************************************************************************ 

Date:05/13/13 Time:07:22:36 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 479.85 Stator 1 exit: 496.57 Stator 2 inlet: 517.01 Stator 2 exit: 525.73 

 Stator 3 inlet: 549.86 Stator 3 exit: 558.50 Stator 4 inlet: 581.29 Stator 4 exit: 589.17 

 Stator 5 inlet: 607.42 Stator 5 exit: 614.82 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.71 

Fan Bypass Relative Humidity 0.31 

LPC Inlet Relative Humidity 2.01 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 414.01 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.99 

Additional Water at LPC Exit 0.0010212 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 425.71 5870.2 0.6091 3575.25 5.6461 793.07 26.071 1.306 72.700 2611.2 2456.2 1704.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 425.71 5.170 482.28 -15.41 0.0000 1166.93 3.458 429.85 3560.1 0.7800 1.40064 0.0000871 425.68 0.037 0.0001

FS1 Inlet.Fl_O 425.71 5.170 482.28 -15.41 0.0000 1166.93 4.146 452.77 4168.2 0.5703 1.40064 0.0000871 425.68 0.037 0.0001

FS12 Splitter.Fl_02 361.66 5.167 482.28 -15.41 0.0000 991.84 4.135 452.49 3531.8 0.5731 1.40064 0.0000871 361.63 0.031 0.0001

FS2 Splitter.Fl_01 64.05 5.167 482.28 -15.41 0.0000 175.67 4.652 467.99 830.5 0.3903 1.40064 0.0000871 64.05 0.006 0.0001

FS14 Fan.Fl_O 361.66 7.964 552.25 1.38 0.0000 688.66 6.611 523.65 2606.7 0.5226 1.39972 0.0000871 361.63 0.031 0.0001

FS23 LPC.Fl_O 64.05 12.286 638.01 22.00 0.0000 84.98 11.132 620.35 412.6 0.3782 1.39784 0.0000871 64.05 0.006 0.0001

FS24 VaporIN.Fl_O 64.12 12.286 639.25 16.43 0.0000 85.15 11.126 621.46 412.6 0.3793 1.39766 0.0011083 64.05 0.071 0.0011

FS25 Bleed2.Fl_O 64.12 12.286 639.25 16.43 0.0000 85.15 11.126 621.46 412.6 0.3793 1.39766 0.0011083 64.05 0.071 0.0011

FS3 HPC.Fl_O 61.01 134.780 1336.94 190.25 0.0000 10.68 120.762 1298.59 49.7 0.4045 1.35946 0.0011083 60.94 0.068 0.0011

FS36 Bleed3.Fl_O 47.28 134.780 1336.94 190.25 0.0000 8.28 126.663 1315.13 49.3 0.3034 1.35946 0.0011083 47.23 0.052 0.0011

FS4 Burner.Fl_O 48.28 131.676 2611.22 164.41 0.0210 12.09 124.383 2577.43 74.6 0.2991 1.29249 0.0011083 47.23 0.052 0.0264

FS45 HPT.Fl_O 64.36 30.641 1711.79 -1.28 0.0157 56.08 27.570 1667.55 265.4 0.4010 1.32848 0.0011083 63.30 0.070 0.0201

FS49 LPT.Fl_O 65.11 7.045 1221.69 -130.11 0.0155 208.45 6.074 1174.86 860.2 0.4720 1.35589 0.0011083 64.05 0.071 0.0199

FS5 TEGV.Fl_O 65.11 7.045 1221.75 -130.11 0.0155 208.45 6.074 1174.93 860.2 0.4720 1.35588 0.0011083 64.05 0.071 0.0199

FS8 Core_Nozz.Fl_O 65.11 7.045 1221.89 -130.11 0.0155 208.46 3.759 1033.95 613.4 1.0000 1.35587 0.0011083 64.05 0.071 0.0199

FS17 FanDuctLkg.Fl_O 361.66 7.964 552.25 1.38 0.0000 688.66 6.611 523.65 2606.7 0.5226 1.39972 0.0000871 361.63 0.031 0.0001

FS171 Bleed15.Fl_O 361.66 7.964 552.25 1.38 0.0000 688.66 6.424 519.38 2481.9 0.5626 1.39972 0.0000871 361.63 0.031 0.0001

FS172 FanDuct.Fl_O 361.66 7.964 552.25 1.38 0.0000 688.66 6.424 519.38 2481.9 0.5626 1.39972 0.0000871 361.63 0.031 0.0001

FS173 Byp_Nozz.Fl_O 361.66 7.964 552.25 1.38 0.0000 688.66 4.206 460.12 2006.9 1.0000 1.39972 0.0000871 361.63 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.84 1.541 0.9070 3812.224 1.1451 0.9125 -8589.4 67.31 30.05

LPC 175.67 2.378 0.8687 3812.224 1.3229 0.8836 -3390.2 4.28 3.37

HPC 85.15 10.970 0.8615 10013.931 2.0914 0.8980 -15386.6 34.44 33.07

HPT 12.09 4.297 0.9083 217.556 1.3543 0.8888 15386.6 

LPT 56.08 4.349 0.9124 88.850 1.3985 0.8954 11979.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.42 1.529 0.9089 3775.875 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.16 2.399 0.8202 1.007 0.0000 1.2444 0.9848 1.0592 0.0003

HPC 77.44 10.500 0.8704 9746.966 12.7574 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9083 1.307 4.2060 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.519 0.9192 0.999 3.5189 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–29
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.09 10493.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3596 994.82 103.34 30.641

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7502 994.82 103.34 7.045

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 959.81 94.65 39.235

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1174.54 148.54 88.232

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 959.81 94.65 39.235

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1336.94 190.25 134.780

Splitter 5.6461 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 959.81 94.65 39.235

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11117.1 7269.2 15386.6 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 639.25 16.43 12.286

LP_Shaft 3676.0 17115.7 11979.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3212 1336.94 190.25 131.676

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4062 1336.94 190.25 73.884

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1336.94 190.25 134.780

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1336.94 190.25 134.780

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1336.94 190.25 134.780

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 552.25 1.38 7.964

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 552.25 1.38 7.964

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 552.25 1.38 7.964

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 552.25 1.38 7.964

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2611.20 0.9995 0.0230 0.99313 0.02103 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.037 0.9811 1.0000 0.9800 613.40 1.000 1527.4 3275.7

Byp_Nozz 2.303 0.9815 1.0000 0.9800 2006.86 1.000 1030.8 13088.1

NASA/TM—2013-218094 G–30
************************************************************************************************************************************ 

Date:05/13/13 Time:07:23:25 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 37/ 51/ 1/35 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 480.73 Stator 1 exit: 497.19 Stator 2 inlet: 517.39 Stator 2 exit: 526.11 

 Stator 3 inlet: 549.75 Stator 3 exit: 558.36 Stator 4 inlet: 580.69 Stator 4 exit: 588.52 

 Stator 5 inlet: 606.44 Stator 5 exit: 613.76 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.60 

Fan Bypass Relative Humidity 0.33 

LPC Inlet Relative Humidity 1.97 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 405.57 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 468.57 

Additional Water at LPC Exit 0.0010436 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 421.73 5651.4 0.6097 3445.70 5.7004 793.07 25.464 1.269 69.900 2581.3 2428.6 1684.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 421.73 5.170 482.28 -15.41 0.0000 1156.01 3.458 429.85 3526.8 0.7800 1.40064 0.0000871 421.70 0.037 0.0001

FS1 Inlet.Fl_O 421.73 5.170 482.28 -15.41 0.0000 1156.01 4.172 453.57 4168.2 0.5620 1.40064 0.0000871 421.70 0.037 0.0001

FS12 Splitter.Fl_02 358.79 5.167 482.28 -15.41 0.0000 983.98 4.157 453.18 3531.8 0.5660 1.40064 0.0000871 358.76 0.031 0.0001

FS2 Splitter.Fl_01 62.94 5.167 482.28 -15.41 0.0000 172.61 4.672 468.57 830.5 0.3821 1.40064 0.0000871 62.94 0.005 0.0001

FS14 Fan.Fl_O 358.79 7.889 550.60 0.98 0.0000 688.66 6.549 522.08 2606.7 0.5226 1.39975 0.0000871 358.76 0.031 0.0001

FS23 LPC.Fl_O 62.94 12.204 636.38 21.61 0.0000 83.96 11.089 619.25 412.6 0.3728 1.39789 0.0000871 62.94 0.005 0.0001

FS24 VaporIN.Fl_O 63.01 12.204 637.64 15.92 0.0000 84.13 11.083 620.39 412.6 0.3738 1.39770 0.0011307 62.94 0.071 0.0011

FS25 Bleed2.Fl_O 63.01 12.204 637.64 15.92 0.0000 84.13 11.083 620.39 412.6 0.3738 1.39770 0.0011307 62.94 0.071 0.0011

FS3 HPC.Fl_O 59.95 131.643 1327.40 187.65 0.0000 10.71 117.877 1289.06 49.7 0.4057 1.36003 0.0011307 59.88 0.068 0.0011

FS36 Bleed3.Fl_O 46.46 131.643 1327.40 187.65 0.0000 8.30 123.674 1305.60 49.3 0.3041 1.36003 0.0011307 46.41 0.052 0.0011

FS4 Burner.Fl_O 47.42 128.611 2581.28 162.37 0.0206 12.09 121.486 2547.79 74.6 0.2990 1.29363 0.0011307 46.41 0.052 0.0260

FS45 HPT.Fl_O 63.23 29.909 1691.79 -1.45 0.0154 56.11 26.908 1647.90 265.4 0.4011 1.32962 0.0011307 62.20 0.070 0.0198

FS49 LPT.Fl_O 63.96 6.877 1206.84 -128.62 0.0152 208.50 5.928 1160.45 860.2 0.4720 1.35702 0.0011307 62.94 0.071 0.0196

FS5 TEGV.Fl_O 63.96 6.877 1206.90 -128.62 0.0152 208.51 5.928 1160.51 860.2 0.4720 1.35701 0.0011307 62.94 0.071 0.0196

FS8 Core_Nozz.Fl_O 63.96 6.877 1207.04 -128.62 0.0152 208.52 3.668 1020.92 613.4 1.0000 1.35700 0.0011307 62.94 0.071 0.0196

FS17 FanDuctLkg.Fl_O 358.79 7.889 550.60 0.98 0.0000 688.66 6.549 522.08 2606.7 0.5226 1.39975 0.0000871 358.76 0.031 0.0001

FS171 Bleed15.Fl_O 358.79 7.889 550.60 0.98 0.0000 688.66 6.364 517.83 2481.9 0.5626 1.39975 0.0000871 358.76 0.031 0.0001

FS172 FanDuct.Fl_O 358.79 7.889 550.60 0.98 0.0000 688.66 6.364 517.83 2481.9 0.5626 1.39975 0.0000871 358.76 0.031 0.0001

FS173 Byp_Nozz.Fl_O 358.79 7.889 550.60 0.98 0.0000 688.66 4.166 458.74 2006.9 1.0000 1.39975 0.0000871 358.76 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.98 1.527 0.9073 3780.705 1.1417 0.9127 -8320.5 73.73 30.75

LPC 172.61 2.362 0.8702 3780.705 1.3195 0.8848 -3296.2 4.57 3.57

HPC 84.13 10.787 0.8615 9985.183 2.0817 0.8978 -14938.2 35.25 33.82

HPT 12.09 4.300 0.9078 217.912 1.3554 0.8883 14938.2 

LPT 56.11 4.349 0.9117 88.634 1.3992 0.8945 11616.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1143.28 1.515 0.9092 3744.657 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.13 2.367 0.8195 0.999 0.0000 1.2407 0.9961 1.0619 0.0003

HPC 76.51 10.326 0.8704 9718.985 12.6923 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.209 0.9078 1.310 4.2087 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.519 0.9185 0.997 3.5189 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–31
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.80 10395.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3187 989.07 101.79 29.909

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7372 989.07 101.79 6.877

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 954.46 93.20 38.480

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1166.77 146.44 86.256

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 954.46 93.20 38.480

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1327.40 187.65 131.643

Splitter 5.7004 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 954.46 93.20 38.480

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11071.3 7086.5 14938.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.64 15.92 12.204

LP_Shaft 3645.6 16735.7 11616.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.1941 1327.40 187.65 128.611

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.2950 1327.40 187.65 72.153

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1327.40 187.65 131.643

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1327.40 187.65 131.643

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1327.40 187.65 131.643

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 550.60 0.98 7.889

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 550.60 0.98 7.889

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 550.60 0.98 7.889

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 550.60 0.98 7.889

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2581.26 0.9995 0.0230 0.95714 0.02062 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.989 0.9808 1.0000 0.9800 613.40 1.000 1518.4 3147.3

Byp_Nozz 2.281 0.9815 1.0000 0.9800 2006.86 1.000 1029.3 12899.6

NASA/TM—2013-218094 G–32
 25μm, ISA +18R

************************************************************************************************************************************ 

Date:05/13/13 Time:09:31:08 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 27/ 55/ 2/24 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 449.02 Stator 1 exit: 467.66 Stator 2 inlet: 489.26 Stator 2 exit: 496.56 

 Stator 3 inlet: 525.33 Stator 3 exit: 533.38 Stator 4 inlet: 560.35 Stator 4 exit: 568.11 

 Stator 5 inlet: 588.99 Stator 5 exit: 596.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.11 

Fan Bypass Relative Humidity 0.16 

LPC Inlet Relative Humidity 2.31 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 483.40 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 442.62 

Additional Water at LPC Exit 0.0000769 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 475.58 8100.7 0.5999 4859.43 5.2932 776.30 31.986 1.684 100.000 2818.7 2645.7 1838.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 475.58 5.170 462.10 -19.92 0.0000 1276.02 3.458 411.85 3892.8 0.7800 1.40081 0.0000308 475.57 0.015 0.0000

FS1 Inlet.Fl_O 475.58 5.170 462.10 -19.92 0.0000 1276.02 3.838 424.34 4168.2 0.6662 1.40081 0.0000308 475.57 0.015 0.0000

FS12 Splitter.Fl_02 400.01 5.167 462.10 -19.92 0.0000 1073.80 3.865 425.25 3531.8 0.6574 1.40081 0.0000308 400.00 0.012 0.0000

FS2 Splitter.Fl_01 75.57 5.167 462.10 -19.92 0.0000 202.86 4.445 442.62 830.5 0.4685 1.40081 0.0000308 75.57 0.002 0.0000

FS14 Fan.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.260 516.24 2606.7 0.5226 1.39985 0.0000308 400.00 0.012 0.0000

FS23 LPC.Fl_O 75.57 12.670 625.31 19.26 0.0000 96.24 11.085 601.95 412.6 0.4413 1.39819 0.0000308 75.57 0.002 0.0000

FS24 VaporIN.Fl_O 75.58 12.670 625.46 18.86 0.0000 96.26 11.084 602.07 412.6 0.4415 1.39817 0.0001078 75.57 0.008 0.0001

FS25 Bleed2.Fl_O 75.58 12.670 625.46 18.86 0.0000 96.26 11.084 602.07 412.6 0.4415 1.39817 0.0001078 75.57 0.008 0.0001

FS3 HPC.Fl_O 71.91 165.364 1379.21 206.83 0.0000 10.42 149.114 1342.09 49.7 0.3928 1.35714 0.0001078 71.90 0.008 0.0001

FS36 Bleed3.Fl_O 55.73 165.364 1379.21 206.83 0.0000 8.08 155.924 1358.01 49.3 0.2953 1.35714 0.0001078 55.73 0.006 0.0001

FS4 Burner.Fl_O 57.08 161.555 2818.68 176.55 0.0242 12.10 152.619 2782.89 74.6 0.3003 1.28468 0.0001078 55.73 0.006 0.0292

FS45 HPT.Fl_O 76.04 37.753 1847.47 -1.63 0.0181 55.87 34.007 1801.01 265.4 0.4002 1.32099 0.0001078 74.68 0.008 0.0220

FS49 LPT.Fl_O 76.93 8.678 1323.60 -141.49 0.0179 208.11 7.485 1273.86 860.2 0.4724 1.34811 0.0001078 75.57 0.008 0.0218

FS5 TEGV.Fl_O 76.93 8.678 1323.66 -141.49 0.0179 208.11 7.485 1273.93 860.2 0.4724 1.34810 0.0001078 75.57 0.008 0.0218

FS8 Core_Nozz.Fl_O 76.93 8.678 1323.79 -141.49 0.0179 208.12 4.641 1123.76 613.4 1.0000 1.34809 0.0001078 75.57 0.008 0.0218

FS17 FanDuctLkg.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.260 516.24 2606.7 0.5226 1.39985 0.0000308 400.00 0.012 0.0000

FS171 Bleed15.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.055 512.03 2481.9 0.5625 1.39985 0.0000308 400.00 0.012 0.0000

FS172 FanDuct.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.055 512.03 2481.9 0.5625 1.39985 0.0000308 400.00 0.012 0.0000

FS173 Byp_Nozz.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 4.619 453.60 2006.9 1.0000 1.39985 0.0000308 400.00 0.012 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.80 1.692 0.9109 4120.456 1.1782 0.9173 -11176.8 38.42 23.46

LPC 202.86 2.452 0.8266 4120.456 1.3532 0.8469 -4189.6 2.96 2.22

HPC 96.26 13.052 0.8586 10344.363 2.2051 0.8979 -19612.3 26.29 25.49

HPT 12.10 4.279 0.9118 213.961 1.3469 0.8911 19612.3 

LPT 55.87 4.350 0.9155 90.485 1.3923 0.8986 15366.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.65 1.677 0.9128 4081.168 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.09 2.727 0.8329 1.088 0.0000 1.2288 0.8407 0.9925 0.0003

HPC 87.55 12.484 0.8674 10068.589 13.4710 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.188 0.9118 1.286 4.1884 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9223 1.018 3.5199 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–33
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.75 11475.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7812 1010.23 112.84 37.753

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8842 1010.23 112.84 8.678

TEGV 0.0000 0.4724 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.39 103.44 46.263

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1204.21 161.71 107.340

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.39 103.44 46.263

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1379.21 206.83 165.364

Splitter 5.2932 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.39 103.44 46.263

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11359.4 9067.9 19612.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 625.46 18.86 12.670

LP_Shaft 3889.2 20751.0 15366.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.6294 1379.21 206.83 161.555

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.5509 1379.21 206.83 90.740

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.21 206.83 165.364

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.21 206.83 165.364

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.21 206.83 165.364

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2818.67 0.9995 0.0230 1.34984 0.02422 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.509 0.9810 1.0000 0.9800 613.40 1.000 1587.7 4521.4

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1023.5 15054.2

NASA/TM—2013-218094 G–34
************************************************************************************************************************************ 

Date:05/13/13 Time:09:31:58 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 21/ 49/ 2/18 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 458.64 Stator 1 exit: 474.89 Stator 2 inlet: 494.62 Stator 2 exit: 502.88 

 Stator 3 inlet: 526.49 Stator 3 exit: 534.74 Stator 4 inlet: 557.07 Stator 4 exit: 564.63 

 Stator 5 inlet: 582.47 Stator 5 exit: 589.59 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.58 

Fan Bypass Relative Humidity 0.24 

LPC Inlet Relative Humidity 1.85 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 414.57 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 447.77 

Additional Water at LPC Exit 0.0000967 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 439.16 6083.5 0.5942 3614.86 5.5833 776.30 26.748 1.342 75.600 2543.7 2391.6 1654.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 439.16 5.170 462.10 -19.92 0.0000 1178.31 3.458 411.85 3594.7 0.7800 1.40081 0.0000308 439.15 0.014 0.0000

FS1 Inlet.Fl_O 439.16 5.170 462.10 -19.92 0.0000 1178.31 4.118 432.98 4168.2 0.5791 1.40081 0.0000308 439.15 0.014 0.0000

FS12 Splitter.Fl_02 372.46 5.167 462.10 -19.92 0.0000 999.83 4.112 432.86 3531.8 0.5805 1.40081 0.0000308 372.44 0.011 0.0000

FS2 Splitter.Fl_01 66.71 5.167 462.10 -19.92 0.0000 179.07 4.629 447.77 830.5 0.3995 1.40081 0.0000308 66.71 0.002 0.0000

FS14 Fan.Fl_O 372.46 8.040 530.74 -3.46 0.0000 688.70 6.674 503.23 2606.7 0.5226 1.40006 0.0000308 372.44 0.011 0.0000

FS23 LPC.Fl_O 66.71 12.320 612.40 16.16 0.0000 86.46 11.117 594.73 412.6 0.3861 1.39851 0.0000308 66.71 0.002 0.0000

FS24 VaporIN.Fl_O 66.71 12.320 612.57 15.64 0.0000 86.48 11.117 594.88 412.6 0.3862 1.39849 0.0001276 66.71 0.009 0.0001

FS25 Bleed2.Fl_O 66.71 12.320 612.57 15.64 0.0000 86.48 11.117 594.88 412.6 0.3862 1.39849 0.0001276 66.71 0.009 0.0001

FS3 HPC.Fl_O 63.48 138.283 1293.52 184.50 0.0000 10.65 123.998 1256.46 49.7 0.4027 1.36225 0.0001276 63.47 0.008 0.0001

FS36 Bleed3.Fl_O 49.20 138.283 1293.52 184.50 0.0000 8.26 130.007 1272.43 49.3 0.3021 1.36225 0.0001276 49.19 0.006 0.0001

FS4 Burner.Fl_O 50.20 135.099 2543.68 159.54 0.0204 12.09 127.608 2510.54 74.6 0.2988 1.29507 0.0001276 49.19 0.006 0.0248

FS45 HPT.Fl_O 66.94 31.404 1662.41 -1.53 0.0152 56.08 28.260 1619.23 265.4 0.4004 1.33128 0.0001276 65.93 0.008 0.0186

FS49 LPT.Fl_O 67.72 7.206 1183.98 -126.43 0.0151 208.65 6.211 1138.28 860.2 0.4719 1.35871 0.0001276 66.71 0.009 0.0184

FS5 TEGV.Fl_O 67.72 7.206 1184.04 -126.43 0.0151 208.65 6.211 1138.35 860.2 0.4719 1.35871 0.0001276 66.71 0.009 0.0184

FS8 Core_Nozz.Fl_O 67.72 7.206 1184.18 -126.43 0.0151 208.66 3.842 1000.91 613.4 1.0000 1.35870 0.0001276 66.71 0.009 0.0184

FS17 FanDuctLkg.Fl_O 372.46 8.040 530.74 -3.46 0.0000 688.70 6.674 503.23 2606.7 0.5226 1.40006 0.0000308 372.44 0.011 0.0000

FS171 Bleed15.Fl_O 372.46 8.040 530.74 -3.46 0.0000 688.70 6.485 499.13 2481.9 0.5625 1.40006 0.0000308 372.44 0.011 0.0000

FS172 FanDuct.Fl_O 372.46 8.040 530.74 -3.46 0.0000 688.70 6.485 499.13 2481.9 0.5625 1.40006 0.0000308 372.44 0.011 0.0000

FS173 Byp_Nozz.Fl_O 372.46 8.040 530.74 -3.46 0.0000 688.70 4.246 442.16 2006.9 1.0000 1.40006 0.0000308 372.44 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 999.83 1.556 0.9070 3842.004 1.1486 0.9126 -8673.5 62.44 29.36

LPC 179.07 2.384 0.8662 3842.004 1.3253 0.8814 -3405.0 4.01 3.17

HPC 86.48 11.224 0.8614 10051.885 2.1116 0.8984 -15552.6 33.26 31.97

HPT 12.09 4.302 0.9079 216.594 1.3570 0.8887 15552.6 

LPT 56.08 4.358 0.9114 88.942 1.4013 0.8940 12078.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.70 1.543 0.9088 3805.371 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.08 2.430 0.8208 1.015 0.0000 1.2516 0.9682 1.0554 0.0003

HPC 78.66 10.742 0.8703 9783.908 12.8557 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.210 0.9079 1.302 4.2105 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9181 1.001 3.5255 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–35
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.67 10596.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4551 959.23 100.07 31.404

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7806 959.23 100.07 7.206

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.05 91.63 40.032

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1134.78 143.97 90.417

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.05 91.63 40.032

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1293.52 184.50 138.283

Splitter 5.5833 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.05 91.63 40.032

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10923.9 7477.5 15552.6 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.57 15.64 12.320

LP_Shaft 3626.4 17493.2 12078.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.6175 1293.52 184.50 135.099

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.6655 1293.52 184.50 75.785

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.52 184.50 138.283

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.52 184.50 138.283

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.52 184.50 138.283

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2543.66 0.9995 0.0230 1.00413 0.02041 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.084 0.9813 1.0000 0.9800 613.40 1.000 1503.8 3400.5

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1010.5 13279.3

NASA/TM—2013-218094 G–36
************************************************************************************************************************************ 

Date:05/13/13 Time:09:32:31 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 459.59 Stator 1 exit: 475.58 Stator 2 inlet: 495.12 Stator 2 exit: 503.42 

 Stator 3 inlet: 526.55 Stator 3 exit: 534.79 Stator 4 inlet: 556.68 Stator 4 exit: 564.21 

 Stator 5 inlet: 581.74 Stator 5 exit: 588.81 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.46 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 1.81 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 406.15 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.35 

Additional Water at LPC Exit 0.0000997 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 434.93 5855.8 0.5946 3481.93 5.6337 776.30 26.124 1.304 72.700 2513.3 2363.4 1635.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 434.93 5.170 462.10 -19.92 0.0000 1166.95 3.458 411.85 3560.0 0.7800 1.40081 0.0000308 434.92 0.013 0.0000

FS1 Inlet.Fl_O 434.93 5.170 462.10 -19.92 0.0000 1166.95 4.146 433.81 4168.2 0.5703 1.40081 0.0000308 434.92 0.013 0.0000

FS12 Splitter.Fl_02 369.37 5.167 462.10 -19.92 0.0000 991.53 4.136 433.58 3531.8 0.5728 1.40081 0.0000308 369.35 0.011 0.0000

FS2 Splitter.Fl_01 65.56 5.167 462.10 -19.92 0.0000 176.00 4.650 448.35 830.5 0.3912 1.40081 0.0000308 65.56 0.002 0.0000

FS14 Fan.Fl_O 369.37 7.961 529.11 -3.85 0.0000 688.70 6.608 501.68 2606.7 0.5226 1.40008 0.0000308 369.35 0.011 0.0000

FS23 LPC.Fl_O 65.56 12.257 611.02 15.82 0.0000 85.32 11.096 593.93 412.6 0.3799 1.39854 0.0000308 65.56 0.002 0.0000

FS24 VaporIN.Fl_O 65.57 12.257 611.19 15.29 0.0000 85.34 11.095 594.08 412.6 0.3801 1.39853 0.0001305 65.56 0.009 0.0001

FS25 Bleed2.Fl_O 65.57 12.257 611.19 15.29 0.0000 85.34 11.095 594.08 412.6 0.3801 1.39853 0.0001305 65.56 0.009 0.0001

FS3 HPC.Fl_O 62.39 135.057 1283.94 182.02 0.0000 10.68 121.022 1246.89 49.7 0.4039 1.36284 0.0001305 62.38 0.008 0.0001

FS36 Bleed3.Fl_O 48.35 135.057 1283.94 182.02 0.0000 8.28 126.929 1262.87 49.3 0.3029 1.36284 0.0001305 48.35 0.006 0.0001

FS4 Burner.Fl_O 49.32 131.946 2513.27 157.61 0.0200 12.09 124.628 2480.43 74.6 0.2987 1.29624 0.0001305 48.35 0.006 0.0243

FS45 HPT.Fl_O 65.77 30.656 1642.57 -1.53 0.0149 56.11 27.584 1599.73 265.4 0.4005 1.33245 0.0001305 64.79 0.008 0.0183

FS49 LPT.Fl_O 66.54 7.034 1169.25 -124.80 0.0148 208.71 6.062 1123.99 860.2 0.4718 1.35985 0.0001305 65.56 0.009 0.0181

FS5 TEGV.Fl_O 66.54 7.034 1169.32 -124.80 0.0148 208.72 6.062 1124.05 860.2 0.4718 1.35984 0.0001305 65.56 0.009 0.0181

FS8 Core_Nozz.Fl_O 66.54 7.034 1169.45 -124.80 0.0148 208.73 3.749 988.01 613.4 1.0000 1.35983 0.0001305 65.56 0.009 0.0181

FS17 FanDuctLkg.Fl_O 369.37 7.961 529.11 -3.85 0.0000 688.70 6.608 501.68 2606.7 0.5226 1.40008 0.0000308 369.35 0.011 0.0000

FS171 Bleed15.Fl_O 369.37 7.961 529.11 -3.85 0.0000 688.70 6.422 497.59 2481.9 0.5625 1.40008 0.0000308 369.35 0.011 0.0000

FS172 FanDuct.Fl_O 369.37 7.961 529.11 -3.85 0.0000 688.70 6.422 497.59 2481.9 0.5625 1.40008 0.0000308 369.35 0.011 0.0000

FS173 Byp_Nozz.Fl_O 369.37 7.961 529.11 -3.85 0.0000 688.70 4.204 440.80 2006.9 1.0000 1.40008 0.0000308 369.35 0.011 0.0000 

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.53 1.541 0.9070 3810.950 1.1450 0.9125 -8396.5 67.56 30.09

LPC 176.00 2.372 0.8684 3810.950 1.3223 0.8833 -3315.8 4.29 3.38

HPC 85.34 11.019 0.8615 10019.853 2.1007 0.8982 -15092.4 34.12 32.77

HPT 12.09 4.304 0.9073 216.963 1.3577 0.8874 15092.4 

LPT 56.11 4.358 0.9107 88.755 1.4021 0.8932 11712.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.06 1.528 0.9089 3774.613 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.07 2.398 0.8201 1.007 0.0000 1.2475 0.9816 1.0588 0.0003

HPC 77.62 10.547 0.8704 9752.731 12.7846 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.213 0.9073 1.304 4.2125 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9175 0.998 3.5257 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–37
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.00 10494.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4130 953.58 98.66 30.656

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7672 953.58 98.66 7.034

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.81 90.32 39.273

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1127.04 142.00 88.393

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.81 90.32 39.273

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1283.94 182.02 135.057

Splitter 5.6337 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.81 90.32 39.273

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt 

HP_Shaft 10876.9 7287.7 15092.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 611.19 15.29 12.257

LP_Shaft 3597.1 17101.9 11712.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4868 1283.94 182.02 131.946

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5511 1283.94 182.02 74.008

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.94 182.02 135.057

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.94 182.02 135.057

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.94 182.02 135.057

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.961

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.961

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.961

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.961

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2513.25 0.9995 0.0230 0.96720 0.02001 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.034 0.9811 1.0000 0.9800 613.40 1.000 1494.6 3269.3

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1009.0 13080.6

NASA/TM—2013-218094 G–38
************************************************************************************************************************************ 

Date:05/13/13 Time:09:33:03 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 460.43 Stator 1 exit: 476.17 Stator 2 inlet: 495.48 Stator 2 exit: 503.78 

 Stator 3 inlet: 526.45 Stator 3 exit: 534.66 Stator 4 inlet: 556.09 Stator 4 exit: 563.58 

 Stator 5 inlet: 580.79 Stator 5 exit: 587.80 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.36 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 1.77 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 397.91 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.90 

Additional Water at LPC Exit 0.0001025 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 430.86 5637.1 0.5955 3356.62 5.6872 776.30 25.519 1.267 69.900 2484.5 2336.9 1615.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 430.86 5.170 462.10 -19.92 0.0000 1156.04 3.458 411.85 3526.7 0.7800 1.40081 0.0000308 430.85 0.013 0.0000

FS1 Inlet.Fl_O 430.86 5.170 462.10 -19.92 0.0000 1156.04 4.172 434.59 4168.2 0.5619 1.40081 0.0000308 430.85 0.013 0.0000

FS12 Splitter.Fl_02 366.43 5.167 462.10 -19.92 0.0000 983.66 4.158 434.24 3531.8 0.5657 1.40081 0.0000308 366.42 0.011 0.0000

FS2 Splitter.Fl_01 64.43 5.167 462.10 -19.92 0.0000 172.96 4.670 448.90 830.5 0.3830 1.40081 0.0000308 64.43 0.002 0.0000

FS14 Fan.Fl_O 366.43 7.886 527.53 -4.23 0.0000 688.70 6.546 500.18 2606.7 0.5226 1.40011 0.0000308 366.42 0.011 0.0000

FS23 LPC.Fl_O 64.43 12.175 609.45 15.45 0.0000 84.31 11.052 592.87 412.6 0.3745 1.39858 0.0000308 64.43 0.002 0.0000

FS24 VaporIN.Fl_O 64.44 12.175 609.62 14.90 0.0000 84.33 11.051 593.02 412.6 0.3746 1.39856 0.0001334 64.43 0.009 0.0001

FS25 Bleed2.Fl_O 64.44 12.175 609.62 14.90 0.0000 84.33 11.051 593.02 412.6 0.3746 1.39856 0.0001334 64.43 0.009 0.0001

FS3 HPC.Fl_O 61.31 131.931 1274.71 179.63 0.0000 10.71 118.146 1237.68 49.7 0.4050 1.36342 0.0001334 61.30 0.008 0.0001

FS36 Bleed3.Fl_O 47.52 131.931 1274.71 179.63 0.0000 8.30 123.950 1253.66 49.3 0.3037 1.36342 0.0001334 47.51 0.006 0.0001

FS4 Burner.Fl_O 48.45 128.892 2484.47 155.73 0.0196 12.09 121.743 2451.90 74.6 0.2985 1.29737 0.0001334 47.51 0.006 0.0239

FS45 HPT.Fl_O 64.62 29.926 1623.10 -1.60 0.0146 56.13 26.924 1580.63 265.4 0.4005 1.33361 0.0001334 63.68 0.008 0.0179

FS49 LPT.Fl_O 65.37 6.867 1154.86 -123.25 0.0145 208.76 5.917 1110.05 860.2 0.4718 1.36096 0.0001334 64.43 0.009 0.0177

FS5 TEGV.Fl_O 65.37 6.867 1154.93 -123.25 0.0145 208.76 5.917 1110.11 860.2 0.4718 1.36096 0.0001334 64.43 0.009 0.0177

FS8 Core_Nozz.Fl_O 65.37 6.867 1155.07 -123.25 0.0145 208.78 3.658 975.43 613.4 1.0000 1.36095 0.0001334 64.43 0.009 0.0177

FS17 FanDuctLkg.Fl_O 366.43 7.886 527.53 -4.23 0.0000 688.70 6.546 500.18 2606.7 0.5226 1.40011 0.0000308 366.42 0.011 0.0000

FS171 Bleed15.Fl_O 366.43 7.886 527.53 -4.23 0.0000 688.70 6.361 496.10 2481.9 0.5625 1.40011 0.0000308 366.42 0.011 0.0000

FS172 FanDuct.Fl_O 366.43 7.886 527.53 -4.23 0.0000 688.70 6.361 496.10 2481.9 0.5625 1.40011 0.0000308 366.42 0.011 0.0000

FS173 Byp_Nozz.Fl_O 366.43 7.886 527.53 -4.23 0.0000 688.70 4.164 439.48 2006.9 1.0000 1.40011 0.0000308 366.42 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.66 1.526 0.9074 3779.269 1.1416 0.9127 -8132.9 74.05 30.79

LPC 172.96 2.356 0.8699 3779.269 1.3189 0.8846 -3224.0 4.58 3.57

HPC 84.33 10.836 0.8615 9991.297 2.0910 0.8980 -14653.9 34.92 33.50

HPT 12.09 4.307 0.9067 217.315 1.3590 0.8875 14653.9 

LPT 56.13 4.358 0.9100 88.543 1.4029 0.8923 11356.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1142.91 1.514 0.9092 3743.234 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.04 2.366 0.8195 0.998 0.0000 1.2440 0.9929 1.0616 0.0003

HPC 76.69 10.373 0.8704 9724.936 12.7199 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.215 0.9067 1.306 4.2154 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9168 0.996 3.5257 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–39
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.71 10396.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3713 948.00 97.26 29.926

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7539 948.00 97.26 6.867

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.63 89.03 38.521

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1119.53 140.09 86.423

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.63 89.03 38.521

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1274.71 179.63 131.931

Splitter 5.6872 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.63 89.03 38.521

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10832.0 7105.3 14653.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 609.62 14.90 12.175

LP_Shaft 3567.2 16721.1 11356.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3575 1274.71 179.63 128.892

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4380 1274.71 179.63 72.283

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.71 179.63 131.931

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.71 179.63 131.931

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.71 179.63 131.931

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 527.53 -4.23 7.886

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 527.53 -4.23 7.886

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 527.53 -4.23 7.886

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 527.53 -4.23 7.886

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2484.45 0.9995 0.0230 0.93240 0.01963 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.986 0.9808 1.0000 0.9800 613.40 1.000 1485.6 3141.2

Byp_Nozz 2.280 0.9815 1.0000 0.9800 2006.86 1.000 1007.5 12891.8

NASA/TM—2013-218094 G–40
 25μm, ISA +36R

************************************************************************************************************************************ 

Date:05/13/13 Time:10:00:09 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 27/ 41/ 1/25 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 468.75 Stator 1 exit: 488.22 Stator 2 inlet: 510.83 Stator 2 exit: 518.50 

 Stator 3 inlet: 548.53 Stator 3 exit: 556.97 Stator 4 inlet: 585.11 Stator 4 exit: 593.25 

 Stator 5 inlet: 615.04 Stator 5 exit: 622.97 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.34 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 2.54 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 493.51 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 461.98 

Additional Water at LPC Exit 0.0001248 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 465.49 8112.6 0.6156 4993.72 5.2964 793.07 31.925 1.687 100.000 2926.1 2747.3 1915.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 465.49 5.170 482.28 -15.41 0.0000 1275.96 3.458 429.85 3892.7 0.7800 1.40064 0.0000871 465.45 0.041 0.0001

FS1 Inlet.Fl_O 465.49 5.170 482.28 -15.41 0.0000 1275.96 3.838 442.89 4168.2 0.6662 1.40064 0.0000871 465.45 0.041 0.0001

FS12 Splitter.Fl_02 391.56 5.167 482.28 -15.41 0.0000 1073.85 3.865 443.82 3531.8 0.6575 1.40064 0.0000871 391.53 0.034 0.0001

FS2 Splitter.Fl_01 73.93 5.167 482.28 -15.41 0.0000 202.75 4.446 461.98 830.5 0.4682 1.40064 0.0000871 73.92 0.006 0.0001

FS14 Fan.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.261 538.78 2606.7 0.5227 1.39944 0.0000871 391.53 0.034 0.0001

FS23 LPC.Fl_O 73.93 12.698 652.75 25.55 0.0000 95.99 11.119 628.55 412.6 0.4400 1.39742 0.0000871 73.92 0.006 0.0001

FS24 VaporIN.Fl_O 73.94 12.698 652.96 24.89 0.0000 96.02 11.118 628.73 412.6 0.4401 1.39740 0.0002119 73.92 0.016 0.0002

FS25 Bleed2.Fl_O 73.94 12.698 652.96 24.89 0.0000 96.02 11.118 628.73 412.6 0.4401 1.39740 0.0002119 73.92 0.016 0.0002

FS3 HPC.Fl_O 70.35 165.047 1433.44 220.42 0.0000 10.41 148.847 1395.15 49.7 0.3930 1.35403 0.0002119 70.34 0.015 0.0002

FS36 Bleed3.Fl_O 54.52 165.047 1433.44 220.42 0.0000 8.07 155.636 1411.58 49.3 0.2955 1.35403 0.0002119 54.51 0.012 0.0002

FS4 Burner.Fl_O 55.91 161.246 2926.06 188.18 0.0254 12.10 152.349 2889.29 74.6 0.3007 1.28088 0.0002119 54.51 0.012 0.0308

FS45 HPT.Fl_O 74.46 37.748 1924.78 3.18 0.0190 55.84 34.006 1876.83 265.4 0.4007 1.31717 0.0002119 73.06 0.015 0.0232

FS49 LPT.Fl_O 75.33 8.694 1382.66 -142.81 0.0188 207.89 7.501 1331.26 860.2 0.4726 1.34396 0.0002119 73.92 0.016 0.0229

FS5 TEGV.Fl_O 75.33 8.694 1382.73 -142.81 0.0188 207.90 7.501 1331.33 860.2 0.4726 1.34396 0.0002119 73.92 0.016 0.0229

FS8 Core_Nozz.Fl_O 75.33 8.694 1382.85 -142.81 0.0188 207.91 4.655 1175.94 613.4 1.0000 1.34395 0.0002119 73.92 0.016 0.0229

FS17 FanDuctLkg.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.261 538.78 2606.7 0.5227 1.39944 0.0000871 391.53 0.034 0.0001

FS171 Bleed15.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.056 534.39 2481.9 0.5626 1.39944 0.0000871 391.53 0.034 0.0001

FS172 FanDuct.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.056 534.39 2481.9 0.5626 1.39944 0.0000871 391.53 0.034 0.0001

FS173 Byp_Nozz.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 4.619 473.44 2006.9 1.0000 1.39944 0.0000871 391.53 0.034 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.85 1.693 0.9109 4120.705 1.1782 0.9173 -11421.0 38.39 23.45

LPC 202.75 2.457 0.8276 4120.705 1.3535 0.8477 -4284.4 2.96 2.22

HPC 96.02 12.998 0.8587 10334.072 2.1953 0.8978 -19959.6 26.51 25.70

HPT 12.10 4.272 0.9122 214.352 1.3425 0.8900 19959.6 

LPT 55.84 4.342 0.9168 90.570 1.3886 0.9005 15705.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.70 1.677 0.9128 4081.415 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.11 2.727 0.8329 1.088 0.0000 1.2280 0.8437 0.9936 0.0003

HPC 87.32 12.433 0.8676 10058.573 13.4500 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1810 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.514 0.9236 1.019 3.5135 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–41
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.72 11474.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7209 1051.90 122.65 37.748

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8651 1051.90 122.65 8.694

TEGV 0.0000 0.4726 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.73 112.88 46.214

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1252.55 173.49 107.154

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.73 112.88 46.214

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1433.44 220.42 165.047

Splitter 5.2964 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.73 112.88 46.214

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11595.0 9041.0 19959.6 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 652.96 24.89 12.698

LP_Shaft 3973.5 20759.7 15705.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.4423 1433.44 220.42 161.246

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.3872 1433.44 220.42 90.605

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.44 220.42 165.047

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.44 220.42 165.047

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.44 220.42 165.047

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2926.06 0.9995 0.0230 1.38714 0.02545 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.514 0.9810 1.0000 0.9800 613.40 1.000 1621.8 4531.2

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1045.6 15055.4

NASA/TM—2013-218094 G–42
************************************************************************************************************************************ 

Date:05/13/13 Time:10:00:41 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 478.73 Stator 1 exit: 495.69 Stator 2 inlet: 516.30 Stator 2 exit: 524.95 

 Stator 3 inlet: 549.58 Stator 3 exit: 558.21 Stator 4 inlet: 581.50 Stator 4 exit: 589.41 

 Stator 5 inlet: 608.02 Stator 5 exit: 615.47 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.82 

Fan Bypass Relative Humidity 0.30 

LPC Inlet Relative Humidity 2.06 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 423.28 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.35 

Additional Water at LPC Exit 0.0001559 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 429.86 6091.0 0.6090 3709.16 5.5867 793.07 26.696 1.344 75.600 2640.9 2483.5 1723.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 429.86 5.170 482.28 -15.41 0.0000 1178.28 3.458 429.85 3594.7 0.7800 1.40064 0.0000871 429.82 0.037 0.0001

FS1 Inlet.Fl_O 429.86 5.170 482.28 -15.41 0.0000 1178.28 4.118 451.90 4168.2 0.5792 1.40064 0.0000871 429.82 0.037 0.0001

FS12 Splitter.Fl_02 364.60 5.167 482.28 -15.41 0.0000 999.89 4.112 451.76 3531.8 0.5806 1.40064 0.0000871 364.56 0.032 0.0001

FS2 Splitter.Fl_01 65.26 5.167 482.28 -15.41 0.0000 178.98 4.629 467.35 830.5 0.3993 1.40064 0.0000871 65.26 0.006 0.0001

FS14 Fan.Fl_O 364.60 8.040 553.91 1.77 0.0000 688.65 6.675 525.21 2606.7 0.5226 1.39969 0.0000871 364.56 0.032 0.0001

FS23 LPC.Fl_O 65.26 12.330 639.17 22.28 0.0000 86.35 11.130 620.80 412.6 0.3856 1.39781 0.0000871 65.26 0.006 0.0001

FS24 VaporIN.Fl_O 65.27 12.330 639.41 21.44 0.0000 86.38 11.129 621.02 412.6 0.3857 1.39778 0.0002430 65.26 0.016 0.0002

FS25 Bleed2.Fl_O 65.27 12.330 639.41 21.44 0.0000 86.38 11.129 621.02 412.6 0.3857 1.39778 0.0002430 65.26 0.016 0.0002

FS3 HPC.Fl_O 62.11 138.011 1345.21 197.23 0.0000 10.65 123.758 1306.93 49.7 0.4031 1.35911 0.0002430 62.09 0.015 0.0002

FS36 Bleed3.Fl_O 48.13 138.011 1345.21 197.23 0.0000 8.25 129.754 1323.44 49.3 0.3024 1.35911 0.0002430 48.12 0.012 0.0002

FS4 Burner.Fl_O 49.16 134.833 2640.85 170.73 0.0214 12.09 127.369 2606.79 74.6 0.2992 1.29152 0.0002430 48.12 0.012 0.0261

FS45 HPT.Fl_O 65.54 31.391 1731.20 3.30 0.0160 56.06 28.250 1686.62 265.4 0.4009 1.32751 0.0002430 64.49 0.016 0.0196

FS49 LPT.Fl_O 66.30 7.216 1235.99 -127.06 0.0158 208.45 6.221 1188.74 860.2 0.4720 1.35492 0.0002430 65.26 0.016 0.0194

FS5 TEGV.Fl_O 66.30 7.216 1236.05 -127.06 0.0158 208.45 6.221 1188.80 860.2 0.4721 1.35491 0.0002430 65.26 0.016 0.0194

FS8 Core_Nozz.Fl_O 66.30 7.216 1236.19 -127.06 0.0158 208.46 3.851 1046.46 613.4 1.0000 1.35490 0.0002430 65.26 0.016 0.0194

FS17 FanDuctLkg.Fl_O 364.60 8.040 553.91 1.77 0.0000 688.65 6.675 525.21 2606.7 0.5226 1.39969 0.0000871 364.56 0.032 0.0001

FS171 Bleed15.Fl_O 364.60 8.040 553.91 1.77 0.0000 688.65 6.486 520.93 2481.9 0.5626 1.39969 0.0000871 364.56 0.032 0.0001

FS172 FanDuct.Fl_O 364.60 8.040 553.91 1.77 0.0000 688.65 6.486 520.93 2481.9 0.5626 1.39969 0.0000871 364.56 0.032 0.0001

FS173 Byp_Nozz.Fl_O 364.60 8.040 553.91 1.77 0.0000 688.65 4.246 461.50 2006.9 1.0000 1.39969 0.0000871 364.56 0.032 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 999.89 1.556 0.9070 3842.318 1.1485 0.9126 -8863.9 62.41 29.35

LPC 178.98 2.386 0.8663 3842.318 1.3253 0.8815 -3479.9 4.01 3.17

HPC 86.38 11.193 0.8615 10048.502 2.1038 0.8982 -15840.8 33.48 32.19

HPT 12.09 4.295 0.9089 217.106 1.3534 0.8892 15840.8 

LPT 56.06 4.350 0.9129 89.048 1.3979 0.8960 12343.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.78 1.543 0.9088 3805.682 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.10 2.430 0.8208 1.015 0.0000 1.2507 0.9694 1.0555 0.0003

HPC 78.56 10.712 0.8704 9780.616 12.8362 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.204 0.9089 1.305 4.2040 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9197 1.002 3.5198 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–43
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.73 10595.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4020 999.21 109.34 31.391

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7637 999.21 109.34 7.216

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.79 100.55 39.980

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1180.99 155.04 90.253

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.79 100.55 39.980

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1345.21 197.23 138.011

Splitter 5.5867 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.79 100.55 39.980

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11156.9 7457.0 15840.8 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 639.41 21.44 12.330

LP_Shaft 3705.1 17497.9 12343.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4528 1345.21 197.23 134.833

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5213 1345.21 197.23 75.664

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1345.21 197.23 138.011

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1345.21 197.23 138.011

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1345.21 197.23 138.011

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.91 1.77 8.040

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.91 1.77 8.040

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.91 1.77 8.040

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.91 1.77 8.040

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2640.84 0.9995 0.0230 1.03032 0.02141 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.087 0.9813 1.0000 0.9800 613.40 1.000 1535.8 3405.8

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1032.4 13280.9

NASA/TM—2013-218094 G–44
************************************************************************************************************************************ 

Date:05/13/13 Time:10:01:13 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 479.70 Stator 1 exit: 496.41 Stator 2 inlet: 516.81 Stator 2 exit: 525.49 

 Stator 3 inlet: 549.63 Stator 3 exit: 558.25 Stator 4 inlet: 581.09 Stator 4 exit: 588.96 

 Stator 5 inlet: 607.25 Stator 5 exit: 614.64 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.70 

Fan Bypass Relative Humidity 0.31 

LPC Inlet Relative Humidity 2.02 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 414.72 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.94 

Additional Water at LPC Exit 0.0001602 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 425.73 5862.8 0.6094 3572.69 5.6367 793.07 26.076 1.306 72.700 2609.4 2454.5 1702.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 425.73 5.170 482.28 -15.41 0.0000 1166.96 3.458 429.85 3560.2 0.7800 1.40064 0.0000871 425.69 0.037 0.0001

FS1 Inlet.Fl_O 425.73 5.170 482.28 -15.41 0.0000 1166.96 4.146 452.76 4168.2 0.5703 1.40064 0.0000871 425.69 0.037 0.0001

FS12 Splitter.Fl_02 361.58 5.167 482.28 -15.41 0.0000 991.62 4.136 452.51 3531.8 0.5729 1.40064 0.0000871 361.55 0.031 0.0001

FS2 Splitter.Fl_01 64.15 5.167 482.28 -15.41 0.0000 175.92 4.650 467.94 830.5 0.3910 1.40064 0.0000871 64.14 0.006 0.0001

FS14 Fan.Fl_O 361.58 7.962 552.21 1.37 0.0000 688.66 6.609 523.60 2606.7 0.5226 1.39972 0.0000871 361.55 0.031 0.0001

FS23 LPC.Fl_O 64.15 12.266 637.72 21.93 0.0000 85.22 11.106 619.95 412.6 0.3795 1.39785 0.0000871 64.14 0.006 0.0001

FS24 VaporIN.Fl_O 64.16 12.266 637.97 21.07 0.0000 85.25 11.105 620.17 412.6 0.3797 1.39782 0.0002473 64.14 0.016 0.0002

FS25 Bleed2.Fl_O 64.16 12.266 637.97 21.07 0.0000 85.25 11.105 620.17 412.6 0.3797 1.39782 0.0002473 64.14 0.016 0.0002

FS3 HPC.Fl_O 61.05 134.805 1335.40 194.66 0.0000 10.68 120.800 1297.12 49.7 0.4043 1.35969 0.0002473 61.03 0.015 0.0002

FS36 Bleed3.Fl_O 47.31 134.805 1335.40 194.66 0.0000 8.28 126.695 1313.62 49.3 0.3032 1.35969 0.0002473 47.30 0.012 0.0002

FS4 Burner.Fl_O 48.30 131.701 2609.43 168.75 0.0210 12.09 124.411 2575.67 74.6 0.2990 1.29271 0.0002473 47.30 0.012 0.0256

FS45 HPT.Fl_O 64.40 30.644 1710.19 3.30 0.0157 56.08 27.575 1666.00 265.4 0.4009 1.32870 0.0002473 63.39 0.016 0.0192

FS49 LPT.Fl_O 65.15 7.043 1220.24 -125.36 0.0155 208.51 6.072 1173.45 860.2 0.4720 1.35612 0.0002473 64.14 0.016 0.0190

FS5 TEGV.Fl_O 65.15 7.043 1220.30 -125.36 0.0155 208.52 6.071 1173.51 860.2 0.4720 1.35611 0.0002473 64.14 0.016 0.0190

FS8 Core_Nozz.Fl_O 65.15 7.043 1220.44 -125.36 0.0155 208.53 3.757 1032.63 613.4 1.0000 1.35610 0.0002473 64.14 0.016 0.0190

FS17 FanDuctLkg.Fl_O 361.58 7.962 552.21 1.37 0.0000 688.66 6.609 523.60 2606.7 0.5226 1.39972 0.0000871 361.55 0.031 0.0001

FS171 Bleed15.Fl_O 361.58 7.962 552.21 1.37 0.0000 688.66 6.423 519.33 2481.9 0.5626 1.39972 0.0000871 361.55 0.031 0.0001

FS172 FanDuct.Fl_O 361.58 7.962 552.21 1.37 0.0000 688.66 6.423 519.33 2481.9 0.5626 1.39972 0.0000871 361.55 0.031 0.0001

FS173 Byp_Nozz.Fl_O 361.58 7.962 552.21 1.37 0.0000 688.66 4.205 460.08 2006.9 1.0000 1.39972 0.0000871 361.55 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.62 1.541 0.9070 3811.363 1.1450 0.9125 -8581.8 67.48 30.07

LPC 175.92 2.374 0.8684 3811.363 1.3223 0.8833 -3388.8 4.29 3.38

HPC 85.25 10.991 0.8615 10017.005 2.0932 0.8980 -15375.4 34.34 32.98

HPT 12.09 4.298 0.9083 217.479 1.3545 0.8888 15375.4 

LPT 56.08 4.351 0.9124 88.871 1.3988 0.8953 11970.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.16 1.528 0.9089 3775.022 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.10 2.398 0.8201 1.007 0.0000 1.2467 0.9825 1.0588 0.0003

HPC 77.54 10.520 0.8704 9749.958 12.7655 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9083 1.307 4.2064 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9192 1.000 3.5204 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–45
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.18 10493.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3610 993.39 107.86 30.644

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7506 993.39 107.86 7.043

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.39 99.18 39.224

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1173.05 153.00 88.240

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.39 99.18 39.224

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1335.40 194.66 134.805

Splitter 5.6367 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.39 99.18 39.224

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11109.4 7268.9 15375.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.97 21.07 12.266

LP_Shaft 3675.2 17106.7 11970.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3254 1335.40 194.66 131.701

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4099 1335.40 194.66 73.896

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.40 194.66 134.805

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.40 194.66 134.805

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.40 194.66 134.805

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 552.21 1.37 7.962

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 552.21 1.37 7.962

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 552.21 1.37 7.962

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 552.21 1.37 7.962

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2609.41 0.9995 0.0230 0.99241 0.02098 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.037 0.9811 1.0000 0.9800 613.40 1.000 1526.2 3274.0

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1030.8 13082.8

NASA/TM—2013-218094 G–46
************************************************************************************************************************************ 

Date:05/13/13 Time:10:01:44 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 480.59 Stator 1 exit: 497.03 Stator 2 inlet: 517.20 Stator 2 exit: 525.88 

 Stator 3 inlet: 549.54 Stator 3 exit: 558.12 Stator 4 inlet: 580.49 Stator 4 exit: 588.31 

 Stator 5 inlet: 606.27 Stator 5 exit: 613.59 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.60 

Fan Bypass Relative Humidity 0.33 

LPC Inlet Relative Humidity 1.98 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 406.28 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 468.52 

Additional Water at LPC Exit 0.0001646 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 421.74 5644.0 0.6101 3443.24 5.6907 793.07 25.469 1.269 69.900 2579.5 2426.8 1682.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 421.74 5.170 482.28 -15.41 0.0000 1156.04 3.458 429.85 3526.9 0.7800 1.40064 0.0000871 421.71 0.037 0.0001

FS1 Inlet.Fl_O 421.74 5.170 482.28 -15.41 0.0000 1156.04 4.172 453.57 4168.2 0.5620 1.40064 0.0000871 421.71 0.037 0.0001

FS12 Splitter.Fl_02 358.71 5.167 482.28 -15.41 0.0000 983.75 4.158 453.20 3531.8 0.5658 1.40064 0.0000871 358.68 0.031 0.0001

FS2 Splitter.Fl_01 63.03 5.167 482.28 -15.41 0.0000 172.87 4.670 468.52 830.5 0.3828 1.40064 0.0000871 63.03 0.005 0.0001

FS14 Fan.Fl_O 358.71 7.887 550.56 0.97 0.0000 688.66 6.547 522.04 2606.7 0.5226 1.39975 0.0000871 358.68 0.031 0.0001

FS23 LPC.Fl_O 63.03 12.183 636.10 21.54 0.0000 84.20 11.062 618.86 412.6 0.3741 1.39789 0.0000871 63.03 0.005 0.0001

FS24 VaporIN.Fl_O 63.05 12.183 636.35 20.65 0.0000 84.23 11.061 619.08 412.6 0.3743 1.39786 0.0002517 63.03 0.016 0.0003

FS25 Bleed2.Fl_O 63.05 12.183 636.35 20.65 0.0000 84.23 11.061 619.08 412.6 0.3743 1.39786 0.0002517 63.03 0.016 0.0003

FS3 HPC.Fl_O 59.99 131.669 1325.83 192.16 0.0000 10.70 117.915 1287.56 49.7 0.4054 1.36027 0.0002517 59.97 0.015 0.0003

FS36 Bleed3.Fl_O 46.49 131.669 1325.83 192.16 0.0000 8.30 123.706 1304.07 49.3 0.3040 1.36027 0.0002517 46.48 0.012 0.0003

FS4 Burner.Fl_O 47.45 128.637 2579.48 166.81 0.0206 12.09 121.513 2546.01 74.6 0.2989 1.29386 0.0002517 46.48 0.012 0.0251

FS45 HPT.Fl_O 63.26 29.912 1690.18 3.23 0.0154 56.11 26.913 1646.33 265.4 0.4009 1.32984 0.0002517 62.29 0.016 0.0189

FS49 LPT.Fl_O 64.00 6.875 1205.38 -123.77 0.0152 208.57 5.926 1159.02 860.2 0.4720 1.35725 0.0002517 63.03 0.016 0.0187

FS5 TEGV.Fl_O 64.00 6.875 1205.45 -123.77 0.0152 208.57 5.926 1159.09 860.2 0.4720 1.35725 0.0002517 63.03 0.016 0.0187

FS8 Core_Nozz.Fl_O 64.00 6.875 1205.58 -123.77 0.0152 208.59 3.666 1019.59 613.4 1.0000 1.35724 0.0002517 63.03 0.016 0.0187

FS17 FanDuctLkg.Fl_O 358.71 7.887 550.56 0.97 0.0000 688.66 6.547 522.04 2606.7 0.5226 1.39975 0.0000871 358.68 0.031 0.0001

FS171 Bleed15.Fl_O 358.71 7.887 550.56 0.97 0.0000 688.66 6.362 517.78 2481.9 0.5626 1.39975 0.0000871 358.68 0.031 0.0001

FS172 FanDuct.Fl_O 358.71 7.887 550.56 0.97 0.0000 688.66 6.362 517.78 2481.9 0.5626 1.39975 0.0000871 358.68 0.031 0.0001

FS173 Byp_Nozz.Fl_O 358.71 7.887 550.56 0.97 0.0000 688.66 4.165 458.70 2006.9 1.0000 1.39975 0.0000871 358.68 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.75 1.526 0.9074 3779.750 1.1416 0.9127 -8312.7 73.94 30.77

LPC 172.87 2.358 0.8699 3779.750 1.3189 0.8845 -3295.1 4.57 3.57

HPC 84.23 10.807 0.8615 9988.260 2.0835 0.8979 -14927.3 35.15 33.72

HPT 12.09 4.301 0.9078 217.834 1.3556 0.8883 14927.3 

LPT 56.11 4.351 0.9117 88.654 1.3996 0.8945 11607.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1143.02 1.514 0.9092 3743.710 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.07 2.366 0.8195 0.998 0.0000 1.2430 0.9938 1.0615 0.0003

HPC 76.61 10.345 0.8704 9721.979 12.7004 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.209 0.9078 1.309 4.2091 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9185 0.997 3.5204 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–47
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.88 10395.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3201 987.62 106.41 29.912

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7376 987.62 106.41 6.875

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 953.02 97.83 38.470

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1165.26 151.00 86.264

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 953.02 97.83 38.470

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1325.83 192.16 131.669

Splitter 5.6907 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 953.02 97.83 38.470

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11063.5 7086.4 14927.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 636.35 20.65 12.183

LP_Shaft 3644.7 16727.0 11607.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.1985 1325.83 192.16 128.637

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.2988 1325.83 192.16 72.166

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.83 192.16 131.669

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.83 192.16 131.669

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.83 192.16 131.669

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 550.56 0.97 7.887

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 550.56 0.97 7.887

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 550.56 0.97 7.887

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 550.56 0.97 7.887

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2579.46 0.9995 0.0230 0.95645 0.02058 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.988 0.9808 1.0000 0.9800 613.40 1.000 1517.1 3145.6

Byp_Nozz 2.281 0.9815 1.0000 0.9800 2006.86 1.000 1029.2 12894.1

NASA/TM—2013-218094 G–48
 50μm, ISA +18R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:22:01 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 29/ 57/ 2/26 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 449.01 Stator 1 exit: 467.65 Stator 2 inlet: 489.24 Stator 2 exit: 496.53 

 Stator 3 inlet: 525.31 Stator 3 exit: 533.35 Stator 4 inlet: 560.32 Stator 4 exit: 568.08 

 Stator 5 inlet: 588.96 Stator 5 exit: 596.53 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.11 

Fan Bypass Relative Humidity 0.16 

LPC Inlet Relative Humidity 2.31 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 483.44 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 442.61 

Additional Water at LPC Exit 0.0000127 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 475.58 8100.1 0.5999 4859.43 5.2928 776.30 31.986 1.684 100.000 2818.7 2645.7 1838.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 475.58 5.170 462.10 -19.92 0.0000 1276.02 3.458 411.85 3892.7 0.7800 1.40081 0.0000308 475.57 0.015 0.0000

FS1 Inlet.Fl_O 475.58 5.170 462.10 -19.92 0.0000 1276.02 3.838 424.34 4168.2 0.6662 1.40081 0.0000308 475.57 0.015 0.0000

FS12 Splitter.Fl_02 400.01 5.167 462.10 -19.92 0.0000 1073.78 3.865 425.25 3531.8 0.6574 1.40081 0.0000308 399.99 0.012 0.0000

FS2 Splitter.Fl_01 75.58 5.167 462.10 -19.92 0.0000 202.88 4.445 442.61 830.5 0.4686 1.40081 0.0000308 75.57 0.002 0.0000

FS14 Fan.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.260 516.24 2606.7 0.5226 1.39985 0.0000308 399.99 0.012 0.0000

FS23 LPC.Fl_O 75.58 12.667 625.29 19.26 0.0000 96.27 11.081 601.91 412.6 0.4415 1.39819 0.0000308 75.57 0.002 0.0000

FS24 VaporIN.Fl_O 75.58 12.667 625.36 19.20 0.0000 96.28 11.081 601.98 412.6 0.4415 1.39818 0.0000435 75.57 0.003 0.0000

FS25 Bleed2.Fl_O 75.58 12.667 625.36 19.20 0.0000 96.28 11.081 601.98 412.6 0.4415 1.39818 0.0000435 75.57 0.003 0.0000

FS3 HPC.Fl_O 71.91 165.364 1379.14 207.17 0.0000 10.42 149.116 1342.03 49.7 0.3928 1.35715 0.0000435 71.91 0.003 0.0000

FS36 Bleed3.Fl_O 55.73 165.364 1379.14 207.17 0.0000 8.08 155.925 1357.95 49.3 0.2953 1.35715 0.0000435 55.73 0.002 0.0000

FS4 Burner.Fl_O 57.08 161.556 2818.71 176.88 0.0242 12.10 152.620 2782.93 74.6 0.3003 1.28469 0.0000435 55.73 0.002 0.0292

FS45 HPT.Fl_O 76.04 37.752 1847.45 -1.29 0.0181 55.87 34.006 1801.00 265.4 0.4002 1.32100 0.0000435 74.69 0.003 0.0219

FS49 LPT.Fl_O 76.93 8.678 1323.57 -141.15 0.0179 208.11 7.485 1273.84 860.2 0.4724 1.34812 0.0000435 75.57 0.003 0.0217

FS5 TEGV.Fl_O 76.93 8.678 1323.64 -141.15 0.0179 208.12 7.485 1273.90 860.2 0.4724 1.34811 0.0000435 75.57 0.003 0.0217

FS8 Core_Nozz.Fl_O 76.93 8.678 1323.77 -141.15 0.0179 208.13 4.641 1123.74 613.4 1.0000 1.34810 0.0000435 75.57 0.003 0.0217

FS17 FanDuctLkg.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.260 516.24 2606.7 0.5226 1.39985 0.0000308 399.99 0.012 0.0000

FS171 Bleed15.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.055 512.03 2481.9 0.5625 1.39985 0.0000308 399.99 0.012 0.0000

FS172 FanDuct.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.055 512.03 2481.9 0.5625 1.39985 0.0000308 399.99 0.012 0.0000

FS173 Byp_Nozz.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 4.619 453.60 2006.9 1.0000 1.39985 0.0000308 399.99 0.012 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.78 1.692 0.9109 4120.393 1.1782 0.9173 -11176.3 38.42 23.46

LPC 202.88 2.451 0.8264 4120.393 1.3532 0.8467 -4189.4 2.96 2.22

HPC 96.28 13.055 0.8586 10345.054 2.2053 0.8979 -19611.7 26.28 25.48

HPT 12.10 4.279 0.9118 213.958 1.3469 0.8911 19611.7 

LPT 55.87 4.350 0.9155 90.484 1.3923 0.8986 15365.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.63 1.677 0.9128 4081.106 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.08 2.727 0.8329 1.088 0.0000 1.2289 0.8404 0.9923 0.0003

HPC 87.57 12.487 0.8674 10069.262 13.4722 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.188 0.9118 1.286 4.1885 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9223 1.018 3.5200 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–49
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.74 11474.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7812 1010.15 113.19 37.752

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8842 1010.15 113.19 8.678

TEGV 0.0000 0.4724 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.31 103.79 46.260

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1204.14 162.06 107.339

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.31 103.79 46.260

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1379.14 207.17 165.364

Splitter 5.2928 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.31 103.79 46.260

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11359.4 9067.7 19611.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 625.36 19.20 12.667

LP_Shaft 3889.2 20750.4 15365.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.6293 1379.14 207.17 161.556

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.5509 1379.14 207.17 90.740

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.14 207.17 165.364

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.14 207.17 165.364

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.14 207.17 165.364

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2818.71 0.9995 0.0230 1.34984 0.02422 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.509 0.9810 1.0000 0.9800 613.40 1.000 1587.6 4521.3

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1023.5 15053.8

NASA/TM—2013-218094 G–50
************************************************************************************************************************************ 

Date:07/05/13 Time:09:22:34 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 458.63 Stator 1 exit: 474.87 Stator 2 inlet: 494.60 Stator 2 exit: 502.86 

 Stator 3 inlet: 526.46 Stator 3 exit: 534.71 Stator 4 inlet: 557.04 Stator 4 exit: 564.60 

 Stator 5 inlet: 582.44 Stator 5 exit: 589.57 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.58 

Fan Bypass Relative Humidity 0.24 

LPC Inlet Relative Humidity 1.86 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 414.64 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 447.77 

Additional Water at LPC Exit 0.0000162 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 439.17 6082.8 0.5942 3614.58 5.5824 776.30 26.748 1.342 75.600 2543.5 2391.4 1654.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 439.17 5.170 462.10 -19.92 0.0000 1178.32 3.458 411.85 3594.7 0.7800 1.40081 0.0000308 439.15 0.014 0.0000

FS1 Inlet.Fl_O 439.17 5.170 462.10 -19.92 0.0000 1178.32 4.118 432.98 4168.2 0.5791 1.40081 0.0000308 439.15 0.014 0.0000

FS12 Splitter.Fl_02 372.45 5.167 462.10 -19.92 0.0000 999.81 4.112 432.86 3531.8 0.5805 1.40081 0.0000308 372.44 0.011 0.0000

FS2 Splitter.Fl_01 66.72 5.167 462.10 -19.92 0.0000 179.10 4.629 447.77 830.5 0.3996 1.40081 0.0000308 66.72 0.002 0.0000

FS14 Fan.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.674 503.23 2606.7 0.5226 1.40006 0.0000308 372.44 0.011 0.0000

FS23 LPC.Fl_O 66.72 12.318 612.36 16.15 0.0000 86.49 11.115 594.68 412.6 0.3862 1.39851 0.0000308 66.72 0.002 0.0000

FS24 VaporIN.Fl_O 66.72 12.318 612.43 16.07 0.0000 86.49 11.114 594.74 412.6 0.3863 1.39851 0.0000470 66.72 0.003 0.0000

FS25 Bleed2.Fl_O 66.72 12.318 612.43 16.07 0.0000 86.49 11.114 594.74 412.6 0.3863 1.39851 0.0000470 66.72 0.003 0.0000

FS3 HPC.Fl_O 63.48 138.285 1293.34 184.91 0.0000 10.65 124.000 1256.30 49.7 0.4027 1.36228 0.0000470 63.48 0.003 0.0000

FS36 Bleed3.Fl_O 49.20 138.285 1293.34 184.91 0.0000 8.26 130.009 1272.26 49.3 0.3021 1.36228 0.0000470 49.20 0.002 0.0000

FS4 Burner.Fl_O 50.20 135.100 2543.47 159.94 0.0204 12.09 127.609 2510.33 74.6 0.2988 1.29509 0.0000470 49.20 0.002 0.0247

FS45 HPT.Fl_O 66.94 31.404 1662.23 -1.11 0.0152 56.08 28.260 1619.05 265.4 0.4004 1.33130 0.0000470 65.94 0.003 0.0185

FS49 LPT.Fl_O 67.72 7.206 1183.82 -125.98 0.0150 208.65 6.211 1138.13 860.2 0.4719 1.35873 0.0000470 66.72 0.003 0.0183

FS5 TEGV.Fl_O 67.72 7.206 1183.89 -125.98 0.0150 208.66 6.211 1138.19 860.2 0.4719 1.35873 0.0000470 66.72 0.003 0.0183

FS8 Core_Nozz.Fl_O 67.72 7.206 1184.02 -125.98 0.0150 208.67 3.841 1000.77 613.4 1.0000 1.35872 0.0000470 66.72 0.003 0.0183

FS17 FanDuctLkg.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.674 503.23 2606.7 0.5226 1.40006 0.0000308 372.44 0.011 0.0000

FS171 Bleed15.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.485 499.13 2481.9 0.5625 1.40006 0.0000308 372.44 0.011 0.0000

FS172 FanDuct.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.485 499.13 2481.9 0.5625 1.40006 0.0000308 372.44 0.011 0.0000

FS173 Byp_Nozz.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 4.246 442.16 2006.9 1.0000 1.40006 0.0000308 372.44 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 999.81 1.556 0.9070 3841.927 1.1486 0.9126 -8672.9 62.44 29.36

LPC 179.10 2.384 0.8662 3841.927 1.3252 0.8814 -3404.6 4.01 3.17

HPC 86.49 11.226 0.8614 10052.195 2.1118 0.8984 -15551.3 33.25 31.96

HPT 12.09 4.302 0.9079 216.586 1.3570 0.8887 15551.3 

LPT 56.08 4.358 0.9114 88.946 1.4014 0.8940 12077.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.68 1.543 0.9088 3805.294 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.07 2.430 0.8207 1.015 0.0000 1.2517 0.9680 1.0554 0.0003

HPC 78.67 10.744 0.8703 9784.210 12.8566 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.210 0.9079 1.302 4.2105 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9181 1.001 3.5256 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–51
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.69 10596.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4553 959.07 100.49 31.404

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7806 959.07 100.49 7.206

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.89 92.05 40.031

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1134.62 144.39 90.417

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.89 92.05 40.031

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1293.34 184.91 138.285

Splitter 5.5824 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.89 92.05 40.031

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10923.1 7477.5 15551.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.43 16.07 12.318

LP_Shaft 3626.3 17492.0 12077.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.6180 1293.34 184.91 135.100

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.6659 1293.34 184.91 75.786

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.34 184.91 138.285

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.34 184.91 138.285

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.34 184.91 138.285

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2543.45 0.9995 0.0230 1.00405 0.02041 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.084 0.9813 1.0000 0.9800 613.40 1.000 1503.7 3400.3

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1010.5 13278.9

NASA/TM—2013-218094 G–52
************************************************************************************************************************************ 

Date:07/05/13 Time:09:23:08 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 459.57 Stator 1 exit: 475.57 Stator 2 inlet: 495.09 Stator 2 exit: 503.39 

 Stator 3 inlet: 526.53 Stator 3 exit: 534.77 Stator 4 inlet: 556.65 Stator 4 exit: 564.18 

 Stator 5 inlet: 581.71 Stator 5 exit: 588.79 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.46 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 1.81 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 406.23 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.34 

Additional Water at LPC Exit 0.0000168 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 434.93 5854.9 0.5947 3481.82 5.6326 776.30 26.125 1.304 72.700 2513.1 2363.2 1634.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 434.93 5.170 462.10 -19.92 0.0000 1166.96 3.458 411.85 3560.0 0.7800 1.40081 0.0000308 434.92 0.013 0.0000

FS1 Inlet.Fl_O 434.93 5.170 462.10 -19.92 0.0000 1166.96 4.146 433.81 4168.2 0.5703 1.40081 0.0000308 434.92 0.013 0.0000

FS12 Splitter.Fl_02 369.36 5.167 462.10 -19.92 0.0000 991.51 4.136 433.58 3531.8 0.5728 1.40081 0.0000308 369.35 0.011 0.0000

FS2 Splitter.Fl_01 65.57 5.167 462.10 -19.92 0.0000 176.03 4.649 448.34 830.5 0.3912 1.40081 0.0000308 65.57 0.002 0.0000

FS14 Fan.Fl_O 369.36 7.960 529.11 -3.85 0.0000 688.70 6.608 501.68 2606.7 0.5226 1.40008 0.0000308 369.35 0.011 0.0000

FS23 LPC.Fl_O 65.57 12.254 610.98 15.81 0.0000 85.35 11.092 593.87 412.6 0.3801 1.39855 0.0000308 65.57 0.002 0.0000

FS24 VaporIN.Fl_O 65.58 12.254 611.04 15.73 0.0000 85.36 11.092 593.93 412.6 0.3801 1.39854 0.0000477 65.57 0.003 0.0000

FS25 Bleed2.Fl_O 65.58 12.254 611.04 15.73 0.0000 85.36 11.092 593.93 412.6 0.3801 1.39854 0.0000477 65.57 0.003 0.0000

FS3 HPC.Fl_O 62.40 135.064 1283.78 182.44 0.0000 10.68 121.030 1246.74 49.7 0.4038 1.36287 0.0000477 62.39 0.003 0.0000

FS36 Bleed3.Fl_O 48.36 135.064 1283.78 182.44 0.0000 8.28 126.936 1262.71 49.3 0.3029 1.36287 0.0000477 48.35 0.002 0.0000

FS4 Burner.Fl_O 49.32 131.953 2513.10 158.02 0.0200 12.09 124.635 2480.26 74.6 0.2987 1.29627 0.0000477 48.35 0.002 0.0242

FS45 HPT.Fl_O 65.78 30.657 1642.24 -1.10 0.0149 56.11 27.585 1599.42 265.4 0.4004 1.33248 0.0000477 64.81 0.003 0.0182

FS49 LPT.Fl_O 66.54 7.034 1168.97 -124.33 0.0147 208.71 6.062 1123.73 860.2 0.4718 1.35988 0.0000477 65.57 0.003 0.0180

FS5 TEGV.Fl_O 66.54 7.034 1169.04 -124.33 0.0147 208.72 6.062 1123.79 860.2 0.4718 1.35988 0.0000477 65.57 0.003 0.0180

FS8 Core_Nozz.Fl_O 66.54 7.034 1169.18 -124.33 0.0147 208.73 3.749 987.77 613.4 1.0000 1.35987 0.0000477 65.57 0.003 0.0180

FS17 FanDuctLkg.Fl_O 369.36 7.960 529.11 -3.85 0.0000 688.70 6.608 501.68 2606.7 0.5226 1.40008 0.0000308 369.35 0.011 0.0000

FS171 Bleed15.Fl_O 369.36 7.960 529.11 -3.85 0.0000 688.70 6.421 497.59 2481.9 0.5625 1.40008 0.0000308 369.35 0.011 0.0000

FS172 FanDuct.Fl_O 369.36 7.960 529.11 -3.85 0.0000 688.70 6.421 497.59 2481.9 0.5625 1.40008 0.0000308 369.35 0.011 0.0000

FS173 Byp_Nozz.Fl_O 369.36 7.960 529.11 -3.85 0.0000 688.70 4.204 440.79 2006.9 1.0000 1.40008 0.0000308 369.35 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.51 1.541 0.9070 3810.868 1.1450 0.9125 -8395.8 67.58 30.09

LPC 176.03 2.371 0.8684 3810.868 1.3222 0.8833 -3315.3 4.29 3.38

HPC 85.36 11.022 0.8615 10020.329 2.1010 0.8982 -15091.9 34.11 32.76

HPT 12.09 4.304 0.9073 216.954 1.3579 0.8878 15091.9 

LPT 56.11 4.358 0.9107 88.762 1.4022 0.8932 11711.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.04 1.528 0.9089 3774.531 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.07 2.398 0.8201 1.007 0.0000 1.2478 0.9813 1.0588 0.0003

HPC 77.63 10.550 0.8704 9753.193 12.7857 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.213 0.9073 1.304 4.2126 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9175 0.998 3.5259 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–53
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.02 10494.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4132 953.42 99.09 30.657

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7672 953.42 99.09 7.034

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.65 90.75 39.272

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1126.88 142.43 88.396

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.65 90.75 39.272

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1283.78 182.44 135.064

Splitter 5.6326 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.65 90.75 39.272

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10876.1 7287.9 15091.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 611.04 15.73 12.254

LP_Shaft 3597.0 17099.6 11711.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4874 1283.78 182.44 131.953

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5516 1283.78 182.44 74.012

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.78 182.44 135.064

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.78 182.44 135.064

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.78 182.44 135.064

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.960

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.960

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.960

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.11 -3.85 7.960

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2513.07 0.9995 0.0230 0.96717 0.02000 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.034 0.9811 1.0000 0.9800 613.40 1.000 1494.4 3269.0

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1009.0 13080.1

NASA/TM—2013-218094 G–54
************************************************************************************************************************************ 

Date:07/05/13 Time:09:23:40 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 460.42 Stator 1 exit: 476.16 Stator 2 inlet: 495.46 Stator 2 exit: 503.76 

 

Stator 3 inlet: 526.43 Stator 3 exit: 534.64 Stator 4 inlet: 556.07 Stator 4 exit: 563.55 

 

Stator 5 inlet: 580.77 Stator 5 exit: 587.78 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.36 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 1.77 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 397.98 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.89 

Additional Water at LPC Exit 0.0000173 

 

 

SUMMARY OUTPUT DATA 

 

MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 430.86 5636.4 0.5955 3356.43 5.6862 776.30 25.519 1.267 69.900 2484.3 2336.7 1615.7

 

 

FLOW STATION DATA 

 

W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 430.86 5.170 462.10 -19.92 0.0000 1156.04 3.458 411.85 3526.7 0.7800 1.40081 0.0000308 430.85 0.013 0.0000

FS1 Inlet.Fl_O 430.86 5.170 462.10 -19.92 0.0000 1156.04 4.172 434.59 4168.2 0.5619 1.40081 0.0000308 430.85 0.013 0.0000

FS12 Splitter.Fl_02 366.42 5.167 462.10 -19.92 0.0000 983.64 4.158 434.24 3531.8 0.5656 1.40081 0.0000308 366.41 0.011 0.0000

FS2 Splitter.Fl_01 64.44 5.167 462.10 -19.92 0.0000 172.99 4.670 448.89 830.5 0.3830 1.40081 0.0000308 64.44 0.002 0.0000

FS14 Fan.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.546 500.18 2606.7 0.5226 1.40011 0.0000308 366.41 0.011 0.0000

FS23 LPC.Fl_O 64.44 12.172 609.42 15.44 0.0000 84.33 11.049 592.82 412.6 0.3747 1.39858 0.0000308 64.44 0.002 0.0000

FS24 VaporIN.Fl_O 64.44 12.172 609.49 15.36 0.0000 84.34 11.048 592.89 412.6 0.3747 1.39858 0.0000482 64.44 0.003 0.0000

FS25 Bleed2.Fl_O 64.44 12.172 609.49 15.36 0.0000 84.34 11.048 592.89 412.6 0.3747 1.39858 0.0000482 64.44 0.003 0.0000

FS3 HPC.Fl_O 61.32 131.932 1274.55 180.06 0.0000 10.71 118.149 1237.52 49.7 0.4049 1.36344 0.0000482 61.31 0.003 0.0000

FS36 Bleed3.Fl_O 47.52 131.932 1274.55 180.06 0.0000 8.30 123.952 1253.50 49.3 0.3036 1.36344 0.0000482 47.52 0.002 0.0000

FS4 Burner.Fl_O 48.45 128.894 2484.30 156.16 0.0196 12.09 121.744 2451.73 74.6 0.2985 1.29739 0.0000482 47.52 0.002 0.0238

FS45 HPT.Fl_O 64.62 29.926 1622.95 -1.15 0.0146 56.13 26.924 1580.48 265.4 0.4005 1.33363 0.0000482 63.68 0.003 0.0178

FS49 LPT.Fl_O 65.37 6.867 1154.72 -122.78 0.0145 208.77 5.917 1109.91 860.2 0.4718 1.36099 0.0000482 64.44 0.003 0.0176

FS5 TEGV.Fl_O 65.37 6.867 1154.79 -122.78 0.0145 208.77 5.917 1109.97 860.2 0.4718 1.36098 0.0000482 64.44 0.003 0.0176

FS8 Core_Nozz.Fl_O 65.37 6.867 1154.93 -122.78 0.0145 208.78 3.658 975.31 613.4 1.0000 1.36097 0.0000482 64.44 0.003 0.0177

FS17 FanDuctLkg.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.546 500.18 2606.7 0.5226 1.40011 0.0000308 366.41 0.011 0.0000

FS171 Bleed15.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.361 496.10 2481.9 0.5625 1.40011 0.0000308 366.41 0.011 0.0000

FS172 FanDuct.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.361 496.10 2481.9 0.5625 1.40011 0.0000308 366.41 0.011 0.0000

FS173 Byp_Nozz.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 4.164 439.47 2006.9 1.0000 1.40011 0.0000308 366.41 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 

Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.64 1.526 0.9074 3779.190 1.1416 0.9127 -8132.3 74.07 30.79

LPC 172.99 2.356 0.8699 3779.190 1.3188 0.8845 -3223.8 4.58 3.57

HPC 84.34 10.839 0.8615 9991.665 2.0912 0.8980 -14652.9 34.91 33.49

HPT 12.09 4.307 0.9067 217.306 1.3591 0.8875 14652.9 

LPT 56.13 4.358 0.9100 88.546 1.4029 0.8923 11356.1 

TURBOMACHINERY MAP DATA 

 

WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1142.89 1.514 0.9092 3743.156 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.03 2.366 0.8195 0.998 0.0000 1.2442 0.9926 1.0615 0.0003

HPC 76.71 10.375 0.8704 9725.294 12.7209 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.215 0.9067 1.306 4.2155 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9168 0.996 3.5258 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–55
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.73 10396.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3714 947.85 97.71 29.926

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7540 947.85 97.71 6.867

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.48 89.47 38.519

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1119.37 140.53 86.423

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.48 89.47 38.519

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1274.55 180.06 131.932

Splitter 5.6862 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.48 89.47 38.519

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10831.1 7105.3 14652.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 609.49 15.36 12.172

LP_Shaft 3567.1 16720.3 11356.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3579 1274.55 180.06 128.894

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4384 1274.55 180.06 72.284

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.55 180.06 131.932

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.55 180.06 131.932

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.55 180.06 131.932

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2484.27 0.9995 0.0230 0.93234 0.01962 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.986 0.9808 1.0000 0.9800 613.40 1.000 1485.5 3141.1

Byp_Nozz 2.280 0.9815 1.0000 0.9800 2006.86 1.000 1007.5 12891.3

NASA/TM—2013-218094 G–56
 50μm, ISA +36R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:33:02 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 28/ 56/ 2/25 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 468.73 Stator 1 exit: 488.20 Stator 2 inlet: 510.80 Stator 2 exit: 518.47 

 Stator 3 inlet: 548.50 Stator 3 exit: 556.94 Stator 4 inlet: 585.08 Stator 4 exit: 593.22 

 Stator 5 inlet: 615.02 Stator 5 exit: 622.95 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.34 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 2.54 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 493.57 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 461.98 

Additional Water at LPC Exit 0.0000218 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 465.50 8112.0 0.6156 4993.32 5.2959 793.07 31.925 1.687 100.000 2926.0 2747.3 1915.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 465.50 5.170 482.28 -15.41 0.0000 1275.97 3.458 429.85 3892.8 0.7800 1.40064 0.0000871 465.45 0.041 0.0001

FS1 Inlet.Fl_O 465.50 5.170 482.28 -15.41 0.0000 1275.97 3.838 442.88 4168.2 0.6662 1.40064 0.0000871 465.45 0.041 0.0001

FS12 Splitter.Fl_02 391.56 5.167 482.28 -15.41 0.0000 1073.84 3.865 443.82 3531.8 0.6575 1.40064 0.0000871 391.53 0.034 0.0001

FS2 Splitter.Fl_01 73.94 5.167 482.28 -15.41 0.0000 202.77 4.446 461.98 830.5 0.4683 1.40064 0.0000871 73.93 0.006 0.0001

FS14 Fan.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.260 538.78 2606.7 0.5227 1.39944 0.0000871 391.53 0.034 0.0001

FS23 LPC.Fl_O 73.94 12.695 652.75 25.55 0.0000 96.02 11.116 628.54 412.6 0.4401 1.39742 0.0000871 73.93 0.006 0.0001

FS24 VaporIN.Fl_O 73.94 12.695 652.85 25.45 0.0000 96.03 11.115 628.62 412.6 0.4402 1.39742 0.0001089 73.93 0.008 0.0001

FS25 Bleed2.Fl_O 73.94 12.695 652.85 25.45 0.0000 96.03 11.115 628.62 412.6 0.4402 1.39742 0.0001089 73.93 0.008 0.0001

FS3 HPC.Fl_O 70.35 165.048 1433.33 220.97 0.0000 10.41 148.851 1395.05 49.7 0.3929 1.35405 0.0001089 70.34 0.008 0.0001

FS36 Bleed3.Fl_O 54.52 165.048 1433.33 220.97 0.0000 8.07 155.639 1411.47 49.3 0.2954 1.35405 0.0001089 54.52 0.006 0.0001

FS4 Burner.Fl_O 55.91 161.247 2926.02 188.71 0.0254 12.10 152.351 2889.25 74.6 0.3007 1.28090 0.0001089 54.52 0.006 0.0307

FS45 HPT.Fl_O 74.46 37.749 1924.71 3.74 0.0190 55.84 34.008 1876.78 265.4 0.4006 1.31719 0.0001089 73.06 0.008 0.0231

FS49 LPT.Fl_O 75.32 8.694 1382.59 -142.25 0.0188 207.88 7.501 1331.20 860.2 0.4725 1.34398 0.0001089 73.93 0.008 0.0228

FS5 TEGV.Fl_O 75.32 8.694 1382.65 -142.25 0.0188 207.89 7.501 1331.26 860.2 0.4725 1.34398 0.0001089 73.93 0.008 0.0228

FS8 Core_Nozz.Fl_O 75.32 8.694 1382.78 -142.25 0.0188 207.90 4.655 1175.87 613.4 1.0000 1.34397 0.0001089 73.93 0.008 0.0228

FS17 FanDuctLkg.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.260 538.78 2606.7 0.5227 1.39944 0.0000871 391.53 0.034 0.0001

FS171 Bleed15.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.055 534.39 2481.9 0.5626 1.39944 0.0000871 391.53 0.034 0.0001

FS172 FanDuct.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.055 534.39 2481.9 0.5626 1.39944 0.0000871 391.53 0.034 0.0001

FS173 Byp_Nozz.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 4.619 473.44 2006.9 1.0000 1.39944 0.0000871 391.53 0.034 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.84 1.693 0.9109 4120.680 1.1782 0.9173 -11420.7 38.39 23.45

LPC 202.77 2.457 0.8274 4120.680 1.3535 0.8476 -4284.9 2.96 2.22

HPC 96.03 13.001 0.8587 10334.499 2.1955 0.8978 -19957.2 26.49 25.69

HPT 12.10 4.272 0.9122 214.344 1.3425 0.8900 19957.2 

LPT 55.84 4.342 0.9168 90.571 1.3886 0.9005 15704.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.70 1.677 0.9128 4081.390 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.11 2.727 0.8329 1.088 0.0000 1.2281 0.8435 0.9934 0.0003

HPC 87.33 12.435 0.8675 10058.988 13.4512 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1808 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.514 0.9236 1.019 3.5136 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–57
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.76 11474.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7209 1051.78 123.21 37.749

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8651 1051.78 123.21 8.694

TEGV 0.0000 0.4725 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.62 113.43 46.213

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1252.44 174.04 107.154

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.62 113.43 46.213

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1433.33 220.97 165.048

Splitter 5.2959 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.62 113.43 46.213

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11594.4 9040.3 19957.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 652.85 25.45 12.695

LP_Shaft 3973.5 20757.7 15704.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.4422 1433.33 220.97 161.247

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.3871 1433.33 220.97 90.606

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.33 220.97 165.048

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.33 220.97 165.048

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.33 220.97 165.048

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2926.02 0.9995 0.0230 1.38703 0.02544 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.514 0.9810 1.0000 0.9800 613.40 1.000 1621.7 4530.9

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1045.6 15055.3

NASA/TM—2013-218094 G–58
************************************************************************************************************************************ 

Date:07/05/13 Time:09:33:34 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 478.71 Stator 1 exit: 495.67 Stator 2 inlet: 516.27 Stator 2 exit: 524.91 

 Stator 3 inlet: 549.55 Stator 3 exit: 558.17 Stator 4 inlet: 581.47 Stator 4 exit: 589.37 

 Stator 5 inlet: 607.99 Stator 5 exit: 615.44 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.82 

Fan Bypass Relative Humidity 0.30 

LPC Inlet Relative Humidity 2.07 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 423.38 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.34 

Additional Water at LPC Exit 0.0000290 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 429.86 6089.9 0.6090 3708.85 5.5854 793.07 26.696 1.344 75.600 2640.6 2483.3 1723.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 429.86 5.170 482.28 -15.41 0.0000 1178.29 3.458 429.85 3594.7 0.7800 1.40064 0.0000871 429.82 0.037 0.0001

FS1 Inlet.Fl_O 429.86 5.170 482.28 -15.41 0.0000 1178.29 4.118 451.90 4168.2 0.5792 1.40064 0.0000871 429.82 0.037 0.0001

FS12 Splitter.Fl_02 364.58 5.167 482.28 -15.41 0.0000 999.86 4.112 451.76 3531.8 0.5806 1.40064 0.0000871 364.55 0.032 0.0001

FS2 Splitter.Fl_01 65.27 5.167 482.28 -15.41 0.0000 179.01 4.629 467.34 830.5 0.3994 1.40064 0.0000871 65.27 0.006 0.0001

FS14 Fan.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.674 525.21 2606.7 0.5226 1.39969 0.0000871 364.55 0.032 0.0001

FS23 LPC.Fl_O 65.27 12.327 639.13 22.27 0.0000 86.38 11.126 620.74 412.6 0.3858 1.39781 0.0000871 65.27 0.006 0.0001

FS24 VaporIN.Fl_O 65.28 12.327 639.22 22.13 0.0000 86.39 11.125 620.83 412.6 0.3858 1.39780 0.0001161 65.27 0.008 0.0001

FS25 Bleed2.Fl_O 65.28 12.327 639.22 22.13 0.0000 86.39 11.125 620.83 412.6 0.3858 1.39780 0.0001161 65.27 0.008 0.0001

FS3 HPC.Fl_O 62.11 138.015 1345.00 197.89 0.0000 10.65 123.763 1306.74 49.7 0.4030 1.35914 0.0001161 62.10 0.007 0.0001

FS36 Bleed3.Fl_O 48.14 138.015 1345.00 197.89 0.0000 8.25 129.759 1323.24 49.3 0.3024 1.35914 0.0001161 48.13 0.006 0.0001

FS4 Burner.Fl_O 49.17 134.836 2640.65 171.37 0.0214 12.09 127.373 2606.59 74.6 0.2992 1.29155 0.0001161 48.13 0.006 0.0259

FS45 HPT.Fl_O 65.54 31.391 1731.00 3.97 0.0160 56.06 28.250 1686.42 265.4 0.4008 1.32754 0.0001161 64.51 0.007 0.0195

FS49 LPT.Fl_O 66.31 7.216 1235.80 -126.37 0.0158 208.46 6.221 1188.56 860.2 0.4720 1.35495 0.0001161 65.27 0.008 0.0193

FS5 TEGV.Fl_O 66.31 7.216 1235.87 -126.37 0.0158 208.46 6.221 1188.62 860.2 0.4720 1.35494 0.0001161 65.27 0.008 0.0193

FS8 Core_Nozz.Fl_O 66.31 7.216 1236.00 -126.37 0.0158 208.47 3.851 1046.30 613.4 1.0000 1.35493 0.0001161 65.27 0.008 0.0193

FS17 FanDuctLkg.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.674 525.21 2606.7 0.5226 1.39969 0.0000871 364.55 0.032 0.0001

FS171 Bleed15.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.486 520.93 2481.9 0.5626 1.39969 0.0000871 364.55 0.032 0.0001

FS172 FanDuct.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.486 520.93 2481.9 0.5626 1.39969 0.0000871 364.55 0.032 0.0001

FS173 Byp_Nozz.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 4.246 461.49 2006.9 1.0000 1.39969 0.0000871 364.55 0.032 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 999.86 1.556 0.9070 3842.192 1.1485 0.9126 -8862.8 62.42 29.35

LPC 179.01 2.386 0.8662 3842.192 1.3252 0.8814 -3479.7 4.01 3.17

HPC 86.39 11.196 0.8615 10049.022 2.1041 0.8982 -15839.3 33.47 32.17 

HPT 12.09 4.295 0.9089 217.095 1.3535 0.8892 15839.3 

LPT 56.06 4.351 0.9129 89.050 1.3979 0.8960 12342.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.74 1.543 0.9088 3805.558 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.09 2.430 0.8208 1.015 0.0000 1.2510 0.9690 1.0554 0.0003

HPC 78.57 10.716 0.8704 9781.122 12.8375 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.204 0.9089 1.305 4.2040 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9197 1.002 3.5200 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–59
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.74 10595.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4022 999.02 110.01 31.391

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7637 999.02 110.01 7.216

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.60 101.22 39.978

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1180.79 155.70 90.253

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.60 101.22 39.978

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1345.00 197.89 138.015

Splitter 5.5854 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.60 101.22 39.978

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11155.9 7457.0 15839.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 639.22 22.13 12.327

LP_Shaft 3704.9 17496.6 12342.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4533 1345.00 197.89 134.836

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5218 1345.00 197.89 75.666

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1345.00 197.89 138.015

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1345.00 197.89 138.015

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1345.00 197.89 138.015

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2640.63 0.9995 0.0230 1.03024 0.02141 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.087 0.9813 1.0000 0.9800 613.40 1.000 1535.6 3405.5

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1032.4 13280.1

NASA/TM—2013-218094 G–60
************************************************************************************************************************************ 

Date:07/05/13 Time:09:34:07 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 479.68 Stator 1 exit: 496.38 Stator 2 inlet: 516.78 Stator 2 exit: 525.46 

 Stator 3 inlet: 549.60 Stator 3 exit: 558.22 Stator 4 inlet: 581.05 Stator 4 exit: 588.92 

 Stator 5 inlet: 607.22 Stator 5 exit: 614.61 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.70 

Fan Bypass Relative Humidity 0.31 

LPC Inlet Relative Humidity 2.02 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 414.83 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.94 

Additional Water at LPC Exit 0.0000300 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 425.73 5861.8 0.6094 3572.28 5.6353 793.07 26.076 1.306 72.700 2609.1 2454.2 1702.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 425.73 5.170 482.28 -15.41 0.0000 1166.96 3.458 429.85 3560.2 0.7800 1.40064 0.0000871 425.69 0.037 0.0001

FS1 Inlet.Fl_O 425.73 5.170 482.28 -15.41 0.0000 1166.96 4.146 452.76 4168.2 0.5703 1.40064 0.0000871 425.69 0.037 0.0001

FS12 Splitter.Fl_02 361.57 5.167 482.28 -15.41 0.0000 991.59 4.136 452.51 3531.8 0.5729 1.40064 0.0000871 361.54 0.031 0.0001

FS2 Splitter.Fl_01 64.16 5.167 482.28 -15.41 0.0000 175.96 4.650 467.94 830.5 0.3911 1.40064 0.0000871 64.16 0.006 0.0001

FS14 Fan.Fl_O 361.57 7.961 552.20 1.36 0.0000 688.66 6.609 523.60 2606.7 0.5226 1.39972 0.0000871 361.54 0.031 0.0001

FS23 LPC.Fl_O 64.16 12.263 637.67 21.92 0.0000 85.26 11.102 619.88 412.6 0.3797 1.39785 0.0000871 64.16 0.006 0.0001

FS24 VaporIN.Fl_O 64.16 12.263 637.77 21.77 0.0000 85.27 11.102 619.97 412.6 0.3798 1.39784 0.0001171 64.16 0.008 0.0001

FS25 Bleed2.Fl_O 64.16 12.263 637.77 21.77 0.0000 85.27 11.102 619.97 412.6 0.3798 1.39784 0.0001171 64.16 0.008 0.0001

FS3 HPC.Fl_O 61.05 134.810 1335.15 195.32 0.0000 10.68 120.807 1296.89 49.7 0.4042 1.35973 0.0001171 61.04 0.007 0.0001

FS36 Bleed3.Fl_O 47.31 134.810 1335.15 195.32 0.0000 8.28 126.701 1313.38 49.3 0.3032 1.35973 0.0001171 47.31 0.006 0.0001

FS4 Burner.Fl_O 48.31 131.706 2609.14 169.41 0.0210 12.09 124.416 2575.38 74.6 0.2990 1.29275 0.0001171 47.31 0.006 0.0254

FS45 HPT.Fl_O 64.40 30.645 1709.93 3.99 0.0157 56.08 27.576 1665.75 265.4 0.4009 1.32873 0.0001171 63.40 0.007 0.0191

FS49 LPT.Fl_O 65.16 7.043 1220.00 -124.64 0.0155 208.52 6.071 1173.22 860.2 0.4720 1.35615 0.0001171 64.16 0.008 0.0189

FS5 TEGV.Fl_O 65.16 7.043 1220.07 -124.64 0.0155 208.52 6.071 1173.28 860.2 0.4720 1.35615 0.0001171 64.16 0.008 0.0189

FS8 Core_Nozz.Fl_O 65.16 7.043 1220.21 -124.64 0.0155 208.53 3.757 1032.42 613.4 1.0000 1.35614 0.0001171 64.16 0.008 0.0189

FS17 FanDuctLkg.Fl_O 361.57 7.961 552.20 1.36 0.0000 688.66 6.609 523.60 2606.7 0.5226 1.39972 0.0000871 361.54 0.031 0.0001

FS171 Bleed15.Fl_O 361.57 7.961 552.20 1.36 0.0000 688.66 6.422 519.33 2481.9 0.5626 1.39972 0.0000871 361.54 0.031 0.0001

FS172 FanDuct.Fl_O 361.57 7.961 552.20 1.36 0.0000 688.66 6.422 519.33 2481.9 0.5626 1.39972 0.0000871 361.54 0.031 0.0001

FS173 Byp_Nozz.Fl_O 361.57 7.961 552.20 1.36 0.0000 688.66 4.205 460.08 2006.9 1.0000 1.39972 0.0000871 361.54 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.59 1.541 0.9070 3811.247 1.1450 0.9125 -8580.7 67.50 30.08

LPC 175.96 2.373 0.8684 3811.247 1.3222 0.8833 -3388.4 4.29 3.38

HPC 85.27 10.994 0.8615 10017.451 2.0935 0.8980 -15373.6 34.33 32.97

HPT 12.09 4.298 0.9083 217.467 1.3546 0.8888 15373.6 

LPT 56.08 4.351 0.9124 88.875 1.3989 0.8953 11969.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.13 1.528 0.9089 3774.907 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.09 2.398 0.8201 1.007 0.0000 1.2471 0.9822 1.0589 0.0003

HPC 77.55 10.523 0.8704 9750.393 12.7668 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9083 1.307 4.2064 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9192 1.000 3.5206 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–61
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.21 10494.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3612 993.17 108.55 30.645

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7507 993.17 108.55 7.043

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.17 99.87 39.223

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1172.81 153.67 88.242

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.17 99.87 39.223

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1335.15 195.32 134.810

Splitter 5.6353 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.17 99.87 39.223

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11108.2 7268.9 15373.6 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.77 21.77 12.263

LP_Shaft 3675.1 17105.2 11969.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3261 1335.15 195.32 131.706

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4105 1335.15 195.32 73.899

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.15 195.32 134.810

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.15 195.32 134.810

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.15 195.32 134.810

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2609.12 0.9995 0.0230 0.99230 0.02097 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.037 0.9811 1.0000 0.9800 613.40 1.000 1526.0 3273.7

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1030.8 13082.0

NASA/TM—2013-218094 G–62
************************************************************************************************************************************ 

Date:07/05/13 Time:09:34:37 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 31/ 1/15 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 480.57 Stator 1 exit: 497.00 Stator 2 inlet: 517.17 Stator 2 exit: 525.85 

 Stator 3 inlet: 549.50 Stator 3 exit: 558.08 Stator 4 inlet: 580.46 Stator 4 exit: 588.27 

 Stator 5 inlet: 606.24 Stator 5 exit: 613.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.60 

Fan Bypass Relative Humidity 0.33 

LPC Inlet Relative Humidity 1.98 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 406.39 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 468.51 

Additional Water at LPC Exit 0.0000311 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 421.75 5642.9 0.6101 3442.82 5.6892 793.07 25.469 1.269 69.900 2579.2 2426.5 1682.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 421.75 5.170 482.28 -15.41 0.0000 1156.05 3.458 429.85 3526.9 0.7800 1.40064 0.0000871 421.71 0.037 0.0001

FS1 Inlet.Fl_O 421.75 5.170 482.28 -15.41 0.0000 1156.05 4.172 453.57 4168.2 0.5620 1.40064 0.0000871 421.71 0.037 0.0001

FS12 Splitter.Fl_02 358.70 5.167 482.28 -15.41 0.0000 983.72 4.158 453.21 3531.8 0.5658 1.40064 0.0000871 358.67 0.031 0.0001

FS2 Splitter.Fl_01 63.05 5.167 482.28 -15.41 0.0000 172.91 4.670 468.51 830.5 0.3829 1.40064 0.0000871 63.04 0.005 0.0001

FS14 Fan.Fl_O 358.70 7.886 550.55 0.97 0.0000 688.66 6.547 522.03 2606.7 0.5226 1.39975 0.0000871 358.67 0.031 0.0001

FS23 LPC.Fl_O 63.05 12.180 636.05 21.53 0.0000 84.24 11.058 618.79 412.6 0.3743 1.39789 0.0000871 63.04 0.005 0.0001

FS24 VaporIN.Fl_O 63.05 12.180 636.14 21.37 0.0000 84.25 11.058 618.88 412.6 0.3743 1.39789 0.0001182 63.04 0.007 0.0001

FS25 Bleed2.Fl_O 63.05 12.180 636.14 21.37 0.0000 84.25 11.058 618.88 412.6 0.3743 1.39789 0.0001182 63.04 0.007 0.0001

FS3 HPC.Fl_O 59.99 131.672 1325.58 192.84 0.0000 10.70 117.920 1287.32 49.7 0.4054 1.36031 0.0001182 59.99 0.007 0.0001

FS36 Bleed3.Fl_O 46.49 131.672 1325.58 192.84 0.0000 8.30 123.710 1303.83 49.3 0.3039 1.36031 0.0001182 46.49 0.005 0.0001

FS4 Burner.Fl_O 47.45 128.640 2579.17 167.48 0.0206 12.09 121.517 2545.70 74.6 0.2988 1.29390 0.0001182 46.49 0.005 0.0250

FS45 HPT.Fl_O 63.27 29.912 1689.91 3.94 0.0153 56.11 26.913 1646.07 265.4 0.4009 1.32988 0.0001182 62.31 0.007 0.0188

FS49 LPT.Fl_O 64.01 6.874 1205.14 -123.03 0.0152 208.58 5.925 1158.79 860.2 0.4720 1.35729 0.0001182 63.04 0.007 0.0186

FS5 TEGV.Fl_O 64.01 6.874 1205.21 -123.03 0.0152 208.59 5.925 1158.85 860.2 0.4720 1.35728 0.0001182 63.04 0.007 0.0186

FS8 Core_Nozz.Fl_O 64.01 6.874 1205.34 -123.03 0.0152 208.60 3.666 1019.37 613.4 1.0000 1.35727 0.0001182 63.04 0.007 0.0186

FS17 FanDuctLkg.Fl_O 358.70 7.886 550.55 0.97 0.0000 688.66 6.547 522.03 2606.7 0.5226 1.39975 0.0000871 358.67 0.031 0.0001

FS171 Bleed15.Fl_O 358.70 7.886 550.55 0.97 0.0000 688.66 6.362 517.77 2481.9 0.5626 1.39975 0.0000871 358.67 0.031 0.0001

FS172 FanDuct.Fl_O 358.70 7.886 550.55 0.97 0.0000 688.66 6.362 517.77 2481.9 0.5626 1.39975 0.0000871 358.67 0.031 0.0001

FS173 Byp_Nozz.Fl_O 358.70 7.886 550.55 0.97 0.0000 688.66 4.165 458.70 2006.9 1.0000 1.39975 0.0000871 358.67 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.72 1.526 0.9074 3779.613 1.1416 0.9127 -8311.6 73.97 30.78

LPC 172.91 2.357 0.8699 3779.613 1.3188 0.8845 -3294.8 4.57 3.57

HPC 84.25 10.810 0.8615 9988.697 2.0838 0.8979 -14925.5 35.13 33.71

HPT 12.09 4.301 0.9078 217.822 1.3557 0.8883 14925.5 

LPT 56.11 4.351 0.9117 88.658 1.3996 0.8945 11606.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1142.98 1.514 0.9092 3743.575 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.06 2.366 0.8195 0.998 0.0000 1.2433 0.9935 1.0615 0.0003

HPC 76.62 10.348 0.8704 9722.405 12.7017 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.209 0.9078 1.309 4.2092 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9185 0.997 3.5206 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–63
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.90 10395.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3203 987.39 107.11 29.912

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7377 987.39 107.11 6.874

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 952.79 98.53 38.468

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1165.02 151.69 86.265

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 952.79 98.53 38.468

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1325.58 192.84 131.672

Splitter 5.6892 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 952.79 98.53 38.468

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11062.2 7086.3 14925.5 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 636.14 21.37 12.180

LP_Shaft 3644.6 16725.6 11606.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.1992 1325.58 192.84 128.640

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.2994 1325.58 192.84 72.167

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.58 192.84 131.672

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.58 192.84 131.672

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.58 192.84 131.672

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2579.15 0.9995 0.0230 0.95634 0.02057 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.988 0.9808 1.0000 0.9800 613.40 1.000 1516.9 3145.3

Byp_Nozz 2.281 0.9815 1.0000 0.9800 2006.86 1.000 1029.2 12893.3

NASA/TM—2013-218094 G–64
 100μm, ISA +18R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:45:29 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 27/ 41/ 1/25 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 449.01 Stator 1 exit: 467.64 Stator 2 inlet: 489.24 Stator 2 exit: 496.53 

 Stator 3 inlet: 525.31 Stator 3 exit: 533.35 Stator 4 inlet: 560.32 Stator 4 exit: 568.08 

 Stator 5 inlet: 588.96 Stator 5 exit: 596.53 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.11 

Fan Bypass Relative Humidity 0.16 

LPC Inlet Relative Humidity 2.31 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 483.45 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 442.61 

Additional Water at LPC Exit 0.0000058 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 475.58 8100.2 0.5999 4859.48 5.2927 776.30 31.986 1.684 100.000 2818.7 2645.7 1838.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 475.58 5.170 462.10 -19.92 0.0000 1276.02 3.458 411.85 3892.8 0.7800 1.40081 0.0000308 475.57 0.015 0.0000

FS1 Inlet.Fl_O 475.58 5.170 462.10 -19.92 0.0000 1276.02 3.838 424.34 4168.2 0.6662 1.40081 0.0000308 475.57 0.015 0.0000

FS12 Splitter.Fl_02 400.01 5.167 462.10 -19.92 0.0000 1073.78 3.865 425.25 3531.8 0.6574 1.40081 0.0000308 399.99 0.012 0.0000

FS2 Splitter.Fl_01 75.58 5.167 462.10 -19.92 0.0000 202.88 4.445 442.61 830.5 0.4686 1.40081 0.0000308 75.57 0.002 0.0000

FS14 Fan.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.260 516.24 2606.7 0.5226 1.39985 0.0000308 399.99 0.012 0.0000

FS23 LPC.Fl_O 75.58 12.667 625.30 19.26 0.0000 96.28 11.081 601.92 412.6 0.4415 1.39819 0.0000308 75.57 0.002 0.0000

FS24 VaporIN.Fl_O 75.58 12.667 625.36 19.24 0.0000 96.28 11.081 601.98 412.6 0.4415 1.39818 0.0000366 75.57 0.003 0.0000

FS25 Bleed2.Fl_O 75.58 12.667 625.36 19.24 0.0000 96.28 11.081 601.98 412.6 0.4415 1.39818 0.0000366 75.57 0.003 0.0000

FS3 HPC.Fl_O 71.91 165.367 1379.15 207.21 0.0000 10.42 149.119 1342.04 49.7 0.3928 1.35715 0.0000366 71.91 0.003 0.0000

FS36 Bleed3.Fl_O 55.73 165.367 1379.15 207.21 0.0000 8.08 155.928 1357.96 49.3 0.2953 1.35715 0.0000366 55.73 0.002 0.0000

FS4 Burner.Fl_O 57.08 161.558 2818.73 176.92 0.0242 12.10 152.623 2782.95 74.6 0.3003 1.28469 0.0000366 55.73 0.002 0.0292

FS45 HPT.Fl_O 76.04 37.753 1847.47 -1.25 0.0181 55.87 34.007 1801.01 265.4 0.4002 1.32100 0.0000366 74.69 0.003 0.0219

FS49 LPT.Fl_O 76.93 8.678 1323.58 -141.11 0.0179 208.11 7.485 1273.85 860.2 0.4724 1.34812 0.0000366 75.57 0.003 0.0217

FS5 TEGV.Fl_O 76.93 8.678 1323.65 -141.11 0.0179 208.12 7.485 1273.91 860.2 0.4724 1.34811 0.0000366 75.57 0.003 0.0217

FS8 Core_Nozz.Fl_O 76.93 8.678 1323.78 -141.11 0.0179 208.13 4.641 1123.74 613.4 1.0000 1.34810 0.0000366 75.57 0.003 0.0217

FS17 FanDuctLkg.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.260 516.24 2606.7 0.5226 1.39985 0.0000308 399.99 0.012 0.0000

FS171 Bleed15.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.055 512.03 2481.9 0.5625 1.39985 0.0000308 399.99 0.012 0.0000

FS172 FanDuct.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 7.055 512.03 2481.9 0.5625 1.39985 0.0000308 399.99 0.012 0.0000

FS173 Byp_Nozz.Fl_O 400.01 8.745 544.45 -0.17 0.0000 688.68 4.619 453.60 2006.9 1.0000 1.39985 0.0000308 399.99 0.012 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.78 1.692 0.9109 4120.398 1.1782 0.9173 -11176.3 38.42 23.46

LPC 202.88 2.451 0.8264 4120.398 1.3532 0.8467 -4189.7 2.96 2.22

HPC 96.28 13.055 0.8586 10345.089 2.2054 0.8979 -19611.9 26.28 25.48

HPT 12.10 4.279 0.9118 213.958 1.3469 0.8911 19611.9 

LPT 55.87 4.351 0.9155 90.484 1.3923 0.8986 15365.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.63 1.677 0.9128 4081.111 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.08 2.727 0.8329 1.088 0.0000 1.2290 0.8404 0.9922 0.0003

HPC 87.57 12.487 0.8674 10069.296 13.4723 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.188 0.9118 1.286 4.1885 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9223 1.018 3.5200 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–65
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.75 11475.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7812 1010.15 113.23 37.753

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8843 1010.15 113.23 8.678

TEGV 0.0000 0.4724 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.32 103.83 46.261

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1204.15 162.10 107.341

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.32 103.83 46.261

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1379.15 207.21 165.367

Splitter 5.2927 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.32 103.83 46.261

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11359.4 9067.7 19611.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 625.36 19.24 12.667

LP_Shaft 3889.2 20750.7 15365.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.6294 1379.15 207.21 161.558

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.5509 1379.15 207.21 90.742

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.15 207.21 165.367

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.15 207.21 165.367

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1379.15 207.21 165.367

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 544.45 -0.17 8.745

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2818.73 0.9995 0.0230 1.34986 0.02422 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.509 0.9810 1.0000 0.9800 613.40 1.000 1587.6 4521.3

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1023.5 15053.9

NASA/TM—2013-218094 G–66
************************************************************************************************************************************ 

Date:07/05/13 Time:09:46:02 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 458.63 Stator 1 exit: 474.88 Stator 2 inlet: 494.60 Stator 2 exit: 502.86 

 Stator 3 inlet: 526.47 Stator 3 exit: 534.71 Stator 4 inlet: 557.05 Stator 4 exit: 564.61 

 Stator 5 inlet: 582.45 Stator 5 exit: 589.57 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.58 

Fan Bypass Relative Humidity 0.24 

LPC Inlet Relative Humidity 1.86 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 414.64 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 447.77 

Additional Water at LPC Exit 0.0000060 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 439.17 6082.8 0.5942 3614.67 5.5824 776.30 26.748 1.342 75.600 2543.5 2391.4 1654.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 439.17 5.170 462.10 -19.92 0.0000 1178.32 3.458 411.85 3594.7 0.7800 1.40081 0.0000308 439.15 0.014 0.0000

FS1 Inlet.Fl_O 439.17 5.170 462.10 -19.92 0.0000 1178.32 4.118 432.98 4168.2 0.5791 1.40081 0.0000308 439.15 0.014 0.0000

FS12 Splitter.Fl_02 372.45 5.167 462.10 -19.92 0.0000 999.81 4.112 432.86 3531.8 0.5805 1.40081 0.0000308 372.44 0.011 0.0000

FS2 Splitter.Fl_01 66.72 5.167 462.10 -19.92 0.0000 179.10 4.629 447.77 830.5 0.3996 1.40081 0.0000308 66.72 0.002 0.0000

FS14 Fan.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.674 503.23 2606.7 0.5226 1.40006 0.0000308 372.44 0.011 0.0000

FS23 LPC.Fl_O 66.72 12.317 612.36 16.15 0.0000 86.49 11.114 594.67 412.6 0.3863 1.39851 0.0000308 66.72 0.002 0.0000

FS24 VaporIN.Fl_O 66.72 12.317 612.42 16.13 0.0000 86.50 11.114 594.73 412.6 0.3863 1.39851 0.0000368 66.72 0.002 0.0000

FS25 Bleed2.Fl_O 66.72 12.317 612.42 16.13 0.0000 86.50 11.114 594.73 412.6 0.3863 1.39851 0.0000368 66.72 0.002 0.0000

FS3 HPC.Fl_O 63.48 138.286 1293.35 184.97 0.0000 10.65 124.002 1256.31 49.7 0.4027 1.36228 0.0000368 63.48 0.002 0.0000

FS36 Bleed3.Fl_O 49.20 138.286 1293.35 184.97 0.0000 8.26 130.011 1272.27 49.3 0.3021 1.36228 0.0000368 49.20 0.002 0.0000

FS4 Burner.Fl_O 50.20 135.101 2543.52 159.99 0.0204 12.09 127.611 2510.39 74.6 0.2988 1.29509 0.0000368 49.20 0.002 0.0247

FS45 HPT.Fl_O 66.94 31.404 1662.26 -1.05 0.0152 56.08 28.260 1619.08 265.4 0.4004 1.33130 0.0000368 65.94 0.002 0.0185

FS49 LPT.Fl_O 67.72 7.206 1183.84 -125.93 0.0150 208.65 6.211 1138.15 860.2 0.4719 1.35873 0.0000368 66.72 0.002 0.0183

FS5 TEGV.Fl_O 67.72 7.206 1183.91 -125.93 0.0150 208.66 6.211 1138.21 860.2 0.4719 1.35873 0.0000368 66.72 0.002 0.0183

FS8 Core_Nozz.Fl_O 67.72 7.206 1184.04 -125.93 0.0150 208.67 3.842 1000.78 613.4 1.0000 1.35872 0.0000368 66.72 0.002 0.0183

FS17 FanDuctLkg.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.674 503.23 2606.7 0.5226 1.40006 0.0000308 372.44 0.011 0.0000

FS171 Bleed15.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.485 499.13 2481.9 0.5625 1.40006 0.0000308 372.44 0.011 0.0000

FS172 FanDuct.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 6.485 499.13 2481.9 0.5625 1.40006 0.0000308 372.44 0.011 0.0000

FS173 Byp_Nozz.Fl_O 372.45 8.040 530.74 -3.46 0.0000 688.70 4.246 442.16 2006.9 1.0000 1.40006 0.0000308 372.44 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 999.81 1.556 0.9070 3841.924 1.1486 0.9126 -8672.8 62.44 29.36

LPC 179.10 2.384 0.8661 3841.924 1.3252 0.8813 -3404.7 4.01 3.17

HPC 86.50 11.227 0.8614 10052.335 2.1119 0.8984 -15551.5 33.25 31.96

HPT 12.09 4.302 0.9079 216.585 1.3570 0.8887 15551.5 

LPT 56.08 4.358 0.9114 88.945 1.4014 0.8940 12077.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.68 1.543 0.9088 3805.291 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.07 2.430 0.8207 1.015 0.0000 1.2519 0.9679 1.0553 0.0003

HPC 78.67 10.745 0.8703 9784.346 12.8567 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.210 0.9079 1.302 4.2105 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9181 1.001 3.5256 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–67
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.69 10596.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4552 959.07 100.55 31.404

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7806 959.07 100.55 7.206

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.89 92.11 40.030

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1134.62 144.45 90.418 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.89 92.11 40.030

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1293.35 184.97 138.286

Splitter 5.5824 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.89 92.11 40.030

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10923.1 7477.5 15551.5 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.42 16.13 12.317

LP_Shaft 3626.3 17492.2 12077.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.6179 1293.35 184.97 135.101

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.6659 1293.35 184.97 75.787

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.35 184.97 138.286

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.35 184.97 138.286

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1293.35 184.97 138.286

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 530.74 -3.46 8.040

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2543.50 0.9995 0.0230 1.00407 0.02041 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.084 0.9813 1.0000 0.9800 613.40 1.000 1503.7 3400.3

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1010.5 13278.8

NASA/TM—2013-218094 G–68
************************************************************************************************************************************ 

Date:07/05/13 Time:09:46:35 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 459.57 Stator 1 exit: 475.56 Stator 2 inlet: 495.09 Stator 2 exit: 503.39 

 Stator 3 inlet: 526.52 Stator 3 exit: 534.76 Stator 4 inlet: 556.65 Stator 4 exit: 564.18 

 Stator 5 inlet: 581.71 Stator 5 exit: 588.79 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.46 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 1.81 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 406.24 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.34 

Additional Water at LPC Exit 0.0000060 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 434.93 5854.8 0.5947 3481.75 5.6325 776.30 26.125 1.304 72.700 2513.1 2363.2 1634.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 434.93 5.170 462.10 -19.92 0.0000 1166.95 3.458 411.85 3560.0 0.7800 1.40081 0.0000308 434.92 0.013 0.0000

FS1 Inlet.Fl_O 434.93 5.170 462.10 -19.92 0.0000 1166.95 4.146 433.81 4168.2 0.5703 1.40081 0.0000308 434.92 0.013 0.0000

FS12 Splitter.Fl_02 369.35 5.167 462.10 -19.92 0.0000 991.50 4.136 433.58 3531.8 0.5728 1.40081 0.0000308 369.34 0.011 0.0000

FS2 Splitter.Fl_01 65.58 5.167 462.10 -19.92 0.0000 176.03 4.649 448.34 830.5 0.3912 1.40081 0.0000308 65.57 0.002 0.0000

FS14 Fan.Fl_O 369.35 7.960 529.10 -3.85 0.0000 688.70 6.608 501.68 2606.7 0.5226 1.40008 0.0000308 369.34 0.011 0.0000

FS23 LPC.Fl_O 65.58 12.254 610.98 15.81 0.0000 85.35 11.092 593.87 412.6 0.3801 1.39855 0.0000308 65.57 0.002 0.0000

FS24 VaporIN.Fl_O 65.58 12.254 611.03 15.79 0.0000 85.36 11.092 593.92 412.6 0.3801 1.39854 0.0000368 65.57 0.002 0.0000

FS25 Bleed2.Fl_O 65.58 12.254 611.03 15.79 0.0000 85.36 11.092 593.92 412.6 0.3801 1.39854 0.0000368 65.57 0.002 0.0000

FS3 HPC.Fl_O 62.40 135.065 1283.76 182.50 0.0000 10.68 121.032 1246.72 49.7 0.4038 1.36287 0.0000368 62.39 0.002 0.0000

FS36 Bleed3.Fl_O 48.36 135.065 1283.76 182.50 0.0000 8.28 126.938 1262.69 49.3 0.3029 1.36287 0.0000368 48.35 0.002 0.0000

FS4 Burner.Fl_O 49.32 131.955 2513.06 158.08 0.0200 12.09 124.637 2480.22 74.6 0.2987 1.29627 0.0000368 48.35 0.002 0.0242

FS45 HPT.Fl_O 65.78 30.657 1642.20 -1.04 0.0149 56.11 27.585 1599.39 265.4 0.4004 1.33249 0.0000368 64.81 0.002 0.0182

FS49 LPT.Fl_O 66.54 7.034 1168.95 -124.27 0.0147 208.71 6.062 1123.70 860.2 0.4718 1.35988 0.0000368 65.57 0.002 0.0180

FS5 TEGV.Fl_O 66.54 7.034 1169.02 -124.27 0.0147 208.72 6.062 1123.77 860.2 0.4718 1.35988 0.0000368 65.57 0.002 0.0180

FS8 Core_Nozz.Fl_O 66.54 7.034 1169.15 -124.27 0.0147 208.73 3.749 987.74 613.4 1.0000 1.35987 0.0000368 65.57 0.002 0.0180

FS17 FanDuctLkg.Fl_O 369.35 7.960 529.10 -3.85 0.0000 688.70 6.608 501.68 2606.7 0.5226 1.40008 0.0000308 369.34 0.011 0.0000

FS171 Bleed15.Fl_O 369.35 7.960 529.10 -3.85 0.0000 688.70 6.421 497.59 2481.9 0.5625 1.40008 0.0000308 369.34 0.011 0.0000

FS172 FanDuct.Fl_O 369.35 7.960 529.10 -3.85 0.0000 688.70 6.421 497.59 2481.9 0.5625 1.40008 0.0000308 369.34 0.011 0.0000

FS173 Byp_Nozz.Fl_O 369.35 7.960 529.10 -3.85 0.0000 688.70 4.204 440.79 2006.9 1.0000 1.40008 0.0000308 369.34 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.50 1.541 0.9070 3810.842 1.1450 0.9125 -8395.6 67.58 30.09

LPC 176.03 2.372 0.8684 3810.842 1.3222 0.8833 -3315.4 4.29 3.38

HPC 85.36 11.022 0.8615 10020.330 2.1010 0.8982 -15091.7 34.11 32.76

HPT 12.09 4.304 0.9073 216.954 1.3579 0.8878 15091.7 

LPT 56.11 4.358 0.9107 88.762 1.4022 0.8932 11710.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.03 1.528 0.9089 3774.506 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.07 2.398 0.8201 1.007 0.0000 1.2479 0.9813 1.0589 0.0003

HPC 77.63 10.550 0.8704 9753.195 12.7857 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.213 0.9073 1.304 4.2126 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9175 0.998 3.5259 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–69
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.01 10494.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4132 953.40 99.14 30.657

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7672 953.40 99.14 7.034

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.64 90.81 39.273

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1126.86 142.49 88.397

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.64 90.81 39.273

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1283.76 182.50 135.065

Splitter 5.6325 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 919.64 90.81 39.273

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10876.0 7287.9 15091.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 611.03 15.79 12.254

LP_Shaft 3597.0 17099.5 11710.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4875 1283.76 182.50 131.955

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5517 1283.76 182.50 74.013

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.76 182.50 135.065

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.76 182.50 135.065

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1283.76 182.50 135.065

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.10 -3.85 7.960

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.10 -3.85 7.960

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.10 -3.85 7.960

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.10 -3.85 7.960

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2513.03 0.9995 0.0230 0.96715 0.02000 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.034 0.9811 1.0000 0.9800 613.40 1.000 1494.4 3269.0

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1009.0 13079.9

NASA/TM—2013-218094 G–70
************************************************************************************************************************************ 

Date:07/05/13 Time:09:47:07 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 460.42 Stator 1 exit: 476.16 Stator 2 inlet: 495.46 Stator 2 exit: 503.76 

 Stator 3 inlet: 526.43 Stator 3 exit: 534.63 Stator 4 inlet: 556.07 Stator 4 exit: 563.55 

 Stator 5 inlet: 580.77 Stator 5 exit: 587.78 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.36 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 1.77 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 776.30 Fan/LPC Inlet Flow Velocity 397.99 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 411.85 Fan/LPC Inlet Static Temperature 448.89 

Additional Water at LPC Exit 0.0000060 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 18.00 430.86 5636.2 0.5955 3356.39 5.6861 776.30 25.519 1.267 69.900 2484.3 2336.7 1615.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 430.86 5.170 462.10 -19.92 0.0000 1156.04 3.458 411.85 3526.7 0.7800 1.40081 0.0000308 430.85 0.013 0.0000

FS1 Inlet.Fl_O 430.86 5.170 462.10 -19.92 0.0000 1156.04 4.172 434.59 4168.2 0.5619 1.40081 0.0000308 430.85 0.013 0.0000

FS12 Splitter.Fl_02 366.42 5.167 462.10 -19.92 0.0000 983.63 4.158 434.25 3531.8 0.5656 1.40081 0.0000308 366.41 0.011 0.0000

FS2 Splitter.Fl_01 64.44 5.167 462.10 -19.92 0.0000 172.99 4.670 448.89 830.5 0.3831 1.40081 0.0000308 64.44 0.002 0.0000

FS14 Fan.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.546 500.18 2606.7 0.5226 1.40011 0.0000308 366.41 0.011 0.0000

FS23 LPC.Fl_O 64.44 12.172 609.41 15.44 0.0000 84.34 11.048 592.82 412.6 0.3747 1.39858 0.0000308 64.44 0.002 0.0000

FS24 VaporIN.Fl_O 64.44 12.172 609.47 15.42 0.0000 84.34 11.048 592.87 412.6 0.3747 1.39858 0.0000369 64.44 0.002 0.0000

FS25 Bleed2.Fl_O 64.44 12.172 609.47 15.42 0.0000 84.34 11.048 592.87 412.6 0.3747 1.39858 0.0000369 64.44 0.002 0.0000

FS3 HPC.Fl_O 61.32 131.930 1274.52 180.12 0.0000 10.71 118.147 1237.50 49.7 0.4050 1.36345 0.0000369 61.31 0.002 0.0000

FS36 Bleed3.Fl_O 47.52 131.930 1274.52 180.12 0.0000 8.30 123.951 1253.47 49.3 0.3036 1.36345 0.0000369 47.52 0.002 0.0000

FS4 Burner.Fl_O 48.45 128.892 2484.26 156.22 0.0196 12.09 121.743 2451.70 74.6 0.2985 1.29739 0.0000369 47.52 0.002 0.0238

FS45 HPT.Fl_O 64.62 29.925 1622.92 -1.09 0.0146 56.14 26.923 1580.45 265.4 0.4005 1.33363 0.0000369 63.69 0.002 0.0178

FS49 LPT.Fl_O 65.37 6.866 1154.70 -122.72 0.0145 208.77 5.917 1109.88 860.2 0.4718 1.36099 0.0000369 64.44 0.002 0.0176

FS5 TEGV.Fl_O 65.37 6.866 1154.77 -122.72 0.0145 208.78 5.917 1109.95 860.2 0.4718 1.36098 0.0000369 64.44 0.002 0.0176

FS8 Core_Nozz.Fl_O 65.37 6.866 1154.90 -122.72 0.0145 208.79 3.658 975.28 613.4 1.0000 1.36097 0.0000369 64.44 0.002 0.0176

FS17 FanDuctLkg.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.546 500.18 2606.7 0.5226 1.40011 0.0000308 366.41 0.011 0.0000

FS171 Bleed15.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.361 496.10 2481.9 0.5625 1.40011 0.0000308 366.41 0.011 0.0000

FS172 FanDuct.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 6.361 496.10 2481.9 0.5625 1.40011 0.0000308 366.41 0.011 0.0000

FS173 Byp_Nozz.Fl_O 366.42 7.885 527.52 -4.23 0.0000 688.70 4.164 439.47 2006.9 1.0000 1.40011 0.0000308 366.41 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.63 1.526 0.9074 3779.174 1.1416 0.9127 -8132.2 74.07 30.79

LPC 172.99 2.355 0.8699 3779.174 1.3188 0.8845 -3223.7 4.58 3.57

HPC 84.34 10.839 0.8615 9991.705 2.0912 0.8980 -14652.7 34.90 33.49

HPT 12.09 4.307 0.9067 217.305 1.3591 0.8875 14652.7 

LPT 56.14 4.358 0.9100 88.546 1.4029 0.8923 11355.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1142.89 1.514 0.9092 3743.140 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.03 2.366 0.8195 0.998 0.0000 1.2442 0.9925 1.0615 0.0003

HPC 76.71 10.376 0.8704 9725.333 12.7210 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.215 0.9067 1.306 4.2155 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9168 0.996 3.5258 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–71
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.73 10396.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3715 947.83 97.77 29.925

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7540 947.83 97.77 6.866

TEGV 0.0000 0.4718 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.45 89.53 38.519

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1119.35 140.59 86.422

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.45 89.53 38.519

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1274.52 180.12 131.930

Splitter 5.6861 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 914.45 89.53 38.519

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10831.0 7105.3 14652.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 609.47 15.42 12.172

LP_Shaft 3567.1 16720.1 11355.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3580 1274.52 180.12 128.892

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4384 1274.52 180.12 72.283

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.52 180.12 131.930

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.52 180.12 131.930

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1274.52 180.12 131.930

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 527.52 -4.23 7.885

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2484.24 0.9995 0.0230 0.93233 0.01962 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.986 0.9808 1.0000 0.9800 613.40 1.000 1485.5 3141.0

Byp_Nozz 2.280 0.9815 1.0000 0.9800 2006.86 1.000 1007.5 12891.2

NASA/TM—2013-218094 G–72
 100μm, ISA +36R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:57:39 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 52/ 2/21 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 468.73 Stator 1 exit: 488.20 Stator 2 inlet: 510.79 Stator 2 exit: 518.46 

 Stator 3 inlet: 548.49 Stator 3 exit: 556.93 Stator 4 inlet: 585.07 Stator 4 exit: 593.21 

 Stator 5 inlet: 615.01 Stator 5 exit: 622.94 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.34 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 2.54 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 493.59 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.45 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 461.97 

Additional Water at LPC Exit 0.0000034 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 465.50 8111.9 0.6156 4993.37 5.2957 793.07 31.926 1.687 100.000 2926.0 2747.3 1915.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 465.50 5.170 482.28 -15.41 0.0000 1275.98 3.458 429.85 3892.8 0.7800 1.40064 0.0000871 465.46 0.041 0.0001

FS1 Inlet.Fl_O 465.50 5.170 482.28 -15.41 0.0000 1275.98 3.838 442.88 4168.2 0.6662 1.40064 0.0000871 465.46 0.041 0.0001

FS12 Splitter.Fl_02 391.56 5.167 482.28 -15.41 0.0000 1073.84 3.865 443.82 3531.8 0.6575 1.40064 0.0000871 391.53 0.034 0.0001

FS2 Splitter.Fl_01 73.94 5.167 482.28 -15.41 0.0000 202.77 4.446 461.97 830.5 0.4683 1.40064 0.0000871 73.93 0.006 0.0001

FS14 Fan.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.260 538.78 2606.7 0.5227 1.39944 0.0000871 391.53 0.034 0.0001

FS23 LPC.Fl_O 73.94 12.694 652.73 25.55 0.0000 96.03 11.114 628.51 412.6 0.4402 1.39742 0.0000871 73.93 0.006 0.0001

FS24 VaporIN.Fl_O 73.94 12.694 652.81 25.55 0.0000 96.03 11.114 628.57 412.6 0.4402 1.39742 0.0000905 73.93 0.007 0.0001

FS25 Bleed2.Fl_O 73.94 12.694 652.81 25.55 0.0000 96.03 11.114 628.57 412.6 0.4402 1.39742 0.0000905 73.93 0.007 0.0001

FS3 HPC.Fl_O 70.35 165.050 1433.29 221.06 0.0000 10.41 148.853 1395.01 49.7 0.3929 1.35406 0.0000905 70.35 0.006 0.0001

FS36 Bleed3.Fl_O 54.52 165.050 1433.29 221.06 0.0000 8.07 155.641 1411.43 49.3 0.2954 1.35406 0.0000905 54.52 0.005 0.0001

FS4 Burner.Fl_O 55.91 161.249 2926.01 188.80 0.0254 12.10 152.353 2889.24 74.6 0.3007 1.28091 0.0000905 54.52 0.005 0.0306

FS45 HPT.Fl_O 74.46 37.749 1924.69 3.83 0.0190 55.84 34.008 1876.75 265.4 0.4006 1.31720 0.0000905 73.07 0.007 0.0231

FS49 LPT.Fl_O 75.33 8.694 1382.56 -142.15 0.0188 207.89 7.501 1331.17 860.2 0.4725 1.34398 0.0000905 73.93 0.007 0.0228

FS5 TEGV.Fl_O 75.33 8.694 1382.63 -142.15 0.0188 207.89 7.501 1331.24 860.2 0.4725 1.34398 0.0000905 73.93 0.007 0.0228

FS8 Core_Nozz.Fl_O 75.33 8.694 1382.75 -142.15 0.0188 207.90 4.655 1175.84 613.4 1.0000 1.34397 0.0000905 73.93 0.007 0.0228

FS17 FanDuctLkg.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.260 538.78 2606.7 0.5227 1.39944 0.0000871 391.53 0.034 0.0001

FS171 Bleed15.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.055 534.39 2481.9 0.5626 1.39944 0.0000871 391.53 0.034 0.0001

FS172 FanDuct.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 7.055 534.39 2481.9 0.5626 1.39944 0.0000871 391.53 0.034 0.0001

FS173 Byp_Nozz.Fl_O 391.56 8.746 568.20 5.21 0.0000 688.62 4.619 473.44 2006.9 1.0000 1.39944 0.0000871 391.53 0.034 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1073.84 1.693 0.9109 4120.682 1.1782 0.9173 -11420.7 38.39 23.45

LPC 202.77 2.457 0.8274 4120.682 1.3534 0.8476 -4284.5 2.96 2.22

HPC 96.03 13.002 0.8587 10334.793 2.1956 0.8978 -19957.3 26.49 25.69

HPT 12.10 4.272 0.9122 214.343 1.3425 0.8900 19957.3 

LPT 55.84 4.342 0.9168 90.571 1.3886 0.9005 15704.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1247.70 1.677 0.9128 4081.391 0.0636 0.8607 1.0235 0.9980 0.9905

LPC 165.11 2.727 0.8329 1.088 0.0000 1.2281 0.8433 0.9934 0.0003

HPC 87.34 12.437 0.8675 10059.274 13.4517 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1809 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.514 0.9236 1.019 3.5137 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–73
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3892.78 11474.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.7210 1051.74 123.30 37.749

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.8651 1051.74 123.30 8.694

TEGV 0.0000 0.4725 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.58 113.53 46.212

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1252.40 174.14 107.155

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.58 113.53 46.212

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1433.29 221.06 165.050

Splitter 5.2957 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1012.58 113.53 46.212

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11594.4 9040.4 19957.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 652.81 25.55 12.694

LP_Shaft 3973.5 20757.6 15704.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 8.4423 1433.29 221.06 161.249

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 7.3872 1433.29 221.06 90.607

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.29 221.06 165.050

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.29 221.06 165.050

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1433.29 221.06 165.050

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 568.20 5.21 8.746

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2926.01 0.9995 0.0230 1.38705 0.02544 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.514 0.9810 1.0000 0.9800 613.40 1.000 1621.7 4530.9

Byp_Nozz 2.529 0.9811 1.0000 0.9800 2006.86 1.000 1045.6 15055.3

NASA/TM—2013-218094 G–74
************************************************************************************************************************************ 

Date:07/05/13 Time:09:58:11 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 75 

Temperature Stator 1 inlet: 478.71 Stator 1 exit: 495.67 Stator 2 inlet: 516.27 Stator 2 exit: 524.91 

 Stator 3 inlet: 549.54 Stator 3 exit: 558.17 Stator 4 inlet: 581.47 Stator 4 exit: 589.37 

 Stator 5 inlet: 607.99 Stator 5 exit: 615.44 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.82 

Fan Bypass Relative Humidity 0.30 

LPC Inlet Relative Humidity 2.07 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 423.40 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.63 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.34 

Additional Water at LPC Exit 0.0000042 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 429.86 6089.7 0.6090 3708.81 5.5851 793.07 26.696 1.344 75.600 2640.6 2483.3 1723.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 429.86 5.170 482.28 -15.41 0.0000 1178.29 3.458 429.85 3594.8 0.7800 1.40064 0.0000871 429.82 0.037 0.0001

FS1 Inlet.Fl_O 429.86 5.170 482.28 -15.41 0.0000 1178.29 4.118 451.90 4168.2 0.5792 1.40064 0.0000871 429.82 0.037 0.0001

FS12 Splitter.Fl_02 364.58 5.167 482.28 -15.41 0.0000 999.86 4.112 451.76 3531.8 0.5806 1.40064 0.0000871 364.55 0.032 0.0001

FS2 Splitter.Fl_01 65.28 5.167 482.28 -15.41 0.0000 179.02 4.629 467.34 830.5 0.3994 1.40064 0.0000871 65.27 0.006 0.0001

FS14 Fan.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.674 525.21 2606.7 0.5226 1.39969 0.0000871 364.55 0.032 0.0001

FS23 LPC.Fl_O 65.28 12.326 639.11 22.27 0.0000 86.39 11.124 620.72 412.6 0.3858 1.39781 0.0000871 65.27 0.006 0.0001

FS24 VaporIN.Fl_O 65.28 12.326 639.18 22.26 0.0000 86.40 11.124 620.78 412.6 0.3858 1.39781 0.0000913 65.27 0.006 0.0001

FS25 Bleed2.Fl_O 65.28 12.326 639.18 22.26 0.0000 86.40 11.124 620.78 412.6 0.3858 1.39781 0.0000913 65.27 0.006 0.0001

FS3 HPC.Fl_O 62.11 138.014 1344.96 198.01 0.0000 10.65 123.763 1306.69 49.7 0.4030 1.35915 0.0000913 62.11 0.006 0.0001

FS36 Bleed3.Fl_O 48.14 138.014 1344.96 198.01 0.0000 8.25 129.759 1323.19 49.3 0.3023 1.35915 0.0000913 48.13 0.004 0.0001

FS4 Burner.Fl_O 49.17 134.836 2640.61 171.50 0.0214 12.09 127.372 2606.55 74.6 0.2992 1.29155 0.0000913 48.13 0.004 0.0259

FS45 HPT.Fl_O 65.54 31.391 1730.96 4.10 0.0160 56.06 28.250 1686.39 265.4 0.4008 1.32754 0.0000913 64.51 0.006 0.0195

FS49 LPT.Fl_O 66.31 7.215 1235.77 -126.23 0.0158 208.46 6.221 1188.52 860.2 0.4721 1.35496 0.0000913 65.27 0.006 0.0193

FS5 TEGV.Fl_O 66.31 7.215 1235.83 -126.23 0.0158 208.47 6.221 1188.58 860.2 0.4721 1.35495 0.0000913 65.27 0.006 0.0193

FS8 Core_Nozz.Fl_O 66.31 7.215 1235.97 -126.23 0.0158 208.48 3.851 1046.26 613.4 1.0000 1.35494 0.0000913 65.27 0.006 0.0193

FS17 FanDuctLkg.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.674 525.21 2606.7 0.5226 1.39969 0.0000871 364.55 0.032 0.0001

FS171 Bleed15.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.486 520.93 2481.9 0.5626 1.39969 0.0000871 364.55 0.032 0.0001 

FS172 FanDuct.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 6.486 520.93 2481.9 0.5626 1.39969 0.0000871 364.55 0.032 0.0001

FS173 Byp_Nozz.Fl_O 364.58 8.040 553.90 1.77 0.0000 688.65 4.246 461.49 2006.9 1.0000 1.39969 0.0000871 364.55 0.032 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 999.86 1.556 0.9070 3842.188 1.1485 0.9126 -8862.7 62.42 29.35

LPC 179.02 2.385 0.8662 3842.188 1.3252 0.8814 -3479.5 4.01 3.17

HPC 86.40 11.197 0.8615 10049.149 2.1042 0.8982 -15839.0 33.46 32.17

HPT 12.09 4.295 0.9089 217.092 1.3535 0.8892 15839.0 

LPT 56.06 4.351 0.9129 89.051 1.3979 0.8960 12342.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1161.74 1.543 0.9088 3805.553 0.0589 0.8607 1.0235 0.9980 0.9905

LPC 143.09 2.430 0.8208 1.015 0.0000 1.2510 0.9689 1.0554 0.0003

HPC 78.58 10.717 0.8704 9781.245 12.8379 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.204 0.9089 1.305 4.2040 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9197 1.002 3.5201 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–75
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3594.76 10595.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.4022 998.97 110.14 31.391

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7637 998.97 110.14 7.215

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.55 101.35 39.977

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1180.75 155.83 90.253

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.55 101.35 39.977

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1344.96 198.01 138.014

Splitter 5.5851 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 963.55 101.35 39.977

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11155.7 7457.0 15839.0 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 639.18 22.26 12.326

LP_Shaft 3704.9 17496.3 12342.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.4534 1344.96 198.01 134.836

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.5219 1344.96 198.01 75.665

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1344.96 198.01 138.014

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1344.96 198.01 138.014

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1344.96 198.01 138.014

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.90 1.77 8.040

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2640.59 0.9995 0.0230 1.03023 0.02140 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.087 0.9813 1.0000 0.9800 613.40 1.000 1535.6 3405.4

Byp_Nozz 2.325 0.9815 1.0000 0.9800 2006.86 1.000 1032.4 13280.1

NASA/TM—2013-218094 G–76
************************************************************************************************************************************ 

Date:07/05/13 Time:09:58:42 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 31/ 1/15 Run by: Philip C Jorgenson PC: 72 

Temperature Stator 1 inlet: 479.68 Stator 1 exit: 496.38 Stator 2 inlet: 516.78 Stator 2 exit: 525.45 

 Stator 3 inlet: 549.60 Stator 3 exit: 558.21 Stator 4 inlet: 581.05 Stator 4 exit: 588.92 

 Stator 5 inlet: 607.22 Stator 5 exit: 614.61 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.70 

Fan Bypass Relative Humidity 0.31 

LPC Inlet Relative Humidity 2.02 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 414.85 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.65 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 467.94 

Additional Water at LPC Exit 0.0000044 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 425.73 5861.5 0.6094 3572.18 5.6350 793.07 26.077 1.306 72.700 2609.1 2454.1 1702.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 425.73 5.170 482.28 -15.41 0.0000 1166.96 3.458 429.85 3560.2 0.7800 1.40064 0.0000871 425.69 0.037 0.0001

FS1 Inlet.Fl_O 425.73 5.170 482.28 -15.41 0.0000 1166.96 4.146 452.76 4168.2 0.5703 1.40064 0.0000871 425.69 0.037 0.0001

FS12 Splitter.Fl_02 361.56 5.167 482.28 -15.41 0.0000 991.58 4.136 452.51 3531.8 0.5729 1.40064 0.0000871 361.53 0.031 0.0001

FS2 Splitter.Fl_01 64.16 5.167 482.28 -15.41 0.0000 175.97 4.650 467.94 830.5 0.3911 1.40064 0.0000871 64.16 0.006 0.0001

FS14 Fan.Fl_O 361.56 7.961 552.20 1.36 0.0000 688.66 6.609 523.59 2606.7 0.5226 1.39972 0.0000871 361.53 0.031 0.0001

FS23 LPC.Fl_O 64.16 12.262 637.67 21.92 0.0000 85.26 11.102 619.87 412.6 0.3797 1.39785 0.0000871 64.16 0.006 0.0001

FS24 VaporIN.Fl_O 64.16 12.262 637.73 21.91 0.0000 85.27 11.102 619.94 412.6 0.3798 1.39785 0.0000915 64.16 0.006 0.0001

FS25 Bleed2.Fl_O 64.16 12.262 637.73 21.91 0.0000 85.27 11.102 619.94 412.6 0.3798 1.39785 0.0000915 64.16 0.006 0.0001

FS3 HPC.Fl_O 61.05 134.813 1335.11 195.46 0.0000 10.68 120.809 1296.84 49.7 0.4042 1.35974 0.0000915 61.05 0.006 0.0001

FS36 Bleed3.Fl_O 47.32 134.813 1335.11 195.46 0.0000 8.28 126.704 1313.33 49.3 0.3032 1.35974 0.0000915 47.31 0.004 0.0001

FS4 Burner.Fl_O 48.31 131.708 2609.08 169.53 0.0210 12.09 124.418 2575.32 74.6 0.2990 1.29275 0.0000915 47.31 0.004 0.0254

FS45 HPT.Fl_O 64.41 30.645 1709.88 4.13 0.0156 56.08 27.576 1665.70 265.4 0.4008 1.32874 0.0000915 63.41 0.006 0.0191

FS49 LPT.Fl_O 65.16 7.043 1219.96 -124.50 0.0155 208.52 6.071 1173.17 860.2 0.4720 1.35616 0.0000915 64.16 0.006 0.0189

FS5 TEGV.Fl_O 65.16 7.043 1220.02 -124.50 0.0155 208.52 6.071 1173.24 860.2 0.4720 1.35615 0.0000915 64.16 0.006 0.0189

FS8 Core_Nozz.Fl_O 65.16 7.043 1220.16 -124.50 0.0155 208.53 3.757 1032.37 613.4 1.0000 1.35614 0.0000915 64.16 0.006 0.0189

FS17 FanDuctLkg.Fl_O 361.56 7.961 552.20 1.36 0.0000 688.66 6.609 523.59 2606.7 0.5226 1.39972 0.0000871 361.53 0.031 0.0001

FS171 Bleed15.Fl_O 361.56 7.961 552.20 1.36 0.0000 688.66 6.422 519.33 2481.9 0.5626 1.39972 0.0000871 361.53 0.031 0.0001

FS172 FanDuct.Fl_O 361.56 7.961 552.20 1.36 0.0000 688.66 6.422 519.33 2481.9 0.5626 1.39972 0.0000871 361.53 0.031 0.0001

FS173 Byp_Nozz.Fl_O 361.56 7.961 552.20 1.36 0.0000 688.66 4.205 460.07 2006.9 1.0000 1.39972 0.0000871 361.53 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 991.58 1.541 0.9070 3811.212 1.1450 0.9125 -8580.4 67.51 30.08

LPC 175.97 2.373 0.8684 3811.212 1.3222 0.8833 -3388.5 4.29 3.38

HPC 85.27 10.994 0.8615 10017.491 2.0935 0.8980 -15373.2 34.33 32.96

HPT 12.09 4.298 0.9083 217.465 1.3546 0.8888 15373.2 

LPT 56.08 4.351 0.9124 88.876 1.3989 0.8953 11968.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1152.12 1.528 0.9089 3774.872 0.0583 0.8607 1.0235 0.9980 0.9905

LPC 141.09 2.398 0.8201 1.007 0.0000 1.2471 0.9822 1.0589 0.0003

HPC 77.55 10.523 0.8704 9750.431 12.7670 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9083 1.307 4.2065 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9192 1.000 3.5206 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–77
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3560.20 10494.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3612 993.13 108.68 30.645

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7507 993.13 108.68 7.043

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.13 100.00 39.223

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1172.77 153.80 88.243

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.13 100.00 39.223

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1335.11 195.46 134.813

Splitter 5.6350 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 958.13 100.00 39.223

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11107.9 7268.9 15373.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.73 21.91 12.262

LP_Shaft 3675.1 17104.9 11968.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.3263 1335.11 195.46 131.708

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.4106 1335.11 195.46 73.900

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.11 195.46 134.813

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.11 195.46 134.813

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1335.11 195.46 134.813

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 552.20 1.36 7.961

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2609.06 0.9995 0.0230 0.99227 0.02097 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.037 0.9811 1.0000 0.9800 613.40 1.000 1526.0 3273.7

Byp_Nozz 2.302 0.9815 1.0000 0.9800 2006.86 1.000 1030.8 13081.8

NASA/TM—2013-218094 G–78
************************************************************************************************************************************ 

Date:07/05/13 Time:09:59:12 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 31/ 1/15 Run by: Philip C Jorgenson PC: 69 

Temperature Stator 1 inlet: 480.57 Stator 1 exit: 497.00 Stator 2 inlet: 517.17 Stator 2 exit: 525.84 

 Stator 3 inlet: 549.50 Stator 3 exit: 558.08 Stator 4 inlet: 580.45 Stator 4 exit: 588.27 

 Stator 5 inlet: 606.24 Stator 5 exit: 613.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.60 

Fan Bypass Relative Humidity 0.33 

LPC Inlet Relative Humidity 1.98 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 793.07 Fan/LPC Inlet Flow Velocity 406.41 

Ambient Static Pressure 3.46 Fan/LPC Inlet Static Pressure 4.67 

Ambient Static Temperature 429.85 Fan/LPC Inlet Static Temperature 468.51 

Additional Water at LPC Exit 0.0000045 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 35000.0 36.00 421.75 5642.7 0.6101 3442.73 5.6888 793.07 25.470 1.269 69.900 2579.1 2426.4 1682.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 421.75 5.170 482.28 -15.41 0.0000 1156.05 3.458 429.85 3526.9 0.7800 1.40064 0.0000871 421.71 0.037 0.0001

FS1 Inlet.Fl_O 421.75 5.170 482.28 -15.41 0.0000 1156.05 4.172 453.57 4168.2 0.5620 1.40064 0.0000871 421.71 0.037 0.0001

FS12 Splitter.Fl_02 358.69 5.167 482.28 -15.41 0.0000 983.71 4.158 453.21 3531.8 0.5657 1.40064 0.0000871 358.66 0.031 0.0001

FS2 Splitter.Fl_01 63.05 5.167 482.28 -15.41 0.0000 172.92 4.670 468.51 830.5 0.3829 1.40064 0.0000871 63.05 0.005 0.0001

FS14 Fan.Fl_O 358.69 7.886 550.55 0.97 0.0000 688.66 6.547 522.03 2606.7 0.5226 1.39975 0.0000871 358.66 0.031 0.0001

FS23 LPC.Fl_O 63.05 12.180 636.04 21.52 0.0000 84.25 11.058 618.78 412.6 0.3743 1.39789 0.0000871 63.05 0.005 0.0001

FS24 VaporIN.Fl_O 63.05 12.180 636.11 21.51 0.0000 84.25 11.058 618.84 412.6 0.3743 1.39789 0.0000916 63.05 0.006 0.0001

FS25 Bleed2.Fl_O 63.05 12.180 636.11 21.51 0.0000 84.25 11.058 618.84 412.6 0.3743 1.39789 0.0000916 63.05 0.006 0.0001

FS3 HPC.Fl_O 59.99 131.676 1325.53 192.98 0.0000 10.70 117.924 1287.27 49.7 0.4053 1.36031 0.0000916 59.99 0.005 0.0001

FS36 Bleed3.Fl_O 46.50 131.676 1325.53 192.98 0.0000 8.30 123.714 1303.78 49.3 0.3039 1.36031 0.0000916 46.49 0.004 0.0001

FS4 Burner.Fl_O 47.45 128.643 2579.11 167.61 0.0206 12.09 121.520 2545.64 74.6 0.2988 1.29390 0.0000916 46.49 0.004 0.0249

FS45 HPT.Fl_O 63.27 29.913 1689.85 4.09 0.0153 56.11 26.914 1646.02 265.4 0.4009 1.32989 0.0000916 62.31 0.006 0.0187

FS49 LPT.Fl_O 64.01 6.874 1205.09 -122.88 0.0152 208.58 5.926 1158.74 860.2 0.4719 1.35729 0.0000916 63.05 0.006 0.0185

FS5 TEGV.Fl_O 64.01 6.874 1205.16 -122.88 0.0152 208.58 5.926 1158.81 860.2 0.4719 1.35729 0.0000916 63.05 0.006 0.0185

FS8 Core_Nozz.Fl_O 64.01 6.874 1205.29 -122.88 0.0152 208.60 3.666 1019.33 613.4 1.0000 1.35728 0.0000916 63.05 0.006 0.0185

FS17 FanDuctLkg.Fl_O 358.69 7.886 550.55 0.97 0.0000 688.66 6.547 522.03 2606.7 0.5226 1.39975 0.0000871 358.66 0.031 0.0001

FS171 Bleed15.Fl_O 358.69 7.886 550.55 0.97 0.0000 688.66 6.362 517.77 2481.9 0.5626 1.39975 0.0000871 358.66 0.031 0.0001

FS172 FanDuct.Fl_O 358.69 7.886 550.55 0.97 0.0000 688.66 6.362 517.77 2481.9 0.5626 1.39975 0.0000871 358.66 0.031 0.0001

FS173 Byp_Nozz.Fl_O 358.69 7.886 550.55 0.97 0.0000 688.66 4.165 458.70 2006.9 1.0000 1.39975 0.0000871 358.66 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 983.71 1.526 0.9074 3779.583 1.1416 0.9127 -8311.3 73.97 30.78

LPC 172.92 2.357 0.8699 3779.583 1.3188 0.8845 -3294.8 4.57 3.57

HPC 84.25 10.811 0.8615 9988.774 2.0838 0.8979 -14925.1 35.13 33.71

HPT 12.09 4.301 0.9078 217.819 1.3557 0.8883 14925.1 

LPT 56.11 4.351 0.9117 88.659 1.3996 0.8945 11606.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1142.97 1.514 0.9092 3743.545 0.0578 0.8607 1.0235 0.9980 0.9905

LPC 139.06 2.366 0.8195 0.998 0.0000 1.2435 0.9934 1.0615 0.0003

HPC 76.63 10.349 0.8704 9722.480 12.7019 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.209 0.9078 1.309 4.2092 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9185 0.997 3.5206 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 G–79
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3526.91 10395.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3203 987.34 107.24 29.913

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7377 987.34 107.24 6.874

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 952.75 98.67 38.469

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1164.97 151.82 86.267

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 952.75 98.67 38.469

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1325.53 192.98 131.676

Splitter 5.6888 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 952.75 98.67 38.469

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11061.9 7086.3 14925.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 636.11 21.51 12.180

LP_Shaft 3644.6 16725.3 11606.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.1993 1325.53 192.98 128.643

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.2996 1325.53 192.98 72.169

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.53 192.98 131.676

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.53 192.98 131.676

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1325.53 192.98 131.676

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 550.55 0.97 7.886

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2579.09 0.9995 0.0230 0.95632 0.02057 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.988 0.9808 1.0000 0.9800 613.40 1.000 1516.9 3145.3

Byp_Nozz 2.281 0.9815 1.0000 0.9800 2006.86 1.000 1029.2 12893.2

NASA/TM—2013-218094 G–80
Appendix H: Compressor code analysis for the altitude cruise conditions at 35000 feet 

 5μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 3.054 EfDer = 0.986 SH = 0.255636E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.348 3889.766 5.167 462.090 1.000 1.000 0.980

 W Kg/sec = 34.249 Wdry = 75.329 WH2O = 0.019 lbm/sec H2O = 0.111g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.318 4121.124 1.381 0.248 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 166900.094 59116.141 1.404 831.557 592.278 619.754 1.046

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 481.70 -0.17 481.70 0.47 0.83 741.91

 MEAN 17.06 0.00 -0.02 481.70 -0.17 481.70 0.47 0.73

 HUB 12.51 0.00 -0.02 481.70 -0.17 481.70 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.48 50.47 5.01 700.28 850.09 4.45 443.44 454.16 18.42

 MEAN 50.25 47.20 3.05 579.10 753.38 4.45 443.44 454.16 18.42

 HUB 41.41 38.62 2.79 424.65 642.26 4.45 443.44 454.16 18.42

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 723.96 356.60 630.05 1044.52 0.69 7.29 6.52 16.04

 MEAN 18.04 768.55 413.44 647.87 1039.05 0.74 7.43 6.80 12.53

 HUB 15.00 906.40 579.08 697.30 1025.44 0.88 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.28 717.68 343.68 0.69 7360.08 0.92 0.90

 MEAN 612.23 677.68 198.78 0.65 7459.70 0.92 0.90 0.90 1.22

 HUB 509.17 700.80 69.91 0.68 8688.28 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.31 4.95 502.26 1.09 460.12 481.68 12.29

 MEAN 6.82 1.32 4.76 502.80 1.09 455.32 482.78 14.86

 HUB 7.12 1.38 4.31 509.51 1.10 443.46 490.20 24.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.51 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.54 17.06 12.70 4.36 0.91 0.23 2.22

 HUB 39.71 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 829.2605 412.6401 719.3060 1032.4968 0.8032 -0.1044 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8881 4.5251 449.5829 485.4478 19.3377 29.8414 35.4000 5.5587

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 673.3131 164.7129 652.8554 1053.8829 0.6389 0.2358 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8199 5.1986 468.4207 482.3842 554.9116 0.0405 0.3647

 

NASA/TM—2013-218094 H–1
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 674.3389 0.0000 674.3389 1053.7159 0.6400 0.2622 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1447 468.3194 482.7632 0.0000 0.0600 0.0695 0.2118

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8288 6.7549 1.3073 504.8534 42.7661 236.5705 1.8339

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 266067.813 0.543 1132.918 860243.063 0.437683E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.757 EfDer = 0.991 SH = 0.706270E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.348 3889.766 6.755 504.852 1.000 1.000 0.980

 W Kg/sec = 34.249 Wdry = 75.295 WH2O = 0.053 lbm/sec H2O = 0.352g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 161.770 3942.748 1.381 0.249 53.371 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 145565.922 59105.691 1.247 590.487 473.709 468.502 0.989

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 591.63 -0.20 591.63 0.56 0.86 707.04

 MEAN 18.08 0.00 -0.02 591.63 -0.20 591.63 0.56 0.80

 HUB 15.21 0.00 -0.02 591.63 -0.20 591.63 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.71 46.36 3.35 697.56 914.82 5.49 476.76 483.40 13.13

 MEAN 46.06 42.30 3.76 613.66 852.55 5.49 476.76 483.40 13.13

 HUB 41.12 37.84 3.28 516.30 785.36 5.49 476.76 483.40 13.13

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 644.19 279.31 580.49 1091.58 0.59 2.33 2.04 9.02

 MEAN 18.01 663.79 303.53 590.32 1087.94 0.61 2.40 2.13 7.35

 HUB 15.22 724.72 404.83 601.11 1084.66 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 693.15 712.90 413.84 0.65 5707.71 0.92 0.91

 MEAN 611.34 665.75 307.81 0.61 5470.30 0.92 0.91 0.91 1.38

 HUB 516.74 611.43 111.91 0.56 6165.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.23 1.22 6.52 535.95 1.06 502.65 498.86 5.90

 MEAN 8.16 1.21 6.37 534.66 1.06 499.29 498.54 6.56

 HUB 8.35 1.24 6.22 538.45 1.07 496.29 501.03 7.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.70 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 27.21 27.54 23.50 4.04 0.92 0.33 1.63

 HUB 33.96 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 758.9691 304.3850 695.2581 1077.8656 0.7041 -0.2306 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2291 5.9338 490.1376 500.8957 9.0032 23.6439 30.6000 6.9561

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 653.4849 138.5434 638.6299 1090.9382 0.5990 0.0344 2.4513

 

NASA/TM—2013-218094 H–2
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1731 6.4320 502.0902 499.1576 491.5697 0.0397 0.2293

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 694.0917 0.0000 694.0917 1086.1399 0.6390 0.1103 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1870 497.7062 499.9218 0.0000 0.0600 0.0699 -0.0958

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8316 8.1164 1.2016 536.3504 31.4985 277.4934 2.1511

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 196334.297 0.409 835.993 777662.125 0.865633E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.173 EfDer = 0.993 SH = 0.109747E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.348 3889.766 8.116 536.349 1.000 1.000 0.980

 W Kg/sec = 34.249 Wdry = 75.266 WH2O = 0.083 lbm/sec H2O = 0.637g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 138.770 3825.228 1.380 0.249 53.384 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 125123.148 59096.594 1.342 545.479 406.477 424.468 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 550.50 -0.19 550.50 0.50 0.80 669.95

 MEAN 17.74 0.00 -0.02 550.50 -0.19 550.50 0.50 0.74

 HUB 15.05 0.00 -0.02 550.50 -0.19 550.50 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.07 46.36 4.71 681.27 876.04 6.86 512.06 499.06 6.23

 MEAN 47.57 43.40 4.17 602.13 815.99 6.86 512.06 499.06 6.23

 HUB 42.87 38.84 4.03 510.87 751.15 6.86 512.06 499.06 6.23

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 614.49 282.80 545.55 1127.70 0.54 2.26 1.98 8.75

 MEAN 17.51 632.09 304.67 553.82 1124.31 0.56 2.34 2.07 6.78

 HUB 14.85 689.61 398.39 562.88 1121.22 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.44 670.41 389.65 0.59 5606.01 0.92 0.91 

 MEAN 594.25 624.96 289.59 0.56 5337.01 0.92 0.91 0.91 1.41

 HUB 504.08 572.72 105.68 0.51 5918.99 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.75 1.20 7.99 566.85 1.06 536.59 512.47 3.40

 MEAN 9.66 1.19 7.82 565.38 1.05 533.37 512.08 3.71

 HUB 9.84 1.21 7.65 568.55 1.06 530.44 513.95 4.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.40 35.54 31.50 4.04 0.93 0.35 1.40

 MEAN 28.82 27.60 23.50 4.10 0.92 0.35 1.62

 HUB 35.29 10.63 6.50 4.13 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 711.3518 306.6650 641.8551 1116.8772 0.6369 -0.2001 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7323 7.4326 526.3967 513.7166 4.5715 25.5375 31.5000 5.9625

 

NASA/TM—2013-218094 H–3
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 618.6938 134.9639 603.7936 1127.3052 0.5488 0.0499 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6876 7.9151 536.2670 512.5826 451.3937 0.0331 0.2626

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 634.8366 0.0000 634.8366 1125.5708 0.5640 0.1567 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7930 534.6465 512.9003 0.0000 0.0600 0.0560 -0.0133

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8520 9.6433 1.1881 566.9176 30.5771 262.7361 2.0367

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 190909.109 0.422 812.892 735414.750 0.134832E-02

 

Melt Ratio at Stator LE, Throat, TE

0.30543E-01 0.49493E-01 0.13065E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.790 EfDer = 0.996 SH = 0.164100E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.348 3889.766 9.643 566.913 1.000 1.000 0.980

 W Kg/sec = 34.249 Wdry = 75.225 WH2O = 0.124 lbm/sec H2O = 1.096g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.079 3720.674 1.379 0.250 53.402 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 108702.531 59083.941 1.459 513.330 351.861 395.845 1.125

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 508.21 -0.18 508.21 0.45 0.73 625.33

 MEAN 16.97 0.00 -0.02 508.21 -0.18 508.21 0.45 0.68

 HUB 14.32 0.00 -0.02 508.21 -0.18 508.21 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.15 46.36 5.79 653.77 828.20 8.43 546.26 512.48 3.55

 MEAN 48.59 43.80 4.79 576.06 768.33 8.43 546.26 512.48 3.55

 HUB 43.74 37.84 5.90 486.09 703.37 8.43 546.26 512.48 3.55

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 578.44 279.10 506.65 1160.84 0.50 2.16 1.89 8.34

 MEAN 16.57 592.43 294.04 514.31 1157.30 0.51 2.24 1.97 6.35

 HUB 13.89 642.69 374.11 522.57 1154.01 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.87 622.56 361.78 0.54 5272.75 0.92 0.91

 MEAN 562.59 580.20 268.56 0.50 4876.27 0.92 0.91 0.91 1.43

 HUB 471.49 531.57 97.38 0.46 5198.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.36 1.18 9.61 595.53 1.05 568.77 523.77 2.15

 MEAN 11.22 1.16 9.41 593.38 1.05 565.31 523.12 2.33

 HUB 11.33 1.18 9.21 595.13 1.05 562.10 524.19 2.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.85 35.53 31.50 4.03 0.93 0.37 1.40

 MEAN 29.76 27.57 23.50 4.07 0.92 0.36 1.62

 HUB 35.60 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 644.6517 295.6886 572.8386 1153.2836 0.5590 -0.1336 2.1803

 

NASA/TM—2013-218094 H–4
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2856 9.1547 561.4514 524.0618 2.5687 27.3019 32.4000 5.0981

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 567.4380 127.2598 552.9836 1160.9316 0.4888 0.0896 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.2530 9.5778 568.9234 523.3543 432.2457 0.0272 0.2924

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 562.7682 0.0000 562.7682 1161.3058 0.4846 0.1973 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5753 569.3198 523.3430 0.0000 0.0600 0.0454 0.0883

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8677 11.2185 1.1633 594.6301 27.7658 262.8693 2.0377

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 173699.969 0.423 739.616 720748.500 0.181332E-02

 

Melt Ratio at Stator LE, Throat, TE

0.58038E+00 0.66267E+00 0.88312E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.398 EfDer = 0.998 SH = 0.199789E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.348 3889.766 11.218 594.615 1.000 1.000 0.980

 W Kg/sec = 34.249 Wdry = 75.198 WH2O = 0.151 lbm/sec H2O = 1.517g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 105.712 3632.940 1.378 0.250 53.413 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 95608.430 59075.629 1.645 509.668 309.852 384.739 1.242

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 450.21 -0.16 450.21 0.38 0.66 580.79

 MEAN 15.91 0.00 -0.02 450.21 -0.16 450.21 0.38 0.60

 HUB 13.07 0.00 -0.02 450.21 -0.16 450.21 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.10 47.36 6.74 621.87 767.85 10.15 578.43 522.97 1.99

 MEAN 50.20 44.80 5.40 540.16 703.30 10.15 578.43 522.97 1.99

 HUB 44.59 38.84 5.75 443.66 632.18 10.15 578.43 522.97 1.99

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 534.47 284.11 452.70 1191.55 0.45 2.05 1.78 7.43

 MEAN 15.50 541.58 284.92 460.58 1187.27 0.46 2.13 1.86 5.75

 HUB 12.59 579.51 340.54 468.90 1183.18 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.97 557.20 324.86 0.47 5099.80 0.92 0.91

 MEAN 526.06 519.89 241.14 0.44 4417.97 0.92 0.91 0.91 1.48

 HUB 427.36 476.87 86.83 0.40 4289.38 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 13.05 1.16 11.39 622.25 1.05 599.44 533.32 1.41

 MEAN 12.80 1.14 11.12 618.56 1.04 595.14 532.13 1.54

 HUB 12.75 1.14 10.85 617.86 1.04 591.05 532.16 1.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.11 35.66 31.50 4.16 0.93 0.41 1.40

 MEAN 31.74 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.99 10.49 6.50 3.99 0.92 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.495 73.000

 

NASA/TM—2013-218094 H–5
 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 607.3917 290.1399 533.6136 1182.1663 0.5138 -0.2134 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.8311 10.7445 590.1249 532.9769 1.7387 28.5341 33.0000 4.4659

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 540.1931 123.3535 525.9206 1188.3105 0.4546 -0.0012 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.7826 11.1165 596.2804 532.5021 410.5396 0.0478 0.3129

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 522.2797 0.0000 522.2797 1189.7889 0.4390 0.2312 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.2269 597.8046 532.7139 0.0000 0.0600 0.0434 0.0620

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8721 12.7902 1.1401 619.5562 24.9423 266.7877 2.0681

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 156341.172 0.422 665.702 726472.438 0.252522E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3408 Tt4 = 619.5562 T1 = 462.0897

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 983352.44 4187.1201 202.3185 2.4752 0.8306 3.0542 1.3408 37.3740

NASA/TM—2013-218094 H–6
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.482 EfDer = 0.998 SH = 0.302674E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.367 3629.122 5.167 462.089 1.000 1.000 0.980

 W Kg/sec = 30.167 Wdry = 66.347 WH2O = 0.020 lbm/sec H2O = 0.136g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 178.204 3844.976 1.381 0.249 53.358 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 142742.766 52068.957 1.594 831.557 521.700 619.754 1.188

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 411.98 -0.14 411.98 0.40 0.75 692.19

 MEAN 17.06 0.00 -0.02 411.98 -0.14 411.98 0.40 0.66

 HUB 12.51 0.00 -0.02 411.98 -0.14 411.98 0.40 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.77 50.47 7.30 653.35 772.52 4.64 448.45 454.08 17.66

 MEAN 52.68 47.20 5.48 540.30 679.56 4.64 448.45 454.08 17.66

 HUB 43.89 38.62 5.27 396.19 571.67 4.64 448.45 454.08 17.66

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 644.09 363.80 531.51 1052.25 0.61 7.29 6.52 16.04

 MEAN 18.04 679.11 403.97 545.89 1046.78 0.65 7.43 6.80 12.53

 HUB 15.00 783.55 532.18 575.10 1036.84 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 653.35 605.26 289.55 0.58 7508.12 0.92 0.91

 MEAN 571.20 570.93 167.23 0.55 7288.50 0.92 0.91 0.91 1.32

 HUB 475.05 577.93 57.12 0.56 7984.40 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.30 5.24 500.31 1.08 466.97 480.25 11.61

 MEAN 6.68 1.29 5.05 499.19 1.08 462.13 480.16 13.96

 HUB 6.84 1.32 4.70 502.74 1.09 453.39 484.13 19.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.39 28.58 24.20 4.38 0.93 0.35 1.80

 MEAN 36.50 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.78 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 719.2814 403.1889 595.6546 1043.4165 0.6894 -0.0761 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7304 4.9161 459.1791 481.7861 16.2087 34.0934 35.4000 1.3066

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 564.6568 138.1323 547.5005 1061.3665 0.5320 0.3092 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6999 5.5386 475.1322 479.8256 554.9116 0.0275 0.4210

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 560.6163 0.0000 560.6163 1061.7371 0.5280 0.3409 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5346 475.5034 480.2422 0.0000 0.0600 0.0409 0.3069

NASA/TM—2013-218094 H–7
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8751 6.6764 1.2921 500.7454 38.6590 220.1158 1.7063

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 240606.453 0.564 902.390 735730.375 0.552108E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.505 EfDer = 1.000 SH = 0.901810E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.367 3629.122 6.676 500.745 1.000 1.000 0.980

 W Kg/sec = 30.167 Wdry = 66.308 WH2O = 0.060 lbm/sec H2O = 0.467g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 143.576 3693.611 1.380 0.249 53.378 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 123338.664 52056.703 1.404 590.487 420.484 468.502 1.114 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 501.29 -0.17 501.29 0.47 0.77 662.37

 MEAN 18.08 0.00 -0.02 501.29 -0.17 501.29 0.47 0.71

 HUB 15.21 0.00 -0.02 501.29 -0.17 501.29 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.40 46.36 6.04 650.82 821.63 5.75 480.59 481.35 14.91

 MEAN 48.80 42.30 6.50 572.54 761.11 5.75 480.59 481.35 14.91

 HUB 43.87 37.84 6.03 481.70 695.33 5.75 480.59 481.35 14.91

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 577.06 294.58 496.21 1093.67 0.53 2.33 2.04 9.02

 MEAN 18.01 592.03 308.37 505.38 1089.60 0.54 2.40 2.13 7.35

 HUB 15.22 644.67 387.50 515.21 1085.82 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 646.70 608.45 352.12 0.56 6018.96 0.92 0.91

 MEAN 570.38 569.26 262.01 0.52 5556.80 0.92 0.91 0.91 1.45

 HUB 482.11 523.82 94.62 0.48 5901.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.13 1.22 6.74 531.32 1.06 504.61 497.25 7.21

 MEAN 8.01 1.20 6.57 528.97 1.06 500.86 496.38 8.11

 HUB 8.10 1.21 6.40 530.72 1.06 497.39 497.88 9.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.70 35.36 31.50 3.86 0.93 0.39 1.40

 MEAN 31.39 27.40 23.50 3.90 0.93 0.38 1.63

 HUB 36.95 10.41 6.50 3.91 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 660.0411 309.2328 583.1203 1083.6073 0.6091 -0.1808 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0676 6.2995 495.4116 498.0308 9.8133 27.9373 30.6000 2.6627

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 549.8896 116.5805 537.3896 1095.2322 0.5021 0.1420 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0443 6.7873 506.0971 496.6037 491.5697 0.0255 0.2969

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 574.9719 0.0000 574.9719 1092.7618 0.5262 0.2042 0.5911

NASA/TM—2013-218094 H–8
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6605 503.8393 497.1248 0.0000 0.0600 0.0393 0.0580

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8781 8.0234 1.2018 530.3386 29.5949 249.5958 1.9349

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184591.797 0.441 692.308 660628.688 0.109306E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.726 EfDer = 1.000 SH = 0.137656E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.367 3629.122 8.023 530.338 1.000 1.000 0.980

 W Kg/sec = 30.167 Wdry = 66.276 WH2O = 0.091 lbm/sec H2O = 0.825g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.950 3589.080 1.379 0.249 53.393 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 106694.203 52046.977 1.514 545.479 360.203 424.468 1.178

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 469.42 -0.16 469.42 0.43 0.72 628.59

 MEAN 17.74 0.00 -0.02 469.42 -0.16 469.42 0.43 0.66

 HUB 15.05 0.00 -0.02 469.42 -0.16 469.42 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.56 46.36 7.20 635.62 790.30 7.09 512.69 496.96 7.89

 MEAN 50.13 43.40 6.73 561.78 732.21 7.09 512.69 496.96 7.89

 HUB 45.45 38.84 6.61 476.63 669.10 7.09 512.69 496.96 7.89

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 553.32 293.97 468.76 1126.36 0.49 2.26 1.98 8.75

 MEAN 17.51 566.51 306.64 476.34 1122.68 0.50 2.34 2.07 6.78

 HUB 14.85 616.01 380.44 484.49 1119.23 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 627.38 575.24 333.41 0.51 5826.88 0.92 0.91

 MEAN 554.43 536.94 247.79 0.48 5371.12 0.92 0.91 0.91 1.48

 HUB 470.30 492.75 89.86 0.44 5651.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.61 1.20 8.17 559.89 1.06 535.37 510.55 4.50

 MEAN 9.48 1.18 7.99 557.58 1.05 531.88 509.77 4.94

 HUB 9.56 1.19 7.80 559.00 1.05 528.62 510.90 5.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.09 35.42 31.50 3.92 0.93 0.40 1.40

 MEAN 32.77 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.14 10.51 6.50 4.01 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 626.2339 308.6547 544.8864 1117.9288 0.5602 -0.1650 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.5362 7.7284 527.4369 511.0313 5.6714 29.5297 31.5000 1.9703

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 525.4392 114.6210 512.7849 1127.7274 0.4659 0.1475 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.5163 8.2175 536.7250 509.9470 451.3937 0.0228 0.3212

 

NASA/TM—2013-218094 H–9
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 536.1374 0.0000 536.1374 1126.7379 0.4758 0.2315 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1469 535.8109 510.2088 0.0000 0.0600 0.0379 0.1024

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8811 9.4925 1.1831 558.8063 28.4827 238.5720 1.8494

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 177991.328 0.452 667.553 632215.438 0.164595E-02

 

Melt Ratio at Stator LE, Throat, TE

0.48231E-01 0.81043E-01 0.20107E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.069 EfDer = 1.000 SH = 0.194804E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.367 3629.122 9.493 558.800 1.000 1.000 0.980

 W Kg/sec = 30.167 Wdry = 66.238 WH2O = 0.129 lbm/sec H2O = 1.331g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.675 3496.464 1.379 0.250 53.411 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 93556.195 52035.254 1.642 513.330 312.645 395.845 1.266

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 437.40 -0.15 437.40 0.39 0.66 587.65

 MEAN 16.97 0.00 -0.02 437.40 -0.15 437.40 0.39 0.61

 HUB 14.32 0.00 -0.02 437.40 -0.15 437.40 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.36 46.36 8.00 609.97 750.70 8.58 543.51 510.07 4.68

 MEAN 50.87 43.80 7.07 537.46 693.07 8.58 543.51 510.07 4.68

 HUB 46.05 37.84 8.21 453.52 630.18 8.58 543.51 510.07 4.68

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 523.79 285.48 439.16 1156.07 0.45 2.16 1.89 8.34

 MEAN 16.57 533.57 293.08 445.87 1152.46 0.46 2.24 1.97 6.35

 HUB 13.89 576.39 356.33 453.06 1149.03 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 597.93 538.96 312.45 0.47 5392.85 0.92 0.91

 MEAN 524.90 502.53 231.82 0.44 4860.00 0.92 0.91 0.91 1.50

 HUB 439.90 460.70 83.57 0.40 4951.56 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.13 1.17 9.69 586.08 1.05 564.16 521.32 2.93

 MEAN 10.96 1.15 9.48 583.38 1.04 560.64 520.42 3.18

 HUB 10.99 1.16 9.28 583.85 1.04 557.30 520.99 3.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.03 35.43 31.50 3.93 0.93 0.42 1.40

 MEAN 33.32 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.19 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 574.8224 294.7265 493.5150 1149.7307 0.5000 -0.1146 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.0102 9.3045 558.0401 521.1985 3.4093 30.8456 32.4000 1.5544

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 488.3393 109.5202 475.8998 1157.2543 0.4220 0.1697 2.2705

 

NASA/TM—2013-218094 H–10
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9947 9.7433 565.3727 520.4586 432.2457 0.0201 0.3425

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 484.2283 0.0000 484.2283 1157.5199 0.4183 0.2558 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7408 565.6607 520.4644 0.0000 0.0600 0.0374 0.1680

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8833 10.9678 1.1554 584.3823 25.6373 241.3918 1.8713

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 160527.438 0.449 602.055 626126.313 0.212807E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.67647E+00 0.76553E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.324 EfDer = 0.999 SH = 0.251636E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.367 3629.122 10.968 584.373 1.000 1.000 0.980

 W Kg/sec = 30.167 Wdry = 66.200 WH2O = 0.167 lbm/sec H2O = 1.932g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.415 3419.095 1.378 0.251 53.430 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 83267.594 52023.574 1.841 509.668 276.823 384.739 1.390

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 392.09 -0.14 392.09 0.34 0.60 546.60

 MEAN 15.91 0.00 -0.02 392.09 -0.14 392.09 0.34 0.55

 HUB 13.07 0.00 -0.02 392.09 -0.14 392.09 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.96 47.36 8.60 580.20 700.37 10.15 572.12 520.55 3.00

 MEAN 52.12 44.80 7.32 503.97 638.63 10.15 572.12 520.55 3.00

 HUB 46.56 38.84 7.72 413.93 570.25 10.15 572.12 520.55 3.00

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 488.23 284.17 397.01 1183.18 0.41 2.05 1.78 7.43

 MEAN 15.50 491.32 280.25 403.55 1179.12 0.42 2.13 1.86 5.75

 HUB 12.59 522.51 323.33 410.45 1175.20 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 568.16 488.12 283.99 0.41 5100.52 0.92 0.91

 MEAN 490.81 455.18 210.56 0.39 4345.38 0.92 0.91 0.91 1.54

 HUB 398.73 417.32 75.39 0.36 4072.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.67 1.16 11.29 610.13 1.04 591.12 530.72 2.19

 MEAN 12.41 1.13 11.03 606.32 1.04 587.07 529.44 2.38

 HUB 12.31 1.12 10.77 604.94 1.04 583.17 529.22 2.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.59 35.58 31.50 4.08 0.93 0.45 1.40

 MEAN 34.78 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.23 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 545.1774 285.3908 464.5110 1175.3927 0.4638 -0.1923 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.4331 10.7526 583.4540 530.2103 2.6186 31.5661 33.0000 1.4339

 

NASA/TM—2013-218094 H–11
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 469.2535 107.1544 456.8553 1181.5476 0.3972 0.0840 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.4086 11.1492 589.5914 529.6664 410.5396 0.0371 0.3550

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 454.8745 0.0000 454.8745 1182.5729 0.3846 0.2795 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.2222 590.6542 529.8978 0.0000 0.0600 0.0373 0.1350

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8820 12.4083 1.1313 607.1263 22.7547 248.5444 1.9267

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 142859.063 0.443 535.790 637550.563 0.313126E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3139 Tt4 = 607.1263 T1 = 462.0887

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 906576.06 3400.0972 178.2035 2.4013 0.8671 5.4816 1.3139 37.3740

NASA/TM—2013-218094 H–12
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.832 EfDer = 0.999 SH = 0.308924E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.212 3599.863 5.167 462.089 1.000 1.000 0.980

 W Kg/sec = 29.642 Wdry = 65.192 WH2O = 0.020 lbm/sec H2O = 0.139g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 175.102 3813.977 1.381 0.249 53.358 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 139803.734 51162.594 1.622 831.557 512.623 619.754 1.209

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 403.49 -0.14 403.49 0.39 0.74 686.61

 MEAN 17.06 0.00 -0.02 403.49 -0.14 403.49 0.39 0.65

 HUB 12.51 0.00 -0.02 403.49 -0.14 403.49 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.10 50.47 7.63 648.09 763.55 4.66 449.00 454.08 17.61

 MEAN 53.03 47.20 5.83 535.94 670.96 4.66 449.00 454.08 17.61

 HUB 44.26 38.62 5.64 393.00 563.35 4.66 449.00 454.08 17.61

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 635.26 364.87 520.03 1053.05 0.60 7.29 6.52 16.04

 MEAN 18.04 669.08 403.08 534.03 1047.58 0.64 7.43 6.80 12.53

 HUB 15.00 770.18 526.99 561.66 1037.92 0.74 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 648.09 592.15 283.21 0.56 7530.21 0.92 0.91

 MEAN 566.60 558.50 163.52 0.53 7272.34 0.92 0.91 0.91 1.34

 HUB 471.22 564.42 55.77 0.54 7906.65 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.30 5.27 500.11 1.08 467.68 480.12 11.58

 MEAN 6.66 1.29 5.08 498.81 1.08 462.83 479.89 13.92

 HUB 6.81 1.32 4.74 502.02 1.09 454.34 483.56 19.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.06 28.57 24.20 4.37 0.93 0.36 1.80

 MEAN 37.05 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.18 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 707.4426 402.2976 581.9207 1044.4629 0.6773 -0.0735 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7127 4.9546 460.1043 481.4440 16.0233 34.6572 35.4000 0.7428

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 552.3212 135.1146 535.5397 1062.1151 0.5200 0.3185 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6843 5.5717 475.8066 479.5599 554.9116 0.0267 0.4285

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 548.1626 0.0000 548.1626 1062.4886 0.5159 0.3499 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5698 476.1798 479.9831 0.0000 0.0600 0.0390 0.3174

NASA/TM—2013-218094 H–13
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8780 6.6634 1.2895 500.3118 38.2255 217.9101 1.6892

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 237918.609 0.566 876.779 720582.250 0.567174E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.867 EfDer = 1.000 SH = 0.927397E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.212 3599.863 6.663 500.311 1.000 1.000 0.980

 W Kg/sec = 29.642 Wdry = 65.152 WH2O = 0.060 lbm/sec H2O = 0.482g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 141.291 3665.420 1.380 0.249 53.378 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 120791.617 51150.164 1.427 590.487 413.801 468.502 1.132

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 490.93 -0.17 490.93 0.46 0.76 657.31

 MEAN 18.08 0.00 -0.02 490.93 -0.17 490.93 0.46 0.70

 HUB 15.21 0.00 -0.02 490.93 -0.17 490.93 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.76 46.36 6.40 645.57 811.17 5.78 480.98 481.14 15.14

 MEAN 49.17 42.30 6.87 567.92 750.83 5.78 480.98 481.14 15.14

 HUB 44.23 37.84 6.39 477.82 685.19 5.78 480.98 481.14 15.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 569.71 296.44 486.52 1093.87 0.52 2.33 2.04 9.02

 MEAN 18.01 584.02 309.03 495.56 1089.76 0.54 2.40 2.13 7.35

 HUB 15.22 635.58 385.60 505.24 1085.93 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 641.49 596.45 345.05 0.55 6056.77 0.92 0.91

 MEAN 565.78 558.12 256.75 0.51 5568.66 0.92 0.91 0.91 1.46

 HUB 478.23 513.66 92.63 0.47 5872.57 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.12 1.22 6.76 530.83 1.06 504.80 497.08 7.38

 MEAN 7.99 1.20 6.59 528.37 1.06 501.02 496.14 8.31

 HUB 8.07 1.21 6.42 529.90 1.06 497.50 497.53 9.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.35 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.95 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.35 10.39 6.50 3.89 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 649.4860 309.8966 570.7855 1084.1176 0.5991 -0.1759 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0432 6.3297 495.8828 497.7305 9.9465 28.4989 30.6000 2.1011

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 538.4592 114.1572 526.2191 1095.6152 0.4915 0.1545 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0220 6.8157 506.4567 496.3235 491.5697 0.0245 0.3050

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 562.5728 0.0000 562.5728 1093.2906 0.5146 0.2135 0.5911

NASA/TM—2013-218094 H–14
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6955 504.3323 496.8290 0.0000 0.0600 0.0381 0.0727

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8799 8.0019 1.2009 529.6987 29.3887 246.2862 1.9092

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183321.172 0.445 675.576 646702.188 0.112300E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.044 EfDer = 1.000 SH = 0.141319E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.212 3599.863 8.002 529.698 1.000 1.000 0.980

 W Kg/sec = 29.642 Wdry = 65.120 WH2O = 0.092 lbm/sec H2O = 0.848g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.062 3562.293 1.379 0.250 53.394 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 104644.211 51140.387 1.538 545.479 354.679 424.468 1.197

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 460.40 -0.16 460.40 0.42 0.71 623.90

 MEAN 17.74 0.00 -0.02 460.40 -0.16 460.40 0.42 0.66

 HUB 15.05 0.00 -0.02 460.40 -0.16 460.40 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.87 46.36 7.51 630.49 780.83 7.11 512.73 496.72 8.11

 MEAN 50.44 43.40 7.04 557.25 722.96 7.11 512.73 496.72 8.11

 HUB 45.77 38.84 6.93 472.79 660.04 7.11 512.73 496.72 8.11

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 546.74 295.15 460.23 1126.16 0.49 2.26 1.98 8.75

 MEAN 17.51 559.34 306.81 467.69 1122.47 0.50 2.34 2.07 6.78

 HUB 14.85 607.84 378.38 475.71 1118.99 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.33 564.68 327.18 0.50 5850.06 0.92 0.91

 MEAN 549.96 527.12 243.15 0.47 5374.01 0.92 0.91 0.91 1.49

 HUB 466.51 483.81 88.13 0.43 5621.29 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.58 1.20 8.17 559.12 1.06 535.19 510.31 4.64

 MEAN 9.45 1.18 7.99 556.73 1.05 531.68 509.49 5.11

 HUB 9.52 1.19 7.81 557.97 1.05 528.39 510.55 5.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.67 35.41 31.50 3.91 0.93 0.41 1.40

 MEAN 33.27 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.50 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 617.1943 308.8241 534.3749 1117.9464 0.5521 -0.1615 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4993 7.7437 527.4594 510.7207 5.8219 30.0243 31.5000 1.4757

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 515.3802 112.4267 502.9681 1127.6782 0.4570 0.1586 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4808 8.2317 536.6848 509.6360 451.3937 0.0221 0.3282

 

NASA/TM—2013-218094 H–15
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 525.7308 0.0000 525.7308 1126.7369 0.4666 0.2393 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1638 535.8167 509.8933 0.0000 0.0600 0.0374 0.1141

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8820 9.4576 1.1819 557.9254 28.2422 235.8393 1.8282

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176508.438 0.456 650.470 619708.250 0.168585E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.49917E-01 0.84141E-01 0.20815E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.344 EfDer = 0.999 SH = 0.199073E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.212 3599.863 9.458 557.919 1.000 1.000 0.980

 W Kg/sec = 29.642 Wdry = 65.082 WH2O = 0.130 lbm/sec H2O = 1.361g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 105.123 3471.011 1.379 0.250 53.413 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91894.227 51128.738 1.666 513.330 308.103 395.845 1.285

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 429.63 -0.15 429.63 0.38 0.65 583.37

 MEAN 16.97 0.00 -0.02 429.63 -0.15 429.63 0.38 0.60

 HUB 14.32 0.00 -0.02 429.63 -0.15 429.63 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.63 46.36 8.27 605.05 742.19 8.58 543.17 509.78 4.84

 MEAN 51.14 43.80 7.34 533.13 684.81 8.58 543.17 509.78 4.84

 HUB 46.33 37.84 8.49 449.86 622.16 8.58 543.17 509.78 4.84

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 517.92 286.06 431.75 1155.49 0.45 2.16 1.89 8.34

 MEAN 16.57 527.17 292.87 438.34 1151.88 0.46 2.24 1.97 6.35

 HUB 13.89 569.10 354.27 445.39 1148.44 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 593.11 529.80 307.05 0.46 5403.70 0.92 0.91

 MEAN 520.66 493.99 227.79 0.43 4856.49 0.92 0.91 0.91 1.51

 HUB 436.35 452.89 82.08 0.39 4922.90 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.08 1.17 9.67 585.03 1.05 563.60 521.01 3.04

 MEAN 10.91 1.15 9.47 582.28 1.04 560.08 520.09 3.30

 HUB 10.93 1.16 9.26 582.62 1.04 556.74 520.61 3.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.53 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.75 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.50 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 567.3364 294.5163 484.9029 1149.2706 0.4936 -0.1127 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9569 9.2979 557.5992 520.8503 3.5261 31.2733 32.4000 1.1267

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 479.8134 107.6081 467.5910 1156.7714 0.4148 0.1787 2.2705

 

NASA/TM—2013-218094 H–16
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9425 9.7361 564.9071 520.1033 432.2457 0.0196 0.3486

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 475.7774 0.0000 475.7774 1157.0249 0.4112 0.2625 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7333 565.1834 520.1119 0.0000 0.0600 0.0370 0.1769

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8839 10.9162 1.1542 583.2550 25.3915 239.0079 1.8528

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 159008.125 0.452 585.978 614425.313 0.217301E-02

 

Melt Ratio at Stator LE, Throat, TE

0.68643E+00 0.77626E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.556 EfDer = 0.999 SH = 0.260876E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.212 3599.863 10.916 583.247 1.000 1.000 0.980

 W Kg/sec = 29.642 Wdry = 65.042 WH2O = 0.170 lbm/sec H2O = 2.000g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 93.121 3394.805 1.378 0.251 53.433 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 81909.859 51116.258 1.867 509.668 273.042 384.739 1.409

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 385.69 -0.13 385.69 0.33 0.60 542.72

 MEAN 15.91 0.00 -0.02 385.69 -0.13 385.69 0.33 0.54

 HUB 13.07 0.00 -0.02 385.69 -0.13 385.69 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.18 47.36 8.82 575.52 692.92 10.13 571.39 520.29 3.17

 MEAN 52.36 44.80 7.56 499.90 631.50 10.13 571.39 520.29 3.17

 HUB 46.80 38.84 7.96 410.59 563.43 10.13 571.39 520.29 3.17

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 483.19 284.07 390.87 1182.21 0.41 2.05 1.78 7.43

 MEAN 15.50 485.83 279.68 397.25 1178.18 0.41 2.13 1.86 5.75

 HUB 12.59 516.22 321.35 404.00 1174.28 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 563.58 480.52 279.51 0.41 5098.65 0.92 0.91

 MEAN 486.85 448.03 207.18 0.38 4336.42 0.92 0.91 0.91 1.55

 HUB 395.51 410.75 74.16 0.35 4047.59 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.60 1.15 11.25 608.78 1.04 590.17 530.42 2.31

 MEAN 12.33 1.13 10.99 604.96 1.04 586.15 529.13 2.52

 HUB 12.24 1.12 10.74 603.52 1.03 582.27 528.89 2.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.01 35.57 31.50 4.07 0.93 0.45 1.40

 MEAN 35.15 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.50 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 538.4658 284.8039 456.9816 1174.5839 0.4584 -0.1902 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3610 10.7256 582.6646 529.8986 2.7609 31.9323 33.0000 1.0677

 

NASA/TM—2013-218094 H–17
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 461.5979 105.4063 449.4020 1180.7291 0.3909 0.0934 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3382 11.1223 588.7885 529.3398 410.5396 0.0363 0.3602

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 447.5556 0.0000 447.5556 1181.7131 0.3787 0.2851 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1919 589.8095 529.5743 0.0000 0.0600 0.0370 0.1432

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8823 12.3373 1.1302 605.7513 22.5057 246.4973 1.9108

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 141334.594 0.445 520.847 626301.188 0.323288E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3109 Tt4 = 605.7513 T1 = 462.0886 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 898091.00 3309.6504 175.1020 2.3876 0.8688 5.8320 1.3109 37.3740

NASA/TM—2013-218094 H–18
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.178 EfDer = 1.000 SH = 0.315175E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.067 3570.371 5.167 462.089 1.000 1.000 0.980

 W Kg/sec = 29.121 Wdry = 64.047 WH2O = 0.020 lbm/sec H2O = 0.142g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.026 3782.731 1.381 0.249 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 136921.016 50263.840 1.651 831.557 503.621 619.754 1.231

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 395.17 -0.14 395.17 0.38 0.73 680.99

 MEAN 17.06 0.00 -0.02 395.17 -0.14 395.17 0.38 0.64

 HUB 12.51 0.00 -0.02 395.17 -0.14 395.17 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.42 50.47 7.95 642.78 754.65 4.68 449.54 454.07 17.57

 MEAN 53.38 47.20 6.18 531.55 662.46 4.68 449.54 454.07 17.57

 HUB 44.62 38.62 6.00 389.78 555.15 4.68 449.54 454.07 17.57

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 626.69 365.69 508.93 1053.77 0.59 7.29 6.52 16.04

 MEAN 18.04 659.31 402.02 522.56 1048.30 0.63 7.43 6.80 12.53

 HUB 15.00 757.26 521.86 548.73 1038.92 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 642.78 579.47 277.08 0.55 7547.03 0.92 0.91

 MEAN 561.96 546.49 159.94 0.52 7253.11 0.92 0.91 0.91 1.35

 HUB 467.36 551.43 54.50 0.53 7829.57 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.30 499.89 1.08 468.32 479.97 11.57

 MEAN 6.65 1.29 5.11 498.41 1.08 463.48 479.62 13.91

 HUB 6.77 1.31 4.78 501.30 1.08 455.21 483.00 19.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.70 28.57 24.20 4.37 0.93 0.37 1.80

 MEAN 37.57 17.02 12.70 4.32 0.93 0.32 2.22

 HUB 43.56 -5.67 -9.30 3.63 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 696.0059 401.2362 568.7123 1045.4167 0.6658 -0.0710 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6940 4.9898 460.9487 481.1044 15.8806 35.2036 35.4000 0.1964

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 540.4739 132.2164 524.0523 1062.7743 0.5085 0.3274 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6674 5.6008 476.4007 479.2893 554.9116 0.0261 0.4356

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 536.2464 0.0000 536.2464 1063.1455 0.5044 0.3584 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.6006 476.7717 479.7189 0.0000 0.0600 0.0376 0.3273

NASA/TM—2013-218094 H–19
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8803 6.6485 1.2867 499.8649 37.7787 215.7722 1.6727

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 235148.047 0.569 851.349 705723.688 0.582065E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.215 EfDer = 1.000 SH = 0.952426E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.067 3570.371 6.649 499.864 1.000 1.000 0.980

 W Kg/sec = 29.121 Wdry = 64.006 WH2O = 0.061 lbm/sec H2O = 0.497g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.058 3637.016 1.380 0.249 53.379 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 118337.859 50251.262 1.450 590.487 407.265 468.502 1.150

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 480.96 -0.17 480.96 0.45 0.75 652.22

 MEAN 18.08 0.00 -0.02 480.96 -0.17 480.96 0.45 0.69

 HUB 15.21 0.00 -0.02 480.96 -0.17 480.96 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.09 46.36 6.73 640.28 800.94 5.80 481.31 480.91 15.38

 MEAN 49.52 42.30 7.22 563.27 740.80 5.80 481.31 480.91 15.38

 HUB 44.59 37.84 6.75 473.90 675.33 5.80 481.31 480.91 15.38

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 562.61 297.95 477.24 1093.97 0.51 2.33 2.04 9.02

 MEAN 18.01 576.26 309.44 486.14 1089.84 0.53 2.40 2.13 7.35

 HUB 15.22 626.75 383.59 495.66 1085.98 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 636.23 584.98 338.28 0.53 6087.51 0.92 0.91

 MEAN 561.14 547.43 251.71 0.50 5575.91 0.92 0.91 0.91 1.47

 HUB 474.31 503.89 90.72 0.46 5841.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.09 1.22 6.77 530.28 1.06 504.90 496.87 7.56

 MEAN 7.96 1.20 6.60 527.73 1.06 501.10 495.88 8.52

 HUB 8.03 1.21 6.43 529.06 1.06 497.56 497.17 9.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.98 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.48 27.37 23.50 3.87 0.93 0.39 1.63

 HUB 37.74 10.37 6.50 3.87 0.93 0.40 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 639.3879 310.3037 559.0425 1084.5151 0.5896 -0.1714 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0151 6.3540 496.2512 497.4129 10.0998 29.0330 30.6000 1.5670

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 527.6115 111.8574 515.6179 1095.8813 0.4814 0.1662 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9956 6.8372 506.7079 496.0236 491.5697 0.0237 0.3125

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 550.8832 0.0000 550.8832 1093.6836 0.5037 0.2218 0.5911

NASA/TM—2013-218094 H–20
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7225 504.6999 496.5154 0.0000 0.0600 0.0374 0.0860

 

 STAGE EXIT CONDITIONS, STAGE 2 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8809 7.9759 1.1996 529.0210 29.1578 243.1940 1.8852

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 181896.031 0.449 658.551 633141.875 0.115220E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.342 EfDer = 0.999 SH = 0.144864E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.067 3570.371 7.976 529.020 1.000 1.000 0.980

 W Kg/sec = 29.121 Wdry = 63.974 WH2O = 0.093 lbm/sec H2O = 0.870g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 119.248 3535.372 1.379 0.250 53.395 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 102692.156 50241.445 1.561 545.479 349.372 424.468 1.215

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 451.81 -0.16 451.81 0.41 0.70 619.18

 MEAN 17.74 0.00 -0.02 451.81 -0.16 451.81 0.41 0.65

 HUB 15.05 0.00 -0.02 451.81 -0.16 451.81 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.16 46.36 7.80 625.33 771.60 7.12 512.68 496.46 8.34

 MEAN 50.74 43.40 7.34 552.68 713.98 7.12 512.68 496.46 8.34

 HUB 46.07 38.84 7.23 468.92 651.28 7.12 512.68 496.46 8.34

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 540.39 295.92 452.16 1125.85 0.48 2.26 1.98 8.75

 MEAN 17.51 552.44 306.70 459.49 1122.15 0.49 2.34 2.07 6.78

 HUB 14.85 599.98 376.23 467.37 1118.66 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 617.23 554.70 321.30 0.49 5865.39 0.92 0.91

 MEAN 545.46 517.82 238.76 0.46 5371.95 0.92 0.91 0.91 1.50

 HUB 462.69 475.30 86.46 0.42 5589.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.54 1.20 8.17 558.28 1.06 534.90 510.03 4.80

 MEAN 9.40 1.18 7.99 555.82 1.05 531.39 509.18 5.28

 HUB 9.46 1.19 7.80 556.90 1.05 528.08 510.17 5.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.20 35.40 31.50 3.90 0.93 0.42 1.40

 MEAN 33.72 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.83 10.48 6.50 3.98 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 608.5686 308.7084 524.4567 1117.8409 0.5444 -0.1583 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4554 7.7504 527.3655 510.3783 5.9858 30.4821 31.5000 1.0179

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 505.9300 110.3652 493.7456 1127.4944 0.4487 0.1686 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4382 8.2358 536.5161 509.2931 451.3937 0.0216 0.3346

 

NASA/TM—2013-218094 H–21
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 515.9702 0.0000 515.9702 1126.5963 0.4580 0.2463 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1704 535.6888 509.5472 0.0000 0.0600 0.0370 0.1246

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8826 9.4154 1.1805 556.9819 27.9767 233.3431 1.8089

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 174868.516 0.459 633.108 607522.000 0.172488E-02

 

Melt Ratio at Stator LE, Throat, TE

0.50523E-01 0.85709E-01 0.21258E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.596 EfDer = 0.999 SH = 0.203315E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.067 3570.371 9.415 556.976 1.000 1.000 0.980

 W Kg/sec = 29.121 Wdry = 63.937 WH2O = 0.130 lbm/sec H2O = 1.389g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 103.652 3445.490 1.378 0.250 53.414 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 90324.969 50229.867 1.690 513.330 303.799 395.845 1.303

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 422.29 -0.15 422.29 0.37 0.65 579.08

 MEAN 16.97 0.00 -0.02 422.29 -0.15 422.29 0.37 0.60

 HUB 14.32 0.00 -0.02 422.29 -0.15 422.29 0.37 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.87 46.36 8.51 600.09 733.90 8.57 542.73 509.46 5.00

 MEAN 51.40 43.80 7.60 528.76 676.81 8.57 542.73 509.46 5.00

 HUB 46.58 37.84 8.74 446.17 614.43 8.57 542.73 509.46 5.00

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 512.25 286.24 424.81 1154.79 0.44 2.16 1.89 8.34

 MEAN 16.57 521.03 292.38 431.26 1151.19 0.45 2.24 1.97 6.35

 HUB 13.89 562.13 352.13 438.17 1147.75 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 588.25 521.22 302.01 0.45 5407.09 0.92 0.91 

 MEAN 516.40 485.97 224.02 0.42 4848.30 0.92 0.91 0.91 1.52

 HUB 432.78 445.53 80.65 0.39 4893.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.02 1.17 9.65 583.88 1.05 562.92 520.66 3.15

 MEAN 10.85 1.15 9.44 581.10 1.04 559.41 519.72 3.43

 HUB 10.86 1.15 9.24 581.32 1.04 556.08 520.19 3.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.97 35.41 31.50 3.91 0.93 0.43 1.40

 MEAN 34.14 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 38.79 10.43 6.50 3.93 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 560.1866 294.0220 476.8229 1148.6821 0.4877 -0.1109 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8938 9.2802 557.0337 520.4633 3.6548 31.6591 32.4000 0.7409

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 471.8521 105.8226 459.8325 1156.1455 0.4081 0.1868 2.2705

 

NASA/TM—2013-218094 H–22
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8803 9.7163 564.3018 519.7094 432.2457 0.0192 0.3540

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 467.8894 0.0000 467.8894 1156.3887 0.4046 0.2684 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7132 564.5673 519.7214 0.0000 0.0600 0.0368 0.1847

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8842 10.8545 1.1529 582.0425 25.1229 236.8775 1.8363

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 157345.156 0.455 569.665 603011.938 0.221833E-02

 

Melt Ratio at Stator LE, Throat, TE

0.69261E+00 0.78303E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.762 EfDer = 0.999 SH = 0.268653E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.067 3570.371 10.855 582.035 1.000 1.000 0.980

 W Kg/sec = 29.121 Wdry = 63.895 WH2O = 0.172 lbm/sec H2O = 2.056g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 91.909 3370.499 1.377 0.251 53.435 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 80636.117 50216.895 1.891 509.668 269.502 384.739 1.428

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 379.70 -0.13 379.69 0.33 0.59 538.83

 MEAN 15.91 0.00 -0.02 379.70 -0.13 379.69 0.33 0.54

 HUB 13.07 0.00 -0.02 379.70 -0.13 379.69 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.37 47.36 9.01 570.80 685.66 10.09 570.55 519.96 3.33

 MEAN 52.56 44.80 7.76 495.81 624.60 10.09 570.55 519.96 3.33

 HUB 47.01 38.84 8.17 407.23 556.87 10.09 570.55 519.96 3.33

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 478.31 283.64 385.13 1181.12 0.40 2.05 1.78 7.43

 MEAN 15.50 480.53 278.81 391.37 1177.12 0.41 2.13 1.86 5.75

 HUB 12.59 510.20 319.26 397.96 1173.25 0.43 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 558.96 473.42 275.32 0.40 5090.94 0.92 0.91

 MEAN 482.86 441.37 204.05 0.37 4323.03 0.92 0.91 0.91 1.56

 HUB 392.27 404.60 73.01 0.34 4021.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.51 1.15 11.19 607.31 1.04 589.08 530.04 2.44

 MEAN 12.25 1.13 10.94 603.50 1.04 585.10 528.76 2.65

 HUB 12.15 1.12 10.69 602.00 1.03 581.26 528.49 2.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.37 35.56 31.50 4.06 0.93 0.46 1.40

 MEAN 35.47 27.54 23.50 4.04 0.93 0.43 1.64

 HUB 38.74 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 532.0501 283.9268 449.9588 1173.6390 0.4533 -0.1882 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2765 10.6852 581.7373 529.5138 2.9001 32.2522 33.0000 0.7478

 

NASA/TM—2013-218094 H–23
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 454.4975 103.7849 442.4892 1179.7579 0.3852 0.1016 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2550 11.0802 587.8308 528.9435 410.5396 0.0357 0.3646

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 440.7608 0.0000 440.7608 1180.7053 0.3733 0.2899 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1465 588.8141 529.1810 0.0000 0.0600 0.0368 0.1503

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8825 12.2536 1.1289 604.2720 22.2380 244.7145 1.8970

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 139685.000 0.447 505.727 615302.500 0.331827E-02

 

Melt Ratio at Stator LE, Throat, TE

 0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3077 Tt4 = 604.2720 T1 = 462.0885

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 888942.75 3218.3982 172.0265 2.3714 0.8701 6.1785 1.3077 37.3740

NASA/TM—2013-218094 H–24
5μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 3.167 EfDer = 0.987 SH = 0.589419E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl 

 73.521 3974.631 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 33.418 Wdry = 73.477 WH2O = 0.043 lbm/sec H2O = 0.246g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 201.679 4121.995 1.381 0.249 53.367 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 169861.500 57674.473 1.408 831.557 590.533 619.754 1.049

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 490.25 -0.17 490.25 0.47 0.83 742.06

 MEAN 17.06 0.00 -0.02 490.25 -0.17 490.25 0.47 0.73

 HUB 12.51 0.00 -0.02 490.25 -0.17 490.25 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.59 50.47 5.12 715.56 867.53 4.46 462.97 467.95 16.48

 MEAN 50.37 47.20 3.17 591.73 768.56 4.46 462.97 467.95 16.48

 HUB 41.52 38.62 2.90 433.91 654.80 4.46 462.97 467.95 16.48

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 737.39 366.45 639.89 1067.60 0.69 7.29 6.52 16.04

 MEAN 18.04 782.74 423.59 658.22 1061.93 0.74 7.43 6.80 12.53

 HUB 15.00 922.38 591.20 707.99 1048.13 0.88 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.56 728.92 349.11 0.68 7563.30 0.92 0.90

 MEAN 625.58 688.52 202.00 0.65 7642.68 0.92 0.90 0.90 1.22

 HUB 520.28 711.54 70.93 0.68 8870.17 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.80 1.32 4.96 524.40 1.09 480.74 493.58 11.04

 MEAN 6.82 1.32 4.78 524.85 1.09 475.64 494.92 13.22

 HUB 7.12 1.38 4.33 531.68 1.10 463.36 503.13 20.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.80 28.62 24.20 4.42 0.93 0.28 1.80

 MEAN 32.76 17.06 12.70 4.36 0.91 0.23 2.22

 HUB 39.86 -5.72 -9.30 3.58 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 843.7387 422.7628 730.1826 1055.4073 0.7994 -0.1027 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8947 4.5467 469.8382 498.0013 16.8162 30.0701 35.4000 5.3299

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 683.1503 167.1194 662.3937 1077.2642 0.6342 0.2412 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8288 5.2261 489.5245 493.7339 554.9116 0.0396 0.3688

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 683.6775 0.0000 683.6775 1077.1611 0.6347 0.2682 1.3089

NASA/TM—2013-218094 H–25
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1765 489.4780 494.2523 0.0000 0.0600 0.0674 0.2190

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8319 6.7668 1.3096 526.9752 44.7075 235.6317 1.8266

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 278538.313 0.544 1157.246 812108.063 0.958559E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.943 EfDer = 0.992 SH = 0.146750E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.521 3974.631 6.767 526.974 1.000 1.000 0.980

 W Kg/sec = 33.418 Wdry = 73.413 WH2O = 0.108 lbm/sec H2O = 0.703g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 160.984 3943.300 1.379 0.249 53.396 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 147781.656 57654.551 1.252 590.487 471.624 468.502 0.993

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 600.61 -0.21 600.61 0.55 0.86 707.14

 MEAN 18.08 0.00 -0.02 600.61 -0.21 600.61 0.55 0.80

 HUB 15.21 0.00 -0.02 600.61 -0.21 600.61 0.55 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.89 46.36 3.53 712.78 932.25 5.51 498.09 495.06 11.38

 MEAN 46.24 42.30 3.94 627.05 868.44 5.51 498.09 495.06 11.38

 HUB 41.31 37.84 3.47 527.56 799.55 5.51 498.09 495.06 11.38

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 655.51 288.76 588.49 1115.80 0.59 2.33 2.04 9.02

 MEAN 18.01 675.43 312.51 598.78 1111.96 0.61 2.40 2.13 7.35

 HUB 15.22 737.49 414.49 609.99 1108.50 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.27 722.71 419.51 0.65 5900.74 0.92 0.91

 MEAN 624.68 675.27 312.17 0.61 5632.04 0.92 0.91 0.91 1.39

 HUB 528.01 620.47 113.53 0.56 6312.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.26 1.22 6.56 559.75 1.06 525.34 509.02 5.33

 MEAN 8.19 1.21 6.40 558.25 1.06 521.73 508.80 5.90

 HUB 8.37 1.24 6.25 562.04 1.07 518.49 511.34 6.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.14 35.48 31.50 3.98 0.93 0.34 1.40

 MEAN 27.56 27.53 23.50 4.03 0.92 0.33 1.63

 HUB 34.20 10.54 6.50 4.04 0.92 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 770.8080 313.3875 704.2253 1101.9858 0.6995 -0.2265 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2565 5.9795 512.4668 511.5618 7.8427 23.9896 30.6000 6.6104

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 661.4235 140.2265 646.3881 1115.3916 0.5930 0.0446 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2034 6.4869 525.0042 509.2442 491.5697 0.0384 0.2358

 

NASA/TM—2013-218094 H–26
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 701.4645 0.0000 701.4645 1110.7216 0.6315 0.1197 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2520 520.6459 510.2152 0.0000 0.0600 0.0668 -0.0809

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8367 8.1501 1.2044 560.0114 33.0376 275.1260 2.1328

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 206452.906 0.412 857.752 733811.125 0.174625E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.419 EfDer = 0.995 SH = 0.213340E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.521 3974.631 8.150 560.010 1.000 1.000 0.980

 W Kg/sec = 33.418 Wdry = 73.364 WH2O = 0.157 lbm/sec H2O = 1.192g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 137.785 3825.221 1.378 0.250 53.417 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126760.305 57639.414 1.351 545.479 403.852 424.468 1.051

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 557.70 -0.19 557.70 0.50 0.79 669.94

 MEAN 17.74 0.00 -0.02 557.70 -0.19 557.70 0.50 0.74

 HUB 15.05 0.00 -0.02 557.70 -0.19 557.70 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.31 46.36 4.95 696.13 892.13 6.91 535.17 509.03 5.43

 MEAN 47.82 43.40 4.42 615.26 830.55 6.91 535.17 509.03 5.43

 HUB 43.12 38.84 4.28 522.01 764.02 6.91 535.17 509.03 5.43

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 624.87 292.97 551.93 1152.85 0.54 2.26 1.98 8.75

 MEAN 17.51 642.62 314.18 560.59 1149.26 0.56 2.34 2.07 6.78

 HUB 14.85 701.06 408.11 570.02 1145.99 0.61 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 687.11 678.21 394.14 0.59 5807.60 0.92 0.91

 MEAN 607.22 632.56 293.04 0.55 5503.58 0.92 0.91 0.91 1.42

 HUB 515.08 579.97 106.97 0.51 6063.27 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.81 1.20 8.06 592.18 1.06 560.99 521.38 2.96

 MEAN 9.72 1.19 7.88 590.50 1.05 557.51 521.04 3.21

 HUB 9.89 1.21 7.71 593.60 1.06 554.34 522.90 3.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.96 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.27 27.60 23.50 4.10 0.92 0.35 1.62

 HUB 35.60 10.63 6.50 4.13 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 721.8940 316.2394 648.9404 1141.9270 0.6322 -0.1962 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7884 7.5061 550.4871 522.8017 3.8446 25.9807 31.5000 5.5193

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 624.9514 136.3289 609.9005 1152.6879 0.5422 0.0617 2.3726

 

NASA/TM—2013-218094 H–27
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7466 8.0021 560.9031 521.3250 451.3937 0.0317 0.2701

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 640.6571 0.0000 640.6571 1151.0017 0.5566 0.1670 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.8872 559.3004 521.5767 0.0000 0.0600 0.0531 0.0020

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8577 9.7056 1.1909 592.0564 32.0837 259.9935 2.0155

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 200982.969 0.426 835.026 693951.500 0.237409E-02

 

Melt Ratio at Stator LE, Throat, TE

0.32404E+00 0.39719E+00 0.60514E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.094 EfDer = 0.997 SH = 0.261797E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.521 3974.631 9.706 592.045 1.000 1.000 0.980

 W Kg/sec = 33.418 Wdry = 73.328 WH2O = 0.192 lbm/sec H2O = 1.687g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 118.967 3720.261 1.378 0.251 53.433 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109891.406 57628.371 1.472 513.330 348.827 395.845 1.135

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 513.77 -0.18 513.77 0.44 0.72 625.27

 MEAN 16.97 0.00 -0.02 513.77 -0.18 513.77 0.44 0.67

 HUB 14.32 0.00 -0.02 513.77 -0.18 513.77 0.44 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.44 46.36 6.08 668.04 842.89 8.51 571.00 520.70 2.70

 MEAN 48.89 43.80 5.09 588.63 781.44 8.51 571.00 520.70 2.70

 HUB 44.04 37.84 6.20 496.69 714.73 8.51 571.00 520.70 2.70

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 587.87 289.65 511.56 1186.81 0.50 2.16 1.89 8.34

 MEAN 16.57 601.78 303.68 519.54 1183.09 0.51 2.24 1.97 6.35

 HUB 13.89 652.65 383.47 528.12 1179.61 0.55 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.86 628.54 365.21 0.53 5472.00 0.92 0.91

 MEAN 574.87 586.06 271.19 0.50 5036.08 0.92 0.91 0.91 1.44

 HUB 481.78 537.19 98.31 0.46 5328.90 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.46 1.18 9.72 622.29 1.05 594.74 531.40 1.67

 MEAN 11.31 1.17 9.51 619.88 1.05 591.01 530.77 1.80

 HUB 11.41 1.18 9.30 621.50 1.05 587.54 531.78 1.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.52 35.52 31.50 4.02 0.93 0.38 1.40

 MEAN 30.31 27.56 23.50 4.06 0.92 0.37 1.62

 HUB 35.98 10.54 6.50 4.04 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 653.9508 305.3830 578.2672 1179.1318 0.5546 -0.1307 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.3763 9.2593 587.1456 531.7690 1.9822 27.8385 32.4000 4.5615

 

NASA/TM—2013-218094 H–28
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 572.1424 128.3148 557.5681 1187.1246 0.4820 0.1035 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.3462 9.7017 595.1396 531.0303 432.2457 0.0260 0.3006

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 567.5103 0.0000 567.5103 1187.5039 0.4779 0.2074 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6984 595.5688 531.2623 0.0000 0.0600 0.0437 0.1017

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8692 11.3127 1.1656 621.2155 29.1758 259.5812 2.0123

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183120.656 0.427 760.813 680024.688 0.305011E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.715 EfDer = 0.999 SH = 0.398565E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.521 3974.631 11.313 621.214 1.000 1.000 0.980

 W Kg/sec = 33.418 Wdry = 73.227 WH2O = 0.293 lbm/sec H2O = 2.921g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.550 3631.899 1.376 0.252 53.478 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96608.602 57597.129 1.661 509.668 306.820 384.739 1.254

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 454.88 -0.16 454.88 0.38 0.65 580.62

 MEAN 15.91 0.00 -0.02 454.88 -0.16 454.88 0.38 0.60

 HUB 13.07 0.00 -0.02 454.88 -0.16 454.88 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.41 47.36 7.05 635.43 781.60 10.26 604.80 531.70 2.00

 MEAN 50.51 44.80 5.71 551.95 715.36 10.26 604.80 531.70 2.00

 HUB 44.91 38.84 6.07 453.34 642.32 10.26 604.80 531.70 2.00

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 543.62 294.41 457.00 1218.04 0.45 2.05 1.78 7.43

 MEAN 15.50 550.30 294.11 465.11 1213.60 0.45 2.13 1.86 5.75

 HUB 12.59 588.39 349.06 473.66 1209.36 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.25 562.43 327.85 0.46 5284.53 0.92 0.91

 MEAN 537.54 524.96 243.43 0.43 4560.49 0.92 0.91 0.91 1.49

 HUB 436.69 481.70 87.63 0.40 4396.72 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 13.19 1.17 11.53 650.30 1.05 626.85 541.77 1.45

 MEAN 12.92 1.14 11.25 646.31 1.04 622.29 540.66 1.57

 HUB 12.86 1.14 10.97 645.41 1.04 617.94 540.75 1.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.79 35.66 31.50 4.16 0.93 0.41 1.40

 MEAN 32.31 27.63 23.50 4.13 0.92 0.39 1.64

 HUB 36.39 10.48 6.50 3.98 0.92 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 616.2197 299.5029 538.5394 1208.5476 0.5099 -0.2099 2.0437

 

NASA/TM—2013-218094 H–29
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.9544 10.8800 617.2589 541.6602 1.7529 29.0802 33.0000 3.9198

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 544.5317 124.3443 530.1445 1214.9780 0.4482 0.0151 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.9096 11.2732 623.8566 540.9945 410.5396 0.0457 0.3212

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 526.6622 0.0000 526.6622 1216.4075 0.4330 0.2411 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.3801 625.3823 541.2516 0.0000 0.0600 0.0418 0.0764

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 12.9163 1.1418 647.3403 26.1275 263.2569 2.0408

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 164921.625 0.426 685.202 685912.375 0.491013E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3423 Tt4 = 647.3403 T1 = 482.2698

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1034016.50 4296.0386 201.6786 2.4997 0.8341 3.1666 1.3423 37.3740

NASA/TM—2013-218094 H–30
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.640 EfDer = 0.999 SH = 0.684545E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.667 3709.801 5.167 482.269 1.000 1.000 0.980

 W Kg/sec = 29.394 Wdry = 64.622 WH2O = 0.044 lbm/sec H2O = 0.294g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 177.391 3847.346 1.381 0.249 53.370 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 145078.531 50727.059 1.601 831.557 519.452 619.754 1.193

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 418.72 -0.14 418.72 0.40 0.75 692.62

 MEAN 17.06 0.00 -0.02 418.72 -0.14 418.72 0.40 0.66

 HUB 12.51 0.00 -0.02 418.72 -0.14 418.72 0.40 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.92 50.47 7.45 667.88 788.40 4.64 468.19 467.80 15.71

 MEAN 52.84 47.20 5.64 552.31 693.20 4.64 468.19 467.80 15.71

 HUB 44.06 38.62 5.44 405.00 582.64 4.64 468.19 467.80 15.71

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 656.35 374.03 539.36 1075.39 0.61 7.29 6.52 16.04

 MEAN 18.04 691.79 414.16 554.11 1069.73 0.65 7.43 6.80 12.53

 HUB 15.00 797.58 543.56 583.67 1059.61 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.88 614.21 293.85 0.57 7719.18 0.92 0.91

 MEAN 583.90 579.53 169.74 0.54 7472.24 0.92 0.91 0.91 1.33

 HUB 485.61 586.54 57.95 0.55 8155.27 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.74 1.30 5.26 522.39 1.08 487.81 492.08 10.38

 MEAN 6.69 1.29 5.06 521.11 1.08 482.69 492.23 12.37

 HUB 6.84 1.32 4.72 524.66 1.09 473.59 496.65 17.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.74 28.58 24.20 4.38 0.93 0.35 1.80

 MEAN 36.78 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.96 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 732.2444 413.3544 604.4171 1066.3785 0.6867 -0.0749 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7372 4.9333 479.7093 494.0466 14.1805 34.3678 35.4000 1.0322

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 572.7131 140.1031 555.3120 1084.7616 0.5280 0.3147 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7073 5.5608 496.4117 491.2483 554.9116 0.0272 0.4254

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 568.5411 0.0000 568.5411 1085.1442 0.5239 0.3461 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5577 496.8010 491.8136 0.0000 0.0600 0.0402 0.3129

NASA/TM—2013-218094 H–31
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8759 6.6847 1.2937 522.7166 40.4497 218.9974 1.6977

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 252167.141 0.565 921.513 693620.625 0.117596E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.707 EfDer = 1.000 SH = 0.182768E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.667 3709.801 6.685 522.716 1.000 1.000 0.980

 W Kg/sec = 29.394 Wdry = 64.549 WH2O = 0.118 lbm/sec H2O = 0.909g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.755 3695.521 1.379 0.250 53.408 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 125187.688 50704.230 1.412 590.487 418.314 468.502 1.120

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 508.78 -0.18 508.78 0.47 0.77 662.71

 MEAN 18.08 0.00 -0.02 508.78 -0.18 508.78 0.47 0.71

 HUB 15.21 0.00 -0.02 508.78 -0.18 508.78 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.60 46.36 6.24 665.29 837.68 5.77 502.01 493.29 12.74

 MEAN 49.01 42.30 6.71 585.27 775.63 5.77 502.01 493.29 12.74

 HUB 44.07 37.84 6.23 492.41 708.17 5.77 502.01 493.29 12.74

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 587.92 304.06 503.18 1117.74 0.53 2.33 2.04 9.02

 MEAN 18.01 602.93 317.32 512.67 1113.50 0.54 2.40 2.13 7.35

 HUB 15.22 656.40 396.90 522.82 1109.57 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.08 616.97 357.02 0.55 6212.48 0.92 0.91

 MEAN 583.06 577.45 265.74 0.52 5718.07 0.92 0.91 0.91 1.46

 HUB 492.83 531.55 95.93 0.48 6044.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.16 1.22 6.77 554.88 1.06 527.24 507.73 6.41

 MEAN 8.03 1.20 6.60 552.32 1.06 523.25 507.01 7.17

 HUB 8.12 1.21 6.43 554.01 1.06 519.56 508.60 7.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.14 35.36 31.50 3.86 0.93 0.39 1.40

 MEAN 31.76 27.40 23.50 3.90 0.93 0.38 1.63

 HUB 37.20 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 671.3428 318.2098 591.1376 1107.5457 0.6062 -0.1780 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0879 6.3312 517.7172 508.8946 8.5161 28.2936 30.6000 2.3064

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 557.1552 118.1209 544.4900 1119.4745 0.4977 0.1505 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0654 6.8258 528.9307 506.9719 491.5697 0.0250 0.3026

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 582.3483 0.0000 582.3483 1117.0177 0.5213 0.2109 0.5911

NASA/TM—2013-218094 H–32
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7018 526.6407 507.6204 0.0000 0.0600 0.0384 0.0680

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 8.0451 1.2035 553.7380 31.0248 247.5375 1.9189

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 194105.891 0.444 709.336 622828.188 0.215587E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.27693E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.955 EfDer = 1.000 SH = 0.257644E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.667 3709.801 8.045 553.735 1.000 1.000 0.980

 W Kg/sec = 29.394 Wdry = 64.500 WH2O = 0.167 lbm/sec H2O = 1.483g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.084 3590.514 1.378 0.250 53.432 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 108186.070 50689.234 1.524 545.479 357.931 424.468 1.186

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 475.98 -0.16 475.98 0.42 0.72 628.84

 MEAN 17.74 0.00 -0.02 475.98 -0.16 475.98 0.42 0.66

 HUB 15.05 0.00 -0.02 475.98 -0.16 475.98 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.78 46.36 7.42 649.75 805.57 7.13 535.66 507.22 6.65

 MEAN 50.35 43.40 6.95 574.27 746.01 7.13 535.66 507.22 6.65

 HUB 45.68 38.84 6.84 487.23 681.25 7.13 535.66 507.22 6.65

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 563.68 303.58 474.95 1151.19 0.49 2.26 1.98 8.75

 MEAN 17.51 576.82 315.66 482.78 1147.36 0.50 2.34 2.07 6.78

 HUB 14.85 627.00 389.70 491.19 1143.77 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 641.33 582.80 337.75 0.51 6017.20 0.92 0.91

 MEAN 566.76 544.17 251.10 0.47 5529.10 0.92 0.91 0.91 1.49

 HUB 480.76 499.56 91.06 0.44 5789.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.66 1.20 8.22 584.80 1.06 559.46 519.69 3.78

 MEAN 9.52 1.18 8.03 582.28 1.05 555.74 519.00 4.14

 HUB 9.59 1.19 7.84 583.63 1.05 552.27 520.17 4.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.59 35.42 31.50 3.92 0.93 0.41 1.40

 MEAN 33.18 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.43 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 636.8553 317.7353 551.9320 1142.6238 0.5574 -0.1624 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.5724 7.7752 551.2301 520.3276 4.6521 29.9281 31.5000 1.5719

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.9593 116.0433 519.1480 1152.6997 0.4615 0.1564 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.5531 8.2724 560.9956 518.9307 451.3937 0.0224 0.3274

 

NASA/TM—2013-218094 H–33
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 542.6265 0.0000 542.6265 1151.6978 0.4712 0.2386 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2040 560.0560 519.1202 0.0000 0.0600 0.0375 0.1125

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8829 9.5296 1.1845 583.5226 29.8361 236.5018 1.8333

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 187151.906 0.455 683.923 596214.125 0.281942E-02

 

Melt Ratio at Stator LE, Throat, TE

0.44207E+00 0.53106E+00 0.77726E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.325 EfDer = 0.999 SH = 0.305969E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.667 3709.801 9.530 583.508 1.000 1.000 0.980

 W Kg/sec = 29.394 Wdry = 64.469 WH2O = 0.198 lbm/sec H2O = 2.011g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 105.802 3497.679 1.377 0.251 53.448 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 94762.789 50679.539 1.654 513.330 310.309 395.845 1.276

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 443.04 -0.15 443.04 0.38 0.66 587.86

 MEAN 16.97 0.00 -0.02 443.04 -0.15 443.04 0.38 0.61

 HUB 14.32 0.00 -0.02 443.04 -0.15 443.04 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.61 46.36 8.25 623.53 765.02 8.63 567.88 518.58 3.51

 MEAN 51.13 43.80 7.33 549.41 705.91 8.63 567.88 518.58 3.51

 HUB 46.31 37.84 8.47 463.60 641.36 8.63 567.88 518.58 3.51

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 533.50 295.02 444.50 1181.57 0.45 2.16 1.89 8.34

 MEAN 16.57 543.08 301.92 451.42 1177.82 0.46 2.24 1.97 6.35

 HUB 13.89 586.35 365.08 458.83 1174.25 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 611.22 545.49 316.20 0.46 5572.98 0.92 0.91

 MEAN 536.56 508.76 234.64 0.43 5006.63 0.92 0.91 0.91 1.51

 HUB 449.68 466.56 84.60 0.40 5073.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.19 1.17 9.75 612.23 1.05 589.57 529.35 2.31

 MEAN 11.01 1.16 9.54 609.31 1.04 585.83 528.50 2.50

 HUB 11.03 1.16 9.33 609.65 1.04 582.28 529.07 2.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.57 35.43 31.50 3.93 0.93 0.42 1.40

 MEAN 33.78 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.51 10.45 6.50 3.95 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 584.5731 303.6216 499.5394 1175.0964 0.4975 -0.1128 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.0647 9.3677 583.2105 529.3630 2.6881 31.2914 32.4000 1.1086

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 493.9328 110.7747 481.3508 1182.8929 0.4176 0.1805 2.2705

 

NASA/TM—2013-218094 H–34
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.0498 9.8190 590.9902 528.5789 432.2457 0.0197 0.3492

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 489.9023 0.0000 489.9023 1183.1666 0.4141 0.2633 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8146 591.3126 528.8648 0.0000 0.0600 0.0370 0.1777

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8811 11.0232 1.1567 610.3925 26.8862 238.9314 1.8522

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 169015.156 0.452 617.645 590502.813 0.366617E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.576 EfDer = 0.999 SH = 0.474568E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.667 3709.801 11.023 610.391 1.000 1.000 0.980

 W Kg/sec = 29.394 Wdry = 64.360 WH2O = 0.307 lbm/sec H2O = 3.504g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 93.549 3419.827 1.375 0.252 53.502 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84353.805 50645.605 1.856 509.668 274.656 384.739 1.401 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 397.18 -0.14 397.18 0.33 0.60 546.72

 MEAN 15.91 0.00 -0.02 397.18 -0.14 397.18 0.33 0.55

 HUB 13.07 0.00 -0.02 397.18 -0.14 397.18 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.20 47.36 8.84 593.09 713.91 10.22 597.90 529.59 2.82

 MEAN 52.38 44.80 7.58 515.17 650.61 10.22 597.90 529.59 2.82

 HUB 46.82 38.84 7.98 423.13 580.44 10.22 597.90 529.59 2.82

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 497.60 293.31 401.97 1209.09 0.41 2.05 1.78 7.43

 MEAN 15.50 500.27 288.55 408.67 1204.91 0.42 2.13 1.86 5.75

 HUB 12.59 531.57 331.24 415.75 1200.87 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 580.79 494.19 287.49 0.41 5264.41 0.92 0.91

 MEAN 501.72 460.93 213.18 0.38 4473.94 0.92 0.91 0.91 1.55

 HUB 407.59 422.70 76.35 0.35 4172.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.75 1.16 11.37 637.38 1.04 617.77 539.41 2.10

 MEAN 12.48 1.13 11.10 633.32 1.04 613.51 538.22 2.28

 HUB 12.37 1.12 10.84 631.78 1.04 609.41 538.08 2.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.12 35.57 31.50 4.07 0.93 0.45 1.40

 MEAN 35.22 27.55 23.50 4.05 0.93 0.43 1.64

 HUB 38.55 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 554.5460 293.8368 470.2991 1201.1766 0.4617 -0.1900 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.5048 10.8322 609.8520 539.1212 2.4759 31.9966 33.0000 1.0034

 

NASA/TM—2013-218094 H–35
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 474.8077 108.4227 462.2628 1207.5350 0.3932 0.0952 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.4811 11.2404 616.3447 538.3982 410.5396 0.0366 0.3616

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 460.3365 0.0000 460.3365 1208.5339 0.3809 0.2867 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.3118 617.4219 538.7219 0.0000 0.0600 0.0369 0.1452

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8814 12.4805 1.1322 634.1583 23.7684 246.0739 1.9075

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 150369.172 0.446 549.505 601716.688 0.580845E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3149 Tt4 = 634.1583 T1 = 482.2690

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 952809.31 3481.9211 177.3912 2.4153 0.8671 5.6405 1.3149 37.3740

NASA/TM—2013-218094 H–36
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.996 EfDer = 0.999 SH = 0.697129E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.529 3679.978 5.167 482.269 1.000 1.000 0.980

 W Kg/sec = 28.877 Wdry = 63.485 WH2O = 0.044 lbm/sec H2O = 0.300g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 174.270 3816.417 1.381 0.249 53.371 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 142065.313 49834.273 1.629 831.557 510.316 619.754 1.214

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 410.02 -0.14 410.02 0.39 0.74 687.05

 MEAN 17.06 0.00 -0.02 410.02 -0.14 410.02 0.39 0.65

 HUB 12.51 0.00 -0.02 410.02 -0.14 410.02 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.25 50.47 7.78 662.51 779.25 4.66 468.77 467.79 15.65

 MEAN 53.20 47.20 6.00 547.87 684.42 4.66 468.77 467.79 15.65

 HUB 44.43 38.62 5.81 401.74 574.13 4.66 468.77 467.79 15.65

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 647.40 375.12 527.65 1076.19 0.60 7.29 6.52 16.04

 MEAN 18.04 681.58 413.24 542.02 1070.54 0.64 7.43 6.80 12.53

 HUB 15.00 784.00 538.31 569.98 1060.69 0.74 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 662.51 600.84 287.39 0.56 7741.71 0.92 0.91

 MEAN 579.21 566.86 165.97 0.53 7455.56 0.92 0.91 0.91 1.34

 HUB 481.71 572.78 56.60 0.54 8076.43 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.30 5.29 522.18 1.08 488.54 491.94 10.35

 MEAN 6.67 1.29 5.09 520.71 1.08 483.42 491.96 12.33

 HUB 6.81 1.32 4.75 523.91 1.09 474.57 496.06 16.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.41 28.58 24.20 4.38 0.93 0.36 1.80

 MEAN 37.32 17.03 12.70 4.33 0.92 0.31 2.22

 HUB 43.36 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 720.2131 412.4341 590.4278 1067.4303 0.6747 -0.0723 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7193 4.9712 480.6616 493.6881 14.0194 34.9356 35.4000 0.4644

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 560.1656 137.0336 543.1458 1085.5087 0.5160 0.3240 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6914 5.5931 497.1010 490.9945 554.9116 0.0265 0.4329

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 555.8933 0.0000 555.8933 1085.8917 0.5119 0.3551 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5919 497.4905 491.5688 0.0000 0.0600 0.0385 0.3233

NASA/TM—2013-218094 H–37
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8785 6.6712 1.2911 522.2640 39.9973 216.7782 1.6805

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 249365.016 0.568 895.239 679214.250 0.120450E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.072 EfDer = 1.000 SH = 0.187530E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.529 3679.978 6.671 522.263 1.000 1.000 0.980

 W Kg/sec = 28.877 Wdry = 63.410 WH2O = 0.119 lbm/sec H2O = 0.936g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.467 3667.400 1.379 0.250 53.409 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 122594.742 49811.160 1.435 590.487 411.620 468.502 1.138

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 498.25 -0.17 498.25 0.46 0.76 657.66

 MEAN 18.08 0.00 -0.02 498.25 -0.17 498.25 0.46 0.70

 HUB 15.21 0.00 -0.02 498.25 -0.17 498.25 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.95 46.36 6.59 659.94 827.04 5.79 502.41 493.10 12.92

 MEAN 49.37 42.30 7.07 580.56 765.18 5.79 502.41 493.10 12.92

 HUB 44.44 37.84 6.60 488.45 697.85 5.79 502.41 493.10 12.92

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 580.50 305.91 493.35 1117.92 0.52 2.33 2.04 9.02

 MEAN 18.01 594.82 317.97 502.70 1113.65 0.53 2.40 2.13 7.35

 HUB 15.22 647.16 394.92 512.69 1109.67 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 655.77 604.81 349.86 0.54 6250.16 0.92 0.91

 MEAN 578.37 566.14 260.40 0.51 5729.66 0.92 0.91 0.91 1.47

 HUB 488.87 521.23 93.95 0.47 6014.47 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.14 1.22 6.79 554.36 1.06 527.42 507.58 6.55

 MEAN 8.01 1.20 6.61 551.69 1.06 523.40 506.81 7.34

 HUB 8.08 1.21 6.44 553.15 1.06 519.66 508.30 8.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.80 35.34 31.50 3.84 0.93 0.40 1.40

 MEAN 32.31 27.38 23.50 3.88 0.93 0.39 1.63

 HUB 37.61 10.38 6.50 3.88 0.93 0.40 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 660.6901 318.8586 578.6541 1108.0347 0.5963 -0.1733 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0624 6.3599 518.1830 508.6222 8.6296 28.8563 30.6000 1.7437

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 545.6069 115.6725 533.2042 1119.8324 0.4872 0.1629 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0418 6.8523 529.2784 506.7252 491.5697 0.0241 0.3105

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 569.8785 0.0000 569.8785 1117.5144 0.5100 0.2199 0.5911

NASA/TM—2013-218094 H–38
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7343 527.1184 507.3477 0.0000 0.0600 0.0376 0.0822

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8804 8.0219 1.2025 553.0635 30.8035 244.2704 1.8936

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 192751.703 0.448 691.993 609614.500 0.220904E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.11183E-02 0.36965E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.271 EfDer = 1.000 SH = 0.263204E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.529 3679.978 8.022 553.061 1.000 1.000 0.980

 W Kg/sec = 28.877 Wdry = 63.362 WH2O = 0.167 lbm/sec H2O = 1.518g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.209 3563.821 1.378 0.250 53.434 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 106114.883 49796.273 1.548 545.479 352.446 424.468 1.204 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 466.86 -0.16 466.86 0.41 0.71 624.16

 MEAN 17.74 0.00 -0.02 466.86 -0.16 466.86 0.41 0.65

 HUB 15.05 0.00 -0.02 466.86 -0.16 466.86 0.41 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.09 46.36 7.73 644.53 795.98 7.14 535.68 507.01 6.80

 MEAN 50.67 43.40 7.27 569.65 736.65 7.14 535.68 507.01 6.80

 HUB 46.00 38.84 7.16 483.31 672.09 7.14 535.68 507.01 6.80

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 557.06 304.67 466.37 1150.95 0.48 2.26 1.98 8.75

 MEAN 17.51 569.61 315.79 474.06 1147.10 0.50 2.34 2.07 6.78

 HUB 14.85 618.78 387.61 482.34 1143.49 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 636.18 572.18 331.51 0.50 6038.75 0.92 0.91

 MEAN 562.20 534.28 246.41 0.47 5531.26 0.92 0.91 0.91 1.50

 HUB 476.89 490.53 89.28 0.43 5758.42 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.62 1.20 8.22 583.98 1.06 559.23 519.48 3.89

 MEAN 9.48 1.18 8.03 581.38 1.05 555.51 518.75 4.26

 HUB 9.54 1.19 7.84 582.55 1.05 552.01 519.84 4.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.16 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.67 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.79 10.49 6.50 3.99 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 627.7856 317.8630 541.3667 1142.6016 0.5494 -0.1590 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.5329 7.7875 551.2172 520.0337 4.7579 30.4193 31.5000 1.0807

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 521.8695 113.8423 509.3012 1152.6062 0.4528 0.1672 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.5150 8.2831 560.9141 518.6395 451.3937 0.0218 0.3344

 

NASA/TM—2013-218094 H–39
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 532.1992 0.0000 532.1992 1151.6505 0.4621 0.2462 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2173 560.0192 518.8234 0.0000 0.0600 0.0370 0.1239

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8836 9.4919 1.1832 582.5888 29.5784 233.8314 1.8126

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 185566.375 0.459 666.197 584354.313 0.287630E-02

 

Melt Ratio at Stator LE, Throat, TE

0.45953E+00 0.55001E+00 0.79997E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.597 EfDer = 0.999 SH = 0.311732E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.529 3679.978 9.492 582.574 1.000 1.000 0.980

 W Kg/sec = 28.877 Wdry = 63.331 WH2O = 0.198 lbm/sec H2O = 2.049g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.270 3472.340 1.377 0.251 53.449 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 93091.844 49786.707 1.679 513.330 305.826 395.845 1.294

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 435.23 -0.15 435.23 0.38 0.65 583.60

 MEAN 16.97 0.00 -0.02 435.23 -0.15 435.23 0.38 0.60

 HUB 14.32 0.00 -0.02 435.23 -0.15 435.23 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.87 46.36 8.51 618.51 756.42 8.62 567.50 518.31 3.61

 MEAN 51.40 43.80 7.60 545.00 697.57 8.62 567.50 518.31 3.61

 HUB 46.59 37.84 8.75 459.87 633.28 8.62 567.50 518.31 3.61

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 527.60 295.51 437.08 1180.94 0.45 2.16 1.89 8.34

 MEAN 16.57 536.66 301.64 443.87 1177.19 0.46 2.24 1.97 6.35

 HUB 13.89 579.04 362.99 451.13 1173.62 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 606.31 536.32 310.80 0.45 5582.04 0.92 0.91

 MEAN 532.25 500.20 230.62 0.42 5001.82 0.92 0.91 0.91 1.52

 HUB 446.06 458.72 83.07 0.39 5044.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.14 1.17 9.73 611.10 1.05 588.95 529.08 2.40

 MEAN 10.96 1.15 9.52 608.14 1.04 585.21 528.21 2.59

 HUB 10.97 1.16 9.31 608.35 1.04 581.66 528.73 2.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.06 35.42 31.50 3.92 0.93 0.43 1.40

 MEAN 34.20 27.45 23.50 3.95 0.93 0.42 1.62

 HUB 38.82 10.43 6.50 3.93 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 577.0691 303.3323 490.9157 1174.5856 0.4913 -0.1109 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.0077 9.3570 582.7137 529.0629 2.7839 31.7115 32.4000 0.6885

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 485.4183 108.8651 473.0532 1182.3528 0.4106 0.1894 2.2705

 

NASA/TM—2013-218094 H–40
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9937 9.8071 590.4616 528.2704 432.2457 0.0194 0.3552

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 481.4659 0.0000 481.4659 1182.6147 0.4071 0.2698 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8024 590.7723 528.5637 0.0000 0.0600 0.0368 0.1863

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8814 10.9676 1.1555 609.1967 26.6244 236.6041 1.8341

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 167405.250 0.455 600.997 579407.750 0.374949E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.803 EfDer = 0.999 SH = 0.485137E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.529 3679.978 10.968 609.195 1.000 1.000 0.980

 W Kg/sec = 28.877 Wdry = 63.221 WH2O = 0.308 lbm/sec H2O = 3.577g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.278 3395.663 1.375 0.252 53.506 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 82992.508 49752.402 1.881 509.668 270.942 384.739 1.420

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 390.77 -0.13 390.77 0.33 0.59 542.86

 MEAN 15.91 0.00 -0.02 390.77 -0.13 390.77 0.33 0.54

 HUB 13.07 0.00 -0.02 390.77 -0.13 390.77 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.41 47.36 9.05 588.33 706.39 10.19 597.11 529.33 2.94

 MEAN 52.60 44.80 7.80 511.03 643.42 10.19 597.11 529.33 2.94

 HUB 47.06 38.84 8.22 419.73 573.57 10.19 597.11 529.33 2.94

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 492.55 293.12 395.83 1208.06 0.41 2.05 1.78 7.43

 MEAN 15.50 494.76 287.88 402.38 1203.91 0.41 2.13 1.86 5.75

 HUB 12.59 525.28 329.24 409.29 1199.90 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 576.12 486.59 283.00 0.40 5261.10 0.92 0.91

 MEAN 497.69 453.79 209.81 0.38 4463.64 0.92 0.91 0.91 1.56

 HUB 404.31 416.12 75.07 0.35 4146.90 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.67 1.16 11.32 635.94 1.04 616.74 539.11 2.19

 MEAN 12.40 1.13 11.06 631.89 1.04 612.51 537.92 2.37

 HUB 12.29 1.12 10.80 630.28 1.03 608.44 537.75 2.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.52 35.56 31.50 4.06 0.93 0.46 1.40

 MEAN 35.58 27.54 23.50 4.04 0.93 0.43 1.64

 HUB 38.81 10.39 6.50 3.89 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 547.8172 293.1620 462.7740 1200.3093 0.4564 -0.1878 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.4277 10.8001 608.9862 538.8074 2.5771 32.3538 33.0000 0.6462

 

NASA/TM—2013-218094 H–41
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 467.1801 106.6810 454.8367 1206.6514 0.3872 0.1043 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.4055 11.2075 615.4584 538.0750 410.5396 0.0359 0.3666

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 453.0406 0.0000 453.0406 1207.6102 0.3752 0.2922 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.2756 616.4940 538.4089 0.0000 0.0600 0.0367 0.1531

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8816 12.4043 1.1310 632.6986 23.5046 244.0947 1.8922

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 148747.703 0.448 534.016 591035.125 0.593610E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3119 Tt4 = 632.6986 T1 = 482.2688

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 943836.06 3388.4429 174.2700 2.4006 0.8685 5.9960 1.3119 37.3740

NASA/TM—2013-218094 H–42
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.347 EfDer = 1.000 SH = 0.709664E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.402 3650.005 5.167 482.269 1.000 1.000 0.980

 W Kg/sec = 28.365 Wdry = 62.358 WH2O = 0.044 lbm/sec H2O = 0.307g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 171.180 3785.334 1.381 0.249 53.371 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 139114.016 48950.289 1.659 831.557 501.271 619.754 1.236

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 401.50 -0.14 401.50 0.38 0.73 681.46

 MEAN 17.06 0.00 -0.02 401.50 -0.14 401.50 0.38 0.64

 HUB 12.51 0.00 -0.02 401.50 -0.14 401.50 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.58 50.47 8.11 657.11 770.18 4.68 469.33 467.78 15.61

 MEAN 53.55 47.20 6.35 543.40 675.75 4.68 469.33 467.78 15.61

 HUB 44.79 38.62 6.17 398.47 565.77 4.68 469.33 467.78 15.61

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 638.73 375.98 516.34 1076.92 0.59 7.29 6.52 16.04

 MEAN 18.04 671.65 412.17 530.32 1071.27 0.63 7.43 6.80 12.53

 HUB 15.00 770.86 533.09 556.82 1061.70 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 657.11 587.92 281.13 0.55 7759.37 0.92 0.91

 MEAN 574.49 554.61 162.32 0.52 7436.21 0.92 0.91 0.91 1.36

 HUB 477.78 559.56 55.31 0.53 7998.08 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.30 5.31 521.95 1.08 489.20 491.79 10.34

 MEAN 6.65 1.29 5.12 520.29 1.08 484.08 491.70 12.30

 HUB 6.78 1.31 4.79 523.17 1.08 475.47 495.49 16.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.06 28.57 24.20 4.37 0.93 0.37 1.80

 MEAN 37.85 17.02 12.70 4.32 0.93 0.32 2.22

 HUB 43.75 -5.67 -9.30 3.63 0.93 0.18 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 708.6157 411.3665 576.9868 1068.3878 0.6633 -0.0698 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7005 5.0059 481.5294 493.3390 13.8940 35.4872 35.4000 -0.0872

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 548.1186 134.0865 531.4648 1086.1671 0.5046 0.3329 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6742 5.6217 497.7094 490.7397 554.9116 0.0260 0.4402

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 543.7916 0.0000 543.7916 1086.5460 0.5005 0.3635 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.6219 498.0950 491.3231 0.0000 0.0600 0.0371 0.3331

NASA/TM—2013-218094 H–43
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 6.6560 1.2881 521.7999 39.5333 214.6261 1.6638

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 246490.078 0.571 869.225 665104.125 0.123270E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.423 EfDer = 0.999 SH = 0.192211E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.402 3650.005 6.656 521.799 1.000 1.000 0.980

 W Kg/sec = 28.365 Wdry = 62.282 WH2O = 0.120 lbm/sec H2O = 0.962g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 138.230 3639.147 1.379 0.250 53.411 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 120097.188 48926.922 1.458 590.487 405.076 468.502 1.157

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 488.09 -0.17 488.09 0.45 0.75 652.60

 MEAN 18.08 0.00 -0.02 488.09 -0.17 488.09 0.45 0.69

 HUB 15.21 0.00 -0.02 488.09 -0.17 488.09 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.30 46.36 6.94 654.56 816.65 5.81 502.75 492.91 13.12

 MEAN 49.72 42.30 7.42 575.83 754.99 5.81 502.75 492.91 13.12

 HUB 44.80 37.84 6.96 484.47 687.83 5.81 502.75 492.91 13.12

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 573.33 307.42 483.94 1118.01 0.51 2.33 2.04 9.02

 MEAN 18.01 586.98 318.39 493.12 1113.72 0.53 2.40 2.13 7.35

 HUB 15.22 638.20 392.87 502.94 1109.71 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 650.42 593.17 343.00 0.53 6281.01 0.92 0.91

 MEAN 573.66 555.28 255.27 0.50 5737.21 0.92 0.91 0.91 1.48

 HUB 484.89 511.29 92.02 0.46 5983.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.12 1.22 6.80 553.79 1.06 527.51 507.42 6.71

 MEAN 7.98 1.20 6.62 551.02 1.06 523.47 506.59 7.51

 HUB 8.04 1.21 6.45 552.27 1.06 519.71 507.98 8.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.43 35.33 31.50 3.83 0.93 0.41 1.40

 MEAN 32.85 27.37 23.50 3.87 0.93 0.39 1.63

 HUB 38.00 10.37 6.50 3.87 0.93 0.40 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 650.5066 319.2825 566.7605 1108.4163 0.5869 -0.1689 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0335 6.3829 518.5479 508.3386 8.7590 29.3946 30.6000 1.2054

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 534.6313 113.3456 522.4781 1120.0807 0.4773 0.1745 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0146 6.8724 529.5222 506.4642 491.5697 0.0233 0.3181

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 558.0699 0.0000 558.0699 1117.8868 0.4992 0.2282 0.5911

NASA/TM—2013-218094 H–44
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7596 527.4786 507.0648 0.0000 0.0600 0.0371 0.0953

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 7.9950 1.2012 552.3557 30.5604 241.2023 1.8698

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191259.109 0.452 674.458 596758.250 0.226139E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.22866E-02 0.45120E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.570 EfDer = 0.999 SH = 0.268747E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.402 3650.005 7.995 552.353 1.000 1.000 0.980

 W Kg/sec = 28.365 Wdry = 62.235 WH2O = 0.168 lbm/sec H2O = 1.551g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 118.400 3537.058 1.378 0.250 53.435 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 104134.664 48912.129 1.571 545.479 347.154 424.468 1.223

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 458.15 -0.16 458.15 0.41 0.70 619.48

 MEAN 17.74 0.00 -0.02 458.15 -0.16 458.15 0.41 0.65

 HUB 15.05 0.00 -0.02 458.15 -0.16 458.15 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.38 46.36 8.02 639.28 786.63 7.15 535.61 506.78 6.97

 MEAN 50.97 43.40 7.57 565.01 727.54 7.15 535.61 506.78 6.97

 HUB 46.31 38.84 7.47 479.38 663.22 7.15 535.61 506.78 6.97

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 550.68 305.44 458.20 1150.61 0.48 2.26 1.98 8.75

 MEAN 17.51 562.64 315.65 465.76 1146.76 0.49 2.34 2.07 6.78

 HUB 14.85 610.80 385.38 473.88 1143.13 0.53 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.99 562.08 325.55 0.49 6053.94 0.92 0.91

 MEAN 557.62 524.87 241.98 0.46 5528.72 0.92 0.91 0.91 1.50

 HUB 473.01 481.92 87.63 0.42 5725.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.58 1.20 8.21 583.10 1.06 558.91 519.23 4.00

 MEAN 9.44 1.18 8.02 580.43 1.05 555.18 518.47 4.38

 HUB 9.49 1.19 7.84 581.43 1.05 551.68 519.49 4.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.69 35.39 31.50 3.89 0.93 0.42 1.40

 MEAN 34.13 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 39.12 10.48 6.50 3.98 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 619.0922 317.7199 531.3467 1142.4684 0.5419 -0.1559 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4875 7.7923 551.0970 519.7184 4.8757 30.8774 31.5000 0.6226

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 512.3386 111.7632 499.9998 1152.3909 0.4446 0.1771 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4707 8.2849 560.7137 518.3263 451.3937 0.0213 0.3408

 

NASA/TM—2013-218094 H–45
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 522.3647 0.0000 522.3647 1151.4767 0.4536 0.2532 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2215 559.8590 518.5056 0.0000 0.0600 0.0367 0.1343

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8840 9.4479 1.1817 581.5986 29.2974 231.3744 1.7936

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183834.125 0.462 648.275 572796.313 0.293337E-02

 

Melt Ratio at Stator LE, Throat, TE

0.47454E+00 0.56629E+00 0.81956E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.848 EfDer = 0.999 SH = 0.317561E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.402 3650.005 9.448 581.583 1.000 1.000 0.980

 W Kg/sec = 28.365 Wdry = 62.204 WH2O = 0.198 lbm/sec H2O = 2.086g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 102.810 3446.990 1.377 0.251 53.451 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91505.820 48902.680 1.702 513.330 301.553 395.845 1.313

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 427.81 -0.15 427.81 0.37 0.65 579.34

 MEAN 16.97 0.00 -0.02 427.81 -0.15 427.81 0.37 0.60

 HUB 14.32 0.00 -0.02 427.81 -0.15 427.81 0.37 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.12 46.36 8.76 613.48 748.03 8.61 567.02 518.02 3.73

 MEAN 51.65 43.80 7.85 540.56 689.48 8.61 567.02 518.02 3.73

 HUB 46.84 37.84 9.00 456.13 625.47 8.61 567.02 518.02 3.73

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 521.90 295.66 430.08 1180.20 0.44 2.16 1.89 8.34

 MEAN 16.57 530.46 301.10 436.72 1176.46 0.45 2.24 1.97 6.35

 HUB 13.89 571.96 360.76 443.84 1172.90 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 601.37 527.66 305.71 0.45 5584.87 0.92 0.91

 MEAN 527.92 492.11 226.81 0.42 4992.92 0.92 0.91 0.91 1.53

 HUB 442.43 451.29 81.67 0.38 5013.04 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.08 1.17 9.70 609.89 1.05 588.21 528.78 2.49

 MEAN 10.89 1.15 9.50 606.89 1.04 584.49 527.89 2.70

 HUB 10.90 1.15 9.29 606.99 1.04 580.96 528.37 2.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.51 35.41 31.50 3.91 0.93 0.43 1.40

 MEAN 34.58 27.45 23.50 3.95 0.93 0.42 1.62

 HUB 39.10 10.43 6.50 3.93 0.93 0.43 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 569.8755 302.7946 482.7769 1173.9587 0.4854 -0.1092 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9422 9.3366 582.1017 528.7291 2.8872 32.0957 32.4000 0.3043

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 477.4150 107.0702 465.2538 1181.6843 0.4040 0.1974 2.2705

 

NASA/TM—2013-218094 H–46
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9290 9.7842 589.8046 527.9285 432.2457 0.0191 0.3606

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 473.5384 0.0000 473.5384 1181.9358 0.4006 0.2756 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7791 590.1042 528.2288 0.0000 0.0600 0.0366 0.1939

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8814 10.9033 1.1540 607.9230 26.3413 234.5055 1.8179

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 165659.844 0.458 584.185 568581.500 0.383130E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 8.008 EfDer = 0.998 SH = 0.495408E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.402 3650.005 10.903 607.922 1.000 1.000 0.980

 W Kg/sec = 28.365 Wdry = 62.093 WH2O = 0.309 lbm/sec H2O = 3.644g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 91.080 3371.532 1.374 0.252 53.509 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 81707.961 48868.113 1.906 509.668 267.441 384.739 1.439

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 384.72 -0.13 384.72 0.32 0.59 539.00

 MEAN 15.91 0.00 -0.02 384.72 -0.13 384.72 0.32 0.54

 HUB 13.07 0.00 -0.02 384.72 -0.13 384.72 0.32 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.61 47.36 9.25 583.53 699.05 10.15 596.21 529.03 3.06

 MEAN 52.81 44.80 8.01 506.87 636.44 10.15 596.21 529.03 3.06

 HUB 47.27 38.84 8.43 416.31 566.95 10.15 596.21 529.03 3.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 487.63 292.64 390.06 1206.91 0.40 2.05 1.78 7.43

 MEAN 15.50 489.41 286.97 396.45 1202.80 0.41 2.13 1.86 5.75

 HUB 12.59 519.20 327.10 403.20 1198.83 0.43 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 571.43 479.45 278.79 0.40 5252.35 0.92 0.91

 MEAN 493.63 447.08 206.66 0.37 4449.45 0.92 0.91 0.91 1.57

 HUB 401.02 409.92 73.92 0.34 4119.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.58 1.15 11.27 634.40 1.04 615.58 538.77 2.29

 MEAN 12.31 1.13 11.01 630.35 1.04 611.40 537.57 2.48

 HUB 12.21 1.12 10.75 628.69 1.03 607.36 537.38 2.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.88 35.56 31.50 4.06 0.93 0.46 1.40

 MEAN 35.90 27.53 23.50 4.03 0.93 0.43 1.64

 HUB 39.05 10.39 6.50 3.89 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 541.3615 292.2320 455.7111 1199.3174 0.4514 -0.1859 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3398 10.7561 607.9933 538.4520 2.6853 32.6707 33.0000 0.3293

 

NASA/TM—2013-218094 H–47
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 460.0562 105.0542 447.9010 1205.6288 0.3816 0.1122 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3188 11.1613 614.4297 537.7109 410.5396 0.0354 0.3710

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 446.2201 0.0000 446.2201 1206.5515 0.3698 0.2969 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.2262 615.4276 538.0544 0.0000 0.0600 0.0366 0.1600

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8815 12.3172 1.1297 631.1430 23.2227 242.3544 1.8787

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 147008.063 0.450 518.411 580591.438 0.605940E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3087 Tt4 = 631.1430 T1 = 482.2687

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 934251.19 3294.5532 171.1796 2.3837 0.8695 6.3475 1.3087 37.3740

NASA/TM—2013-218094 H–48
10μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.970 EfDer = 0.985 SH = 0.992751E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.525 3889.388 5.167 462.090 1.000 1.000 0.980

 W Kg/sec = 34.329 Wdry = 75.517 WH2O = 0.007 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.792 4120.723 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 167381.375 59258.020 1.401 831.557 593.615 619.754 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 483.09 -0.17 483.09 0.47 0.83 741.83

 MEAN 17.06 0.00 -0.02 483.09 -0.17 483.09 0.47 0.74

 HUB 12.51 0.00 -0.02 483.09 -0.17 483.09 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.40 50.47 4.93 700.21 850.82 4.45 443.32 453.00 7.19

 MEAN 50.17 47.20 2.97 579.04 754.23 4.45 443.32 453.00 7.19

 HUB 41.32 38.62 2.70 424.61 643.28 4.45 443.32 453.00 7.19

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 725.65 355.06 632.85 1044.10 0.69 7.29 6.52 16.04

 MEAN 18.04 770.38 412.57 650.59 1038.69 0.74 7.43 6.80 12.53

 HUB 15.00 909.15 579.42 700.59 1024.99 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.21 720.85 345.15 0.69 7328.26 0.92 0.90

 MEAN 612.17 680.51 199.59 0.66 7444.04 0.92 0.90 0.90 1.21

 HUB 509.12 704.11 70.30 0.69 8693.33 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 502.09 1.09 459.75 479.29 4.53

 MEAN 6.81 1.32 4.75 502.73 1.09 455.00 479.96 5.46

 HUB 7.12 1.38 4.29 509.55 1.10 443.08 485.22 8.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.29 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.38 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.59 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 831.8768 411.7729 722.8154 1031.9886 0.8061 -0.1057 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8832 4.5086 449.1398 481.6946 7.1449 29.6693 35.4000 5.7307

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 676.8344 165.5743 656.2697 1053.3680 0.6425 0.2318 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8131 5.1777 467.9523 480.4142 554.9116 0.0412 0.3616

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 678.2740 0.0000 678.2740 1053.1658 0.6440 0.2576 1.3089

NASA/TM—2013-218094 H–49
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1204 467.8000 480.4042 0.0000 0.0600 0.0711 0.2063

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8264 6.7458 1.3055 504.7875 42.6995 237.2524 1.8392

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 265523.625 0.542 1133.245 862723.750 0.148003E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.618 EfDer = 0.990 SH = 0.214637E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.525 3889.388 6.746 504.787 1.000 1.000 0.980

 W Kg/sec = 34.329 Wdry = 75.508 WH2O = 0.016 lbm/sec H2O = 0.107g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.355 3942.621 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146256.797 59255.340 1.242 590.487 475.290 468.502 0.986

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 594.45 -0.20 594.45 0.56 0.86 707.02

 MEAN 18.08 0.00 -0.02 594.45 -0.20 594.45 0.56 0.80

 HUB 15.21 0.00 -0.02 594.45 -0.20 594.45 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.57 46.36 3.21 697.49 916.60 5.47 476.39 480.48 4.04

 MEAN 45.92 42.30 3.62 613.60 854.47 5.47 476.39 480.48 4.04

 HUB 40.98 37.84 3.14 516.25 787.46 5.47 476.39 480.48 4.04

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 646.16 276.83 583.85 1091.06 0.59 2.33 2.04 9.02

 MEAN 18.01 665.82 301.77 593.51 1087.51 0.61 2.40 2.13 7.35

 HUB 15.22 726.86 404.15 604.15 1084.32 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 693.08 717.04 416.25 0.66 5657.08 0.92 0.91

 MEAN 611.28 669.37 309.51 0.62 5438.58 0.92 0.91 0.91 1.37

 HUB 516.69 614.54 112.54 0.57 6155.52 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.20 1.22 6.49 535.65 1.06 502.09 496.15 1.78

 MEAN 8.14 1.21 6.34 534.46 1.06 498.83 495.67 1.97

 HUB 8.34 1.24 6.19 538.37 1.07 495.91 497.75 2.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.37 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 26.95 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.78 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 762.4059 302.6180 699.7750 1077.2028 0.7078 -0.2337 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2085 5.8991 489.4503 496.9626 2.7133 23.3861 30.6000 7.2139

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 658.0977 139.5214 643.1379 1090.2357 0.6036 0.0268 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1503 6.3904 501.3551 496.3201 491.5697 0.0408 0.2244

 

NASA/TM—2013-218094 H–50
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 699.8377 0.0000 699.8377 1085.2544 0.6449 0.1032 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1373 496.8038 496.4650 0.0000 0.0600 0.0724 -0.1073

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8276 8.0907 1.1994 536.1587 31.3734 279.3031 2.1651

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195233.063 0.406 833.248 780500.875 0.249548E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.991 EfDer = 0.992 SH = 0.307016E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.525 3889.388 8.091 536.158 1.000 1.000 0.980

 W Kg/sec = 34.329 Wdry = 75.501 WH2O = 0.023 lbm/sec H2O = 0.177g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.510 3825.540 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 125909.281 59253.191 1.335 545.479 408.452 424.468 1.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 553.97 -0.19 553.97 0.50 0.80 670.00

 MEAN 17.74 0.00 -0.02 553.97 -0.19 553.97 0.50 0.74

 HUB 15.05 0.00 -0.02 553.97 -0.19 553.97 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.89 46.36 4.53 681.20 878.17 6.82 511.51 496.15 1.77

 MEAN 47.39 43.40 3.99 602.07 818.29 6.82 511.51 496.15 1.77

 HUB 42.69 38.84 3.85 510.82 753.67 6.82 511.51 496.15 1.77

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 616.71 279.84 549.57 1127.07 0.55 2.26 1.98 8.75

 MEAN 17.51 634.45 302.54 557.67 1123.77 0.56 2.34 2.07 6.78

 HUB 14.85 692.17 397.56 566.60 1120.77 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.38 675.36 392.54 0.60 5547.44 0.92 0.91

 MEAN 594.20 629.33 291.65 0.56 5299.88 0.92 0.91 0.91 1.40

 HUB 504.03 576.52 106.47 0.51 5906.65 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.70 1.20 7.93 566.41 1.06 535.86 509.54 0.95

 MEAN 9.62 1.19 7.77 565.06 1.05 532.72 509.04 1.03

 HUB 9.81 1.21 7.61 568.37 1.06 529.88 510.59 1.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.99 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.48 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 35.06 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 714.9573 304.5287 646.8587 1116.1420 0.6406 -0.2030 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6897 7.3767 525.5596 509.9667 1.2775 25.2102 31.5000 6.2898

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 623.9691 136.1146 608.9419 1126.4917 0.5539 0.0408 2.3726

 

NASA/TM—2013-218094 H–51
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6428 7.8487 535.3418 509.5646 451.3937 0.0342 0.2571

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 640.6728 0.0000 640.6728 1124.6827 0.5696 0.1490 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7213 533.6492 509.5974 0.0000 0.0600 0.0583 -0.0249

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8481 9.5960 1.1860 566.6084 30.4516 264.8798 2.0533

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189619.953 0.419 809.291 738172.375 0.368941E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.70166E-02

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.572 EfDer = 0.995 SH = 0.459095E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.525 3889.388 9.596 566.608 1.000 1.000 0.980

 W Kg/sec = 34.329 Wdry = 75.490 WH2O = 0.035 lbm/sec H2O = 0.305g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.921 3721.328 1.380 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109526.742 59249.656 1.450 513.330 354.077 395.845 1.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 512.07 -0.18 512.07 0.45 0.73 625.44

 MEAN 16.97 0.00 -0.02 512.07 -0.18 512.07 0.45 0.68

 HUB 14.32 0.00 -0.02 512.07 -0.18 512.07 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.93 46.36 5.57 653.71 830.53 8.36 545.56 509.49 1.01

 MEAN 48.37 43.80 4.57 576.01 770.85 8.36 545.56 509.49 1.01

 HUB 43.52 37.84 5.68 486.04 706.13 8.36 545.56 509.49 1.01

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 580.69 275.91 510.95 1160.21 0.50 2.16 1.89 8.34

 MEAN 16.57 594.93 291.74 518.49 1156.74 0.51 2.24 1.97 6.35

 HUB 13.89 645.51 373.24 526.66 1153.53 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.81 627.88 364.90 0.54 5212.59 0.92 0.91

 MEAN 562.54 584.95 270.80 0.51 4838.18 0.92 0.91 0.91 1.42

 HUB 471.44 535.74 98.20 0.46 5186.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.28 1.18 9.53 595.00 1.05 567.94 520.79 0.62

 MEAN 11.16 1.16 9.33 592.97 1.05 564.56 520.07 0.67

 HUB 11.27 1.17 9.14 594.86 1.05 561.42 520.92 0.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.37 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.36 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.33 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 647.9975 293.3762 577.7813 1152.6129 0.5622 -0.1357 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2183 9.0768 560.5861 520.6871 0.7386 26.9198 32.4000 5.4802

 

NASA/TM—2013-218094 H–52
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 572.7350 128.4477 558.1456 1160.1666 0.4937 0.0807 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1838 9.4880 567.9557 520.4297 432.2457 0.0281 0.2865

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 568.1506 0.0000 568.1506 1160.5651 0.4895 0.1900 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4836 568.3731 520.3835 0.0000 0.0600 0.0467 0.0784

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8639 11.1484 1.1618 594.2686 27.6706 265.2646 2.0563

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 172458.281 0.420 736.046 723347.750 0.514815E-03

 

Melt Ratio at Stator LE, Throat, TE

0.12546E+00 0.15061E+00 0.21800E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.157 EfDer = 0.997 SH = 0.580843E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.525 3889.388 11.148 594.265 1.000 1.000 0.980

 W Kg/sec = 34.329 Wdry = 75.481 WH2O = 0.044 lbm/sec H2O = 0.438g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.592 3633.691 1.380 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96417.633 59246.820 1.633 509.668 312.166 384.739 1.232

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 454.02 -0.16 454.02 0.39 0.66 580.91

 MEAN 15.91 0.00 -0.02 454.02 -0.16 454.02 0.39 0.60

 HUB 13.07 0.00 -0.02 454.02 -0.16 454.02 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.87 47.36 6.51 621.80 770.05 10.06 577.74 520.29 0.59

 MEAN 49.96 44.80 5.16 540.11 705.71 10.06 577.74 520.29 0.59

 HUB 44.35 38.84 5.51 443.61 634.88 10.06 577.74 520.29 0.59

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 536.37 280.99 456.88 1191.02 0.45 2.05 1.78 7.43

 MEAN 15.50 543.91 282.64 464.70 1186.78 0.46 2.13 1.86 5.75

 HUB 12.59 582.32 339.69 472.97 1182.75 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.91 562.37 327.91 0.47 5043.87 0.92 0.91

 MEAN 526.01 524.57 243.37 0.44 4382.76 0.92 0.91 0.91 1.47

 HUB 427.32 481.02 87.63 0.41 4278.71 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.95 1.16 11.29 621.72 1.05 598.65 530.38 0.39

 MEAN 12.70 1.14 11.02 618.12 1.04 594.39 529.14 0.42

 HUB 12.67 1.14 10.76 617.55 1.04 590.36 529.01 0.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.59 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.31 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.69 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 610.7081 287.8249 538.6291 1181.5527 0.5169 -0.2161 2.0437

 

NASA/TM—2013-218094 H–53
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7390 10.6427 589.2258 529.5770 0.4728 28.1185 33.0000 4.8815

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 545.8027 124.6345 531.3820 1187.5718 0.4596 -0.0141 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6874 10.9976 595.2393 529.3515 410.5396 0.0495 0.3067

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 527.5016 0.0000 527.5016 1189.1055 0.4436 0.2236 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1115 596.8058 529.3508 0.0000 0.0600 0.0447 0.0509

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8712 12.6958 1.1388 619.1097 24.8628 269.5066 2.0892

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 155091.875 0.418 661.926 728826.063 0.622990E-03

 

Melt Ratio at Stator LE, Throat, TE

0.44757E+00 0.48127E+00 0.57739E+00

 trTOT = 1.3398 Tt4 = 619.1097 T1 = 462.0901

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 977926.75 4173.7559 202.7916 2.4570 0.8275 2.9703 1.3398 37.3740

NASA/TM—2013-218094 H–54
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.336 EfDer = 0.998 SH = 0.113169E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.638 3627.044 5.167 462.089 1.000 1.000 0.980

 W Kg/sec = 30.290 Wdry = 66.631 WH2O = 0.008 lbm/sec H2O = 0.051g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 178.931 3842.775 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143417.094 52285.305 1.588 831.557 523.775 619.754 1.183

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 413.92 -0.14 413.92 0.40 0.75 691.80

 MEAN 17.06 0.00 -0.02 413.92 -0.14 413.92 0.40 0.66

 HUB 12.51 0.00 -0.02 413.92 -0.14 413.92 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.64 50.47 7.17 652.98 773.24 4.63 448.31 452.94 6.64

 MEAN 52.54 47.20 5.34 539.99 680.49 4.63 448.31 452.94 6.64

 HUB 43.74 38.62 5.12 395.97 572.92 4.63 448.31 452.94 6.64

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 645.60 361.64 534.81 1051.80 0.61 7.29 6.52 16.04

 MEAN 18.04 680.94 402.67 549.12 1046.40 0.65 7.43 6.80 12.53

 HUB 15.00 786.17 532.25 578.59 1036.44 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.98 609.01 291.33 0.58 7463.66 0.92 0.91

 MEAN 570.88 574.31 168.21 0.55 7264.94 0.92 0.91 0.91 1.31

 HUB 474.78 581.44 57.47 0.56 7985.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.30 5.22 500.08 1.08 466.57 478.00 4.13

 MEAN 6.67 1.29 5.04 499.07 1.08 461.78 477.62 4.96

 HUB 6.84 1.32 4.69 502.74 1.09 453.04 480.46 7.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.07 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.25 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.61 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 721.6682 401.8846 599.4111 1042.9557 0.6919 -0.0773 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7238 4.8999 458.7552 478.7779 5.7671 33.8405 35.4000 1.5595

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 568.4388 139.0575 551.1675 1060.8596 0.5358 0.3041 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6926 5.5176 474.6507 478.0067 554.9116 0.0278 0.4170

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 564.4474 0.0000 564.4474 1061.2411 0.5319 0.3361 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5128 475.0165 478.0653 0.0000 0.0600 0.0416 0.3014

NASA/TM—2013-218094 H–55
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8742 6.6682 1.2905 500.6279 38.5410 221.1329 1.7142

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 239701.516 0.562 902.664 739206.250 0.180011E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.317 EfDer = 1.000 SH = 0.271468E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.638 3627.044 6.668 500.627 1.000 1.000 0.980

 W Kg/sec = 30.290 Wdry = 66.620 WH2O = 0.018 lbm/sec H2O = 0.140g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.321 3691.930 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124084.586 52282.055 1.398 590.487 422.512 468.502 1.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 504.33 -0.17 504.33 0.47 0.77 662.06

 MEAN 18.08 0.00 -0.02 504.33 -0.17 504.33 0.47 0.71

 HUB 15.21 0.00 -0.02 504.33 -0.17 504.33 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.22 46.36 5.86 650.45 823.20 5.73 480.19 478.33 4.55

 MEAN 48.62 42.30 6.32 572.21 762.87 5.73 480.19 478.33 4.55

 HUB 43.68 37.84 5.84 481.43 697.34 5.73 480.19 478.33 4.55

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 578.58 291.76 499.64 1093.17 0.53 2.33 2.04 9.02

 MEAN 18.01 593.79 306.28 508.71 1089.17 0.55 2.40 2.13 7.35

 HUB 15.22 646.70 386.59 518.43 1085.46 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 646.33 612.67 354.58 0.56 5961.23 0.92 0.91

 MEAN 570.05 573.02 263.77 0.53 5519.20 0.92 0.91 0.91 1.44

 HUB 481.84 527.11 95.25 0.49 5887.67 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.11 1.22 6.72 530.95 1.06 504.05 494.26 2.17

 MEAN 7.99 1.20 6.55 528.70 1.06 500.37 493.25 2.44

 HUB 8.09 1.21 6.38 530.58 1.06 496.97 494.38 2.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.28 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 31.05 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.71 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 662.7843 307.1380 587.3239 1083.0392 0.6120 -0.1833 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0482 6.2693 494.7835 494.2203 2.9519 27.6071 30.6000 2.9929

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 554.1271 117.4789 541.5308 1094.6072 0.5062 0.1340 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0239 6.7508 505.4062 493.7289 491.5697 0.0260 0.2916

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 579.6560 0.0000 579.6560 1092.0671 0.5308 0.1976 0.5911

NASA/TM—2013-218094 H–56
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6208 503.0830 493.8462 0.0000 0.0600 0.0404 0.0483

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8769 8.0021 1.2000 530.0750 29.4492 251.5323 1.9499

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183298.406 0.439 690.262 664102.813 0.315863E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.514 EfDer = 1.000 SH = 0.386610E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.638 3627.044 8.002 530.075 1.000 1.000 0.980

 W Kg/sec = 30.290 Wdry = 66.612 WH2O = 0.026 lbm/sec H2O = 0.231g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.751 3587.916 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107436.227 52279.695 1.505 545.479 362.331 424.468 1.171

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 472.69 -0.16 472.69 0.43 0.72 628.38

 MEAN 17.74 0.00 -0.02 472.69 -0.16 472.69 0.43 0.67

 HUB 15.05 0.00 -0.02 472.69 -0.16 472.69 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.35 46.36 6.99 635.25 791.96 7.06 512.13 493.75 2.25

 MEAN 49.91 43.40 6.51 561.46 734.07 7.06 512.13 493.75 2.25

 HUB 45.23 38.84 6.39 476.36 671.20 7.06 512.13 493.75 2.25

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 554.82 290.99 472.39 1125.80 0.49 2.26 1.98 8.75

 MEAN 17.51 568.30 304.43 479.88 1122.19 0.51 2.34 2.07 6.78

 HUB 14.85 618.14 379.48 487.94 1118.81 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 627.02 579.71 336.03 0.51 5767.82 0.92 0.91

 MEAN 554.12 540.95 249.68 0.48 5332.43 0.92 0.91 0.91 1.47

 HUB 470.03 496.28 90.55 0.44 5637.70 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.57 1.20 8.12 559.40 1.06 534.68 507.24 1.27

 MEAN 9.45 1.18 7.95 557.18 1.05 531.25 506.34 1.39

 HUB 9.53 1.19 7.77 558.73 1.05 528.05 507.18 1.52

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.63 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.39 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.87 10.51 6.50 4.01 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 628.8948 306.4286 549.1904 1117.3187 0.5629 -0.1673 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.5007 7.6830 526.6835 507.0936 1.6042 29.1600 31.5000 2.3400

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 529.8723 115.5881 517.1112 1127.0500 0.4701 0.1389 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4800 8.1639 535.8956 506.7414 451.3937 0.0232 0.3154

 

NASA/TM—2013-218094 H–57
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 540.7592 0.0000 540.7592 1126.0417 0.4802 0.2249 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0918 534.9619 506.7916 0.0000 0.0600 0.0385 0.0930

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8801 9.4560 1.1817 558.4355 28.3628 240.6169 1.8652

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176659.891 0.449 665.263 635483.250 0.457410E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.46434E-03 0.18240E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.839 EfDer = 1.000 SH = 0.552736E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.638 3627.044 9.456 558.435 1.000 1.000 0.980

 W Kg/sec = 30.290 Wdry = 66.601 WH2O = 0.037 lbm/sec H2O = 0.376g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.489 3495.622 1.380 0.249 53.366 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94268.719 52276.281 1.631 513.330 314.764 395.845 1.258

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 440.74 -0.15 440.74 0.39 0.66 587.51

 MEAN 16.97 0.00 -0.02 440.74 -0.15 440.74 0.39 0.61

 HUB 14.32 0.00 -0.02 440.74 -0.15 440.74 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.14 46.36 7.78 609.62 752.37 8.53 542.85 506.77 1.35

 MEAN 50.64 43.80 6.84 537.16 694.94 8.53 542.85 506.77 1.35

 HUB 45.81 37.84 7.97 453.26 632.32 8.53 542.85 506.77 1.35

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 525.23 282.53 442.77 1155.55 0.45 2.16 1.89 8.34

 MEAN 16.57 535.34 290.89 449.42 1151.99 0.46 2.24 1.97 6.35

 HUB 13.89 578.56 355.38 456.55 1148.61 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 597.59 543.42 315.06 0.47 5337.00 0.92 0.91

 MEAN 524.59 506.55 233.71 0.44 4823.72 0.92 0.91 0.91 1.49

 HUB 439.65 464.26 84.26 0.40 4938.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.07 1.17 9.63 585.54 1.05 563.41 518.00 0.85

 MEAN 10.91 1.15 9.43 582.93 1.04 559.94 517.02 0.93

 HUB 10.94 1.16 9.22 583.52 1.04 556.66 517.37 1.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.54 35.43 31.50 3.93 0.93 0.41 1.40

 MEAN 32.91 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.90 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 577.2064 292.5242 497.5910 1149.1910 0.5023 -0.1163 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9587 9.2450 557.2703 517.5410 0.9949 30.4505 32.4000 1.9496

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 492.6031 110.4765 480.0549 1156.6479 0.4259 0.1616 2.2705

 

NASA/TM—2013-218094 H–58
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9426 9.6753 564.5286 517.2951 432.2457 0.0204 0.3363

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 488.5454 0.0000 488.5454 1156.9438 0.4223 0.2488 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6714 564.8441 517.2673 0.0000 0.0600 0.0379 0.1591

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 10.9154 1.1543 583.9861 25.5622 243.5052 1.8876

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 159357.484 0.446 600.106 629206.250 0.613922E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14301E+00 0.17047E+00 0.24355E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.085 EfDer = 1.000 SH = 0.685380E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.638 3627.044 10.915 583.983 1.000 1.000 0.980

 W Kg/sec = 30.290 Wdry = 66.593 WH2O = 0.046 lbm/sec H2O = 0.524g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.223 3418.296 1.380 0.249 53.371 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 83937.172 52273.559 1.828 509.668 278.886 384.739 1.380

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 395.25 -0.14 395.25 0.34 0.60 546.47

 MEAN 15.91 0.00 -0.02 395.25 -0.14 395.25 0.34 0.55

 HUB 13.07 0.00 -0.02 395.25 -0.14 395.25 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.73 47.36 8.37 579.86 701.87 10.09 571.46 517.22 0.83

 MEAN 51.88 44.80 7.08 503.68 640.35 10.09 571.46 517.22 0.83

 HUB 46.32 38.84 7.48 413.69 572.26 10.09 571.46 517.22 0.83

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.38 281.35 400.42 1182.79 0.41 2.05 1.78 7.43

 MEAN 15.50 492.93 278.17 406.94 1178.76 0.42 2.13 1.86 5.75

 HUB 12.59 524.58 322.41 413.81 1174.87 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 567.84 492.35 286.48 0.42 5050.00 0.92 0.91

 MEAN 490.53 459.01 212.36 0.39 4313.17 0.92 0.91 0.91 1.53

 HUB 398.50 420.75 76.09 0.36 4060.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.59 1.15 11.21 609.61 1.04 590.41 527.03 0.56

 MEAN 12.34 1.13 10.96 605.87 1.04 586.39 525.68 0.61

 HUB 12.25 1.12 10.70 604.59 1.04 582.52 525.29 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.09 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.36 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.92 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 547.4834 283.2729 468.5024 1174.9573 0.4660 -0.1947 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3645 10.6765 582.6595 526.0632 0.6670 31.1586 33.0000 1.8414

 

NASA/TM—2013-218094 H–59
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 473.5848 108.1435 461.0722 1181.0347 0.4010 0.0729 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3390 11.0613 588.7034 525.8598 410.5396 0.0377 0.3489

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 458.9590 0.0000 458.9590 1182.0939 0.3883 0.2725 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1365 589.7870 525.8510 0.0000 0.0600 0.0378 0.1252

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8833 12.3389 1.1304 606.6674 22.7038 250.9926 1.9457

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 141653.594 0.439 533.437 640382.938 0.732011E-03

 

Melt Ratio at Stator LE, Throat, TE

0.47434E+00 0.50973E+00 0.60855E+00

 trTOT = 1.3129 Tt4 = 606.6674 T1 = 462.0892 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 900670.88 3391.7329 178.9307 2.3879 0.8665 5.3355 1.3129 37.3740

NASA/TM—2013-218094 H–60
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.678 EfDer = 0.999 SH = 0.115029E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.495 3597.669 5.167 462.089 1.000 1.000 0.980

 W Kg/sec = 29.771 Wdry = 65.488 WH2O = 0.008 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 175.862 3811.653 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140501.625 51388.609 1.615 831.557 514.794 619.754 1.204

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 405.51 -0.14 405.51 0.39 0.74 686.19

 MEAN 17.06 0.00 -0.02 405.51 -0.14 405.51 0.39 0.65

 HUB 12.51 0.00 -0.02 405.51 -0.14 405.51 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.96 50.47 7.49 647.69 764.28 4.65 448.87 452.94 6.59

 MEAN 52.88 47.20 5.68 535.61 671.91 4.65 448.87 452.94 6.59

 HUB 44.10 38.62 5.48 392.76 564.63 4.65 448.87 452.94 6.59

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 636.74 362.67 523.37 1052.60 0.60 7.29 6.52 16.04

 MEAN 18.04 670.89 401.72 537.32 1047.20 0.64 7.43 6.80 12.53

 HUB 15.00 772.82 527.08 565.19 1037.53 0.74 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.69 595.95 285.03 0.57 7484.68 0.92 0.91

 MEAN 566.25 561.94 164.53 0.54 7247.83 0.92 0.91 0.91 1.33

 HUB 470.93 567.98 56.14 0.55 7907.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 499.88 1.08 467.28 477.88 4.11

 MEAN 6.66 1.29 5.07 498.68 1.08 462.49 477.38 4.93

 HUB 6.81 1.32 4.73 502.02 1.09 453.99 479.98 6.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.72 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.78 17.02 12.70 4.32 0.92 0.30 2.22

 HUB 43.00 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 709.7903 400.9406 585.7038 1044.0114 0.6799 -0.0746 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7061 4.9386 459.6863 478.4877 5.6784 34.3934 35.4000 1.0066

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 556.1285 136.0460 539.2313 1061.6135 0.5239 0.3133 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6772 5.5509 475.3275 477.7508 554.9116 0.0269 0.4243

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 552.0004 0.0000 552.0004 1061.9996 0.5198 0.3450 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5484 475.6974 477.8154 0.0000 0.0600 0.0397 0.3118

NASA/TM—2013-218094 H–61
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8774 6.6555 1.2880 500.1912 38.1045 218.9610 1.6974

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 236990.578 0.565 877.151 724178.875 0.184307E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.673 EfDer = 1.000 SH = 0.279001E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.495 3597.669 6.655 500.191 1.000 1.000 0.980

 W Kg/sec = 29.771 Wdry = 65.477 WH2O = 0.018 lbm/sec H2O = 0.145g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.055 3663.628 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121544.781 51385.301 1.420 590.487 415.882 468.502 1.127

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 494.01 -0.17 494.01 0.46 0.76 656.99

 MEAN 18.08 0.00 -0.02 494.01 -0.17 494.01 0.46 0.71

 HUB 15.21 0.00 -0.02 494.01 -0.17 494.01 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.57 46.36 6.21 645.18 812.72 5.76 480.58 478.10 4.62

 MEAN 48.97 42.30 6.67 567.58 752.58 5.76 480.58 478.10 4.62

 HUB 44.04 37.84 6.20 477.53 687.20 5.76 480.58 478.10 4.62

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 571.18 293.58 489.95 1093.37 0.52 2.33 2.04 9.02

 MEAN 18.01 585.74 306.91 498.90 1089.33 0.54 2.40 2.13 7.35

 HUB 15.22 637.60 384.67 508.49 1085.58 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 641.10 600.68 347.52 0.55 5998.46 0.92 0.91

 MEAN 565.43 561.90 258.52 0.52 5530.57 0.92 0.91 0.91 1.45

 HUB 477.94 516.97 93.26 0.48 5858.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.09 1.22 6.73 530.46 1.06 504.24 494.05 2.22

 MEAN 7.97 1.20 6.56 528.09 1.06 500.53 492.98 2.50

 HUB 8.05 1.21 6.40 529.75 1.06 497.08 494.00 2.78

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.93 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.60 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.11 10.39 6.50 3.89 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 652.1634 307.7747 574.9712 1083.5621 0.6019 -0.1784 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0243 6.3003 495.2632 493.9193 2.9921 28.1596 30.6000 2.4404

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 542.6697 115.0498 530.3339 1095.0018 0.4956 0.1465 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0023 6.7800 505.7732 493.4375 491.5697 0.0249 0.2997

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 567.1297 0.0000 567.1297 1092.6196 0.5191 0.2074 0.5911

NASA/TM—2013-218094 H–62
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6578 503.5945 493.5521 0.0000 0.0600 0.0386 0.0636

 

 STAGE EXIT CONDITIONS, STAGE 2 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.9820 1.1993 529.4316 29.2425 248.2314 1.9243

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182016.844 0.443 673.682 650258.000 0.324650E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.831 EfDer = 1.000 SH = 0.397149E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.495 3597.669 7.982 529.431 1.000 1.000 0.980

 W Kg/sec = 29.771 Wdry = 65.469 WH2O = 0.026 lbm/sec H2O = 0.238g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.860 3561.020 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105373.844 51382.922 1.529 545.479 356.799 424.468 1.190

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 463.62 -0.16 463.62 0.42 0.71 623.67

 MEAN 17.74 0.00 -0.02 463.62 -0.16 463.62 0.42 0.66

 HUB 15.05 0.00 -0.02 463.62 -0.16 463.62 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.66 46.36 7.30 630.11 782.42 7.08 512.17 493.47 2.32

 MEAN 50.23 43.40 6.83 556.91 724.76 7.08 512.17 493.47 2.32

 HUB 45.55 38.84 6.71 472.50 662.08 7.08 512.17 493.47 2.32

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 548.15 292.20 463.78 1125.62 0.49 2.26 1.98 8.75

 MEAN 17.51 561.05 304.62 471.16 1121.99 0.50 2.34 2.07 6.78

 HUB 14.85 609.90 377.42 479.10 1118.57 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 621.95 569.05 329.75 0.51 5791.71 0.92 0.91

 MEAN 549.63 531.05 245.01 0.47 5335.68 0.92 0.91 0.91 1.48

 HUB 466.22 487.26 88.81 0.44 5607.07 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.54 1.20 8.13 558.63 1.06 534.51 506.96 1.31

 MEAN 9.41 1.18 7.95 556.33 1.05 531.06 506.02 1.44

 HUB 9.49 1.19 7.77 557.70 1.05 527.83 506.78 1.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.21 35.41 31.50 3.91 0.93 0.41 1.40

 MEAN 32.88 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.23 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 619.7361 306.6189 538.5701 1117.3585 0.5546 -0.1638 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4659 7.7008 526.7229 506.7543 1.6486 29.6537 31.5000 1.8463

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 519.6914 113.3672 507.1755 1127.0255 0.4611 0.1501 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4468 8.1808 535.8745 506.4039 451.3937 0.0224 0.3224

 

NASA/TM—2013-218094 H–63
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 530.2167 0.0000 530.2167 1126.0680 0.4709 0.2328 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1116 534.9891 506.4537 0.0000 0.0600 0.0378 0.1049

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8813 9.4234 1.1806 557.5556 28.1263 237.8495 1.8438

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 175192.625 0.453 648.424 623038.188 0.469230E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.81544E-03 0.19191E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.115 EfDer = 1.000 SH = 0.565709E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.495 3597.669 9.423 557.555 1.000 1.000 0.980

 W Kg/sec = 29.771 Wdry = 65.458 WH2O = 0.037 lbm/sec H2O = 0.385g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 105.927 3470.046 1.380 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 92590.664 51379.520 1.655 513.330 310.194 395.845 1.276

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 432.89 -0.15 432.89 0.38 0.66 583.21

 MEAN 16.97 0.00 -0.02 432.89 -0.15 432.89 0.38 0.61

 HUB 14.32 0.00 -0.02 432.89 -0.15 432.89 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.41 46.36 8.05 604.68 743.78 8.53 542.52 506.44 1.40

 MEAN 50.91 43.80 7.11 532.81 686.61 8.53 542.52 506.44 1.40

 HUB 46.09 37.84 8.25 449.58 624.22 8.53 542.52 506.44 1.40

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 519.26 283.15 435.27 1154.99 0.45 2.16 1.89 8.34

 MEAN 16.57 528.87 290.71 441.80 1151.43 0.46 2.24 1.97 6.35

 HUB 13.89 571.20 353.33 448.80 1148.04 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 592.75 534.15 309.60 0.46 5348.73 0.92 0.91 

 MEAN 520.35 497.92 229.64 0.43 4820.73 0.92 0.91 0.91 1.50

 HUB 436.08 456.37 82.76 0.40 4909.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.03 1.17 9.61 584.50 1.05 562.87 517.65 0.89

 MEAN 10.86 1.15 9.41 581.84 1.04 559.40 516.64 0.96

 HUB 10.89 1.16 9.21 582.29 1.04 556.11 516.94 1.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.04 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.35 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.21 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 569.6124 292.3452 488.8687 1148.7552 0.4959 -0.1143 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9085 9.2416 556.8486 517.1537 1.0305 30.8796 32.4000 1.5204

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 483.9526 108.5364 471.6248 1156.1926 0.4186 0.1708 2.2705

 

NASA/TM—2013-218094 H–64
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8936 9.6718 564.0857 516.9069 432.2457 0.0199 0.3424

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 479.9664 0.0000 479.9664 1156.4774 0.4150 0.2556 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6677 564.3898 516.8807 0.0000 0.0600 0.0374 0.1681

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8820 10.8672 1.1532 582.8649 25.3209 241.0762 1.8688

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 157858.781 0.449 584.268 617568.063 0.627853E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14435E+00 0.17204E+00 0.24568E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.319 EfDer = 0.999 SH = 0.700341E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.495 3597.669 10.867 582.861 1.000 1.000 0.980

 W Kg/sec = 29.771 Wdry = 65.450 WH2O = 0.046 lbm/sec H2O = 0.535g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 93.916 3393.872 1.380 0.249 53.371 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 82559.484 51376.801 1.853 509.668 275.058 384.739 1.399

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 388.77 -0.13 388.77 0.33 0.60 542.57

 MEAN 15.91 0.00 -0.02 388.77 -0.13 388.77 0.33 0.54

 HUB 13.07 0.00 -0.02 388.77 -0.13 388.77 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.95 47.36 8.59 575.17 694.34 10.07 570.74 516.83 0.86

 MEAN 52.12 44.80 7.32 499.60 633.14 10.07 570.75 516.83 0.86

 HUB 46.56 38.84 7.72 410.34 565.36 10.07 570.74 516.83 0.86

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 484.27 281.33 394.17 1181.86 0.41 2.05 1.78 7.43

 MEAN 15.50 487.34 277.61 400.54 1177.85 0.41 2.13 1.86 5.75

 HUB 12.59 518.24 320.48 407.26 1173.98 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 563.24 484.60 281.90 0.41 5049.59 0.92 0.91

 MEAN 486.56 451.76 208.94 0.38 4304.45 0.92 0.91 0.91 1.54

 HUB 395.27 414.07 74.79 0.35 4036.65 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.53 1.15 11.18 608.27 1.04 589.47 526.61 0.59

 MEAN 12.27 1.13 10.92 604.52 1.04 585.48 525.25 0.64

 HUB 12.18 1.12 10.67 603.18 1.03 581.65 524.83 0.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.52 35.57 31.50 4.07 0.93 0.45 1.40

 MEAN 34.73 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.20 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 540.6373 282.7025 460.8340 1174.1870 0.4604 -0.1923 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2967 10.6541 581.8953 525.6256 0.6944 31.5274 33.0000 1.4726

 

NASA/TM—2013-218094 H–65
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 465.7704 106.3591 453.4642 1180.2590 0.3946 0.0826 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2731 11.0396 587.9304 525.4221 410.5396 0.0368 0.3540

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 451.4936 0.0000 451.4936 1181.2753 0.3822 0.2783 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1112 588.9703 525.4130 0.0000 0.0600 0.0373 0.1337

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8838 12.2724 1.1293 605.3054 22.4631 248.8838 1.9293

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 140156.500 0.442 518.748 629187.813 0.747741E-03

 

Melt Ratio at Stator LE, Throat, TE

 0.47654E+00 0.51210E+00 0.61124E+00

 trTOT = 1.3099 Tt4 = 605.3054 T1 = 462.0891

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 892215.38 3302.2712 175.8621 2.3750 0.8686 5.6781 1.3099 37.3740

NASA/TM—2013-218094 H–66
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.017 EfDer = 0.999 SH = 0.116889E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.359 3567.880 5.167 462.089 1.000 1.000 0.980

 W Kg/sec = 29.254 Wdry = 64.352 WH2O = 0.008 lbm/sec H2O = 0.053g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.812 3780.092 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 137634.703 50497.172 1.644 831.557 505.865 619.754 1.225

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 397.23 -0.14 397.23 0.38 0.73 680.51

 MEAN 17.06 0.00 -0.02 397.23 -0.14 397.23 0.38 0.64

 HUB 12.51 0.00 -0.02 397.23 -0.14 397.23 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.27 50.47 7.80 642.33 755.35 4.67 449.40 452.94 6.55

 MEAN 53.22 47.20 6.02 531.18 663.39 4.67 449.40 452.94 6.55

 HUB 44.45 38.62 5.83 389.51 556.43 4.67 449.40 452.94 6.55

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 628.11 363.42 512.30 1053.33 0.60 7.29 6.52 16.04

 MEAN 18.04 661.08 400.60 525.87 1047.93 0.63 7.43 6.80 12.53

 HUB 15.00 759.86 521.90 552.27 1038.53 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 642.33 583.31 278.91 0.55 7500.07 0.92 0.91 

 MEAN 561.56 549.96 160.96 0.52 7227.56 0.92 0.91 0.91 1.34

 HUB 467.03 554.99 54.86 0.53 7830.20 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 499.64 1.08 467.92 477.73 4.09

 MEAN 6.64 1.28 5.09 498.28 1.08 463.14 477.13 4.91

 HUB 6.77 1.31 4.76 501.30 1.08 454.87 479.51 6.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.35 28.57 24.20 4.37 0.93 0.36 1.80

 MEAN 37.30 17.02 12.70 4.32 0.93 0.31 2.22

 HUB 43.38 -5.67 -9.30 3.63 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 698.2968 399.8217 572.5041 1044.9722 0.6682 -0.0721 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6872 4.9740 460.5344 478.1911 5.6075 34.9294 35.4000 0.4706

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 544.2917 133.1504 527.7542 1062.2745 0.5124 0.3221 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6603 5.5803 475.9213 477.4849 554.9116 0.0263 0.4313

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 540.0797 0.0000 540.0797 1062.6598 0.5082 0.3534 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5795 476.2905 477.5549 0.0000 0.0600 0.0381 0.3216

NASA/TM—2013-218094 H–67
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8799 6.6407 1.2852 499.7374 37.6508 216.8577 1.6811

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 234172.844 0.568 851.687 709402.063 0.188579E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.014 EfDer = 1.000 SH = 0.286363E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.359 3567.880 6.641 499.737 1.000 1.000 0.980

 W Kg/sec = 29.254 Wdry = 64.341 WH2O = 0.018 lbm/sec H2O = 0.149g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.838 3634.942 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 119095.414 50493.813 1.442 590.487 409.392 468.502 1.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 484.05 -0.17 484.05 0.45 0.75 651.84

 MEAN 18.08 0.00 -0.02 484.05 -0.17 484.05 0.45 0.70

 HUB 15.21 0.00 -0.02 484.05 -0.17 484.05 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.90 46.36 6.54 639.84 802.44 5.78 480.91 477.86 4.69

 MEAN 49.31 42.30 7.01 562.88 742.51 5.78 480.91 477.86 4.69

 HUB 44.38 37.84 6.54 473.57 677.30 5.78 480.91 477.86 4.69

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 564.00 295.02 480.68 1093.47 0.52 2.33 2.04 9.02

 MEAN 18.01 577.94 307.27 489.48 1089.42 0.53 2.40 2.13 7.35

 HUB 15.22 628.74 382.62 498.92 1085.63 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.79 589.22 340.77 0.54 6027.71 0.92 0.91

 MEAN 560.75 551.23 253.48 0.51 5536.89 0.92 0.91 0.91 1.46

 HUB 473.98 507.21 91.36 0.47 5827.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.07 1.22 6.75 529.90 1.06 504.34 493.81 2.27

 MEAN 7.94 1.20 6.57 527.44 1.06 500.60 492.68 2.56

 HUB 8.02 1.21 6.41 528.89 1.06 497.13 493.60 2.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.54 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.12 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.48 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 641.9910 308.1302 563.2124 1083.9640 0.5923 -0.1739 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9962 6.3251 495.6322 493.5928 3.0390 28.6828 30.6000 1.9172

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 531.8032 112.7461 519.7143 1095.2693 0.4855 0.1580 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9761 6.8020 506.0224 493.1194 491.5697 0.0240 0.3070

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 555.4017 0.0000 555.4017 1093.0175 0.5081 0.2156 0.5911

NASA/TM—2013-218094 H–68
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6854 503.9632 493.2303 0.0000 0.0600 0.0379 0.0768

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8806 7.9562 1.1981 528.7421 29.0067 245.1622 1.9005

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180553.922 0.447 656.675 636751.500 0.333246E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.123 EfDer = 1.000 SH = 0.407419E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.359 3567.880 7.956 528.742 1.000 1.000 0.980

 W Kg/sec = 29.254 Wdry = 64.333 WH2O = 0.026 lbm/sec H2O = 0.244g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.057 3533.836 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 103422.672 50491.410 1.552 545.479 351.521 424.468 1.208

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 455.04 -0.16 455.04 0.41 0.70 618.91

 MEAN 17.74 0.00 -0.02 455.04 -0.16 455.04 0.41 0.65

 HUB 15.05 0.00 -0.02 455.04 -0.16 455.04 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.95 46.36 7.59 624.89 773.14 7.09 512.11 493.17 2.38

 MEAN 50.52 43.40 7.12 552.30 715.73 7.09 512.11 493.17 2.38

 HUB 45.85 38.84 7.01 468.59 653.29 7.09 512.11 493.17 2.38

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 541.74 292.95 455.70 1125.31 0.48 2.26 1.98 8.75

 MEAN 17.51 554.09 304.46 462.95 1121.66 0.49 2.34 2.07 6.78

 HUB 14.85 602.01 375.23 470.76 1118.24 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 616.80 559.05 323.85 0.50 5806.40 0.92 0.91

 MEAN 545.08 521.75 240.62 0.47 5332.82 0.92 0.91 0.91 1.49

 HUB 462.36 478.76 87.14 0.43 5574.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.50 1.19 8.13 557.78 1.05 534.21 506.63 1.36

 MEAN 9.37 1.18 7.95 555.41 1.05 530.75 505.66 1.49

 HUB 9.44 1.19 7.77 556.62 1.05 527.51 506.34 1.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.73 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.33 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.56 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 611.0366 306.4573 528.6299 1117.2539 0.5469 -0.1606 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4223 7.7081 526.6255 506.3723 1.6977 30.1017 31.5000 1.3983

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 510.2144 111.2998 497.9267 1126.8408 0.4528 0.1600 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4047 8.1856 535.7009 506.0233 451.3937 0.0218 0.3287

 

NASA/TM—2013-218094 H–69
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 520.4200 0.0000 520.4200 1125.9282 0.4622 0.2397 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1190 534.8582 506.0730 0.0000 0.0600 0.0373 0.1153

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 9.3817 1.1792 556.5977 27.8579 235.3669 1.8245

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 173526.406 0.456 631.116 610910.250 0.480767E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.89448E-03 0.19461E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.361 EfDer = 0.999 SH = 0.578572E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.359 3567.880 9.382 556.597 1.000 1.000 0.980

 W Kg/sec = 29.254 Wdry = 64.322 WH2O = 0.037 lbm/sec H2O = 0.394g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.462 3444.274 1.380 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91020.258 50488.016 1.678 513.330 305.906 395.845 1.294 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 425.55 -0.15 425.55 0.38 0.65 578.88

 MEAN 16.97 0.00 -0.02 425.55 -0.15 425.55 0.38 0.60

 HUB 14.32 0.00 -0.02 425.55 -0.15 425.55 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.65 46.36 8.29 599.67 735.44 8.52 542.07 506.07 1.45

 MEAN 51.16 43.80 7.36 528.39 678.56 8.52 542.07 506.07 1.45

 HUB 46.34 37.84 8.50 445.86 616.45 8.52 542.07 506.07 1.45

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 513.53 283.31 428.31 1154.28 0.44 2.16 1.89 8.34

 MEAN 16.57 522.67 290.18 434.71 1150.73 0.45 2.24 1.97 6.35

 HUB 13.89 564.18 351.15 441.58 1147.34 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 587.84 525.54 304.53 0.46 5351.65 0.92 0.91

 MEAN 516.04 489.88 225.86 0.43 4811.93 0.92 0.91 0.91 1.51

 HUB 432.47 449.00 81.32 0.39 4879.61 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.97 1.17 9.59 583.33 1.05 562.17 517.24 0.92

 MEAN 10.80 1.15 9.39 580.64 1.04 558.72 516.21 1.00

 HUB 10.82 1.15 9.19 580.97 1.04 555.44 516.47 1.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.48 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.72 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 38.49 10.43 6.50 3.93 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 562.4016 291.8142 480.7702 1148.1636 0.4898 -0.1126 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8462 9.2249 556.2756 516.7133 1.0702 31.2566 32.4000 1.1434

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 475.9669 106.7455 463.8426 1155.5634 0.4119 0.1788 2.2705

 

NASA/TM—2013-218094 H–70
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8323 9.6531 563.4726 516.4650 432.2457 0.0194 0.3477

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 472.0503 0.0000 472.0503 1155.8378 0.4084 0.2614 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6488 563.7663 516.4405 0.0000 0.0600 0.0371 0.1758

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8825 10.8064 1.1519 581.6364 25.0502 238.9568 1.8524

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 156176.125 0.452 568.013 606220.313 0.641805E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14418E+00 0.17194E+00 0.24582E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.521 EfDer = 0.999 SH = 0.715508E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.359 3567.880 10.806 581.633 1.000 1.000 0.980

 W Kg/sec = 29.254 Wdry = 64.313 WH2O = 0.046 lbm/sec H2O = 0.546g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.708 3369.323 1.380 0.249 53.372 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 81282.375 50485.305 1.877 509.668 271.523 384.739 1.417

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 382.75 -0.13 382.75 0.33 0.59 538.64

 MEAN 15.91 0.00 -0.02 382.75 -0.13 382.75 0.33 0.54

 HUB 13.07 0.00 -0.02 382.75 -0.13 382.75 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.14 47.36 8.78 570.40 687.03 10.03 569.89 516.40 0.90

 MEAN 52.32 44.80 7.52 495.46 626.19 10.03 569.89 516.40 0.90

 HUB 46.76 38.84 7.92 406.94 558.76 10.03 569.89 516.40 0.90

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 479.33 280.87 388.42 1180.75 0.41 2.05 1.78 7.43

 MEAN 15.50 482.00 276.74 394.64 1176.78 0.41 2.13 1.86 5.75

 HUB 12.59 512.17 318.36 401.20 1172.94 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 558.57 477.48 277.70 0.40 5041.26 0.92 0.91

 MEAN 482.53 445.07 205.78 0.38 4290.96 0.92 0.91 0.91 1.55

 HUB 392.00 407.90 73.63 0.35 4009.94 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.44 1.15 11.12 606.79 1.04 588.37 526.12 0.62

 MEAN 12.19 1.13 10.87 603.05 1.04 584.42 524.76 0.67

 HUB 12.09 1.12 10.63 601.65 1.03 580.62 524.31 0.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.87 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 35.04 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.43 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 534.1733 281.8182 453.7837 1173.2408 0.4553 -0.1904 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2133 10.6149 580.9568 525.1260 0.7253 31.8420 33.0000 1.1580

 

NASA/TM—2013-218094 H–71
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 458.6299 104.7285 446.5124 1179.2893 0.3889 0.0906 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1912 10.9990 586.9639 524.9219 410.5396 0.0362 0.3584

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 444.6648 0.0000 444.6648 1180.2678 0.3767 0.2830 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0673 587.9651 524.9126 0.0000 0.0600 0.0371 0.1407

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8842 12.1900 1.1280 603.8093 22.1956 247.1115 1.9156

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 138491.406 0.444 503.694 618255.813 0.763787E-03

 

Melt Ratio at Stator LE, Throat, TE

0.47615E+00 0.51177E+00 0.61099E+00

 trTOT = 1.3067 Tt4 = 603.8093 T1 = 462.0890

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 882920.63 3211.1848 172.8116 2.3591 0.8701 6.0166 1.3067 37.3740

NASA/TM—2013-218094 H–72
 10μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.998 EfDer = 0.986 SH = 0.232229E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.869 3973.766 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 33.577 Wdry = 73.852 WH2O = 0.017 lbm/sec H2O = 0.097g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.634 4121.098 1.381 0.248 53.356 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 170845.094 57955.750 1.402 831.557 593.203 619.754 1.045

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 493.08 -0.17 493.08 0.47 0.83 741.90

 MEAN 17.06 0.00 -0.02 493.08 -0.17 493.08 0.47 0.74

 HUB 12.51 0.00 -0.02 493.08 -0.17 493.08 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.43 50.47 4.96 715.40 869.01 4.45 462.73 465.97 6.56

 MEAN 50.20 47.20 3.00 591.61 770.28 4.45 462.73 465.97 6.56

 HUB 41.35 38.62 2.73 433.82 656.87 4.45 462.73 465.97 6.56

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 740.78 363.27 645.60 1066.78 0.69 7.29 6.52 16.04

 MEAN 18.04 786.44 421.80 663.75 1061.23 0.74 7.43 6.80 12.53

 HUB 15.00 927.91 591.85 714.66 1047.27 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.40 735.39 352.13 0.69 7497.73 0.92 0.90

 MEAN 625.45 694.29 203.65 0.65 7610.52 0.92 0.90 0.90 1.21

 HUB 520.16 718.25 71.69 0.69 8879.87 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.31 4.94 524.07 1.09 479.96 489.88 4.18

 MEAN 6.81 1.32 4.75 524.70 1.09 474.98 490.64 4.99

 HUB 7.12 1.38 4.30 531.78 1.10 462.56 496.18 7.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.37 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.44 17.06 12.70 4.36 0.91 0.23 2.22

 HUB 39.63 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 849.0142 420.9822 737.2918 1054.4296 0.8052 -0.1053 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8848 4.5140 468.9125 492.5395 6.3943 29.7257 35.4000 5.6743

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 690.2915 168.8664 669.3179 1076.2708 0.6414 0.2332 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8154 5.1846 488.5531 490.6584 554.9116 0.0409 0.3627

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 691.6230 0.0000 691.6230 1076.0790 0.6427 0.2592 1.3089

NASA/TM—2013-218094 H–73
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1284 488.4113 490.6686 0.0000 0.0600 0.0705 0.2081

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8271 6.7488 1.3061 526.8475 44.5792 237.0189 1.8374

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 277352.156 0.542 1157.775 816810.500 0.330432E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.665 EfDer = 0.990 SH = 0.455418E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.869 3973.766 6.749 526.847 1.000 1.000 0.980

 W Kg/sec = 33.577 Wdry = 73.835 WH2O = 0.034 lbm/sec H2O = 0.217g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.156 3942.919 1.381 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149186.266 57950.676 1.244 590.487 474.780 468.502 0.987

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 606.35 -0.21 606.35 0.56 0.86 707.07

 MEAN 18.08 0.00 -0.02 606.35 -0.21 606.35 0.56 0.80

 HUB 15.21 0.00 -0.02 606.35 -0.21 606.35 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.61 46.36 3.25 712.63 935.84 5.48 497.32 490.73 3.62

 MEAN 45.96 42.30 3.66 626.91 872.32 5.48 497.32 490.73 3.62

 HUB 41.03 37.84 3.19 527.45 803.79 5.48 497.32 490.73 3.62

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 659.46 283.70 595.31 1114.78 0.59 2.33 2.04 9.02

 MEAN 18.01 679.53 308.93 605.24 1111.12 0.61 2.40 2.13 7.35

 HUB 15.22 741.86 413.16 616.17 1107.83 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.12 731.11 424.41 0.66 5797.50 0.92 0.91

 MEAN 624.54 682.59 315.62 0.61 5567.51 0.92 0.91 0.91 1.38

 HUB 527.90 626.76 114.74 0.57 6292.66 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.21 1.22 6.50 559.14 1.06 524.21 504.93 1.66

 MEAN 8.15 1.21 6.35 557.86 1.06 520.77 504.53 1.84

 HUB 8.34 1.24 6.20 561.90 1.07 517.70 506.54 2.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.48 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 27.04 27.54 23.50 4.04 0.92 0.33 1.63

 HUB 33.84 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 777.7106 309.7927 713.3458 1100.6708 0.7066 -0.2326 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2156 5.9109 511.0679 505.9639 2.4655 23.4744 30.6000 7.1256

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 670.7184 142.1971 655.4717 1114.0001 0.6021 0.0294 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1582 6.4046 523.5085 505.0672 491.5697 0.0405 0.2261

 

NASA/TM—2013-218094 H–74
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 712.9634 0.0000 712.9634 1108.9729 0.6429 0.1056 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1543 518.8205 505.2965 0.0000 0.0600 0.0715 -0.1033

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8290 8.0996 1.2001 559.6291 32.7834 278.6781 2.1603

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 204182.406 0.407 852.336 739166.375 0.517065E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.055 EfDer = 0.993 SH = 0.611997E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.869 3973.766 8.100 559.629 1.000 1.000 0.980

 W Kg/sec = 33.577 Wdry = 73.823 WH2O = 0.045 lbm/sec H2O = 0.339g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.254 3825.694 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 128354.023 57947.109 1.338 545.479 407.785 424.468 1.041

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 564.73 -0.19 564.73 0.50 0.80 670.03

 MEAN 17.74 0.00 -0.02 564.73 -0.19 564.73 0.50 0.74

 HUB 15.05 0.00 -0.02 564.73 -0.19 564.73 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.95 46.36 4.59 695.98 896.42 6.83 534.04 504.80 1.60

 MEAN 47.46 43.40 4.06 615.13 835.19 6.83 534.04 504.80 1.60

 HUB 42.75 38.84 3.91 521.90 769.09 6.83 534.04 504.80 1.60

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 629.25 286.98 560.01 1151.60 0.55 2.26 1.98 8.75

 MEAN 17.51 647.33 309.87 568.35 1148.19 0.56 2.34 2.07 6.78

 HUB 14.85 706.23 406.48 577.53 1145.09 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.96 688.18 399.99 0.60 5688.89 0.92 0.91 

 MEAN 607.09 641.37 297.22 0.56 5428.20 0.92 0.91 0.91 1.40

 HUB 514.96 587.63 108.48 0.51 6039.16 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.71 1.20 7.95 591.29 1.06 559.51 517.22 0.88

 MEAN 9.64 1.19 7.79 589.84 1.05 556.21 516.76 0.95

 HUB 9.82 1.21 7.62 593.24 1.06 553.21 518.27 1.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.13 35.54 31.50 4.04 0.93 0.35 1.40

 MEAN 28.60 27.61 23.50 4.11 0.92 0.35 1.62

 HUB 35.14 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 729.1244 311.9030 659.0439 1140.4646 0.6393 -0.2019 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7047 7.3962 548.8092 517.7455 1.1508 25.3266 31.5000 6.1734

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 635.5494 138.6408 620.2433 1151.0688 0.5521 0.0440 2.3726

 

NASA/TM—2013-218094 H–75
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6586 7.8720 559.0500 517.2009 451.3937 0.0338 0.2591

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 652.3992 0.0000 652.3992 1149.2428 0.5677 0.1518 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7466 557.3113 517.2255 0.0000 0.0600 0.0575 -0.0207

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8496 9.6127 1.1868 591.4478 31.8254 264.1176 2.0474

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 198402.547 0.420 828.209 699173.875 0.687395E-03

 

Melt Ratio at Stator LE, Throat, TE

0.47522E-01 0.63716E-01 0.11294E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.652 EfDer = 0.996 SH = 0.774524E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.869 3973.766 9.613 591.446 1.000 1.000 0.980

 W Kg/sec = 33.577 Wdry = 73.811 WH2O = 0.057 lbm/sec H2O = 0.494g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.624 3721.364 1.380 0.249 53.373 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111586.211 57943.406 1.453 513.330 353.288 395.845 1.120

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 521.70 -0.18 521.70 0.45 0.73 625.45

 MEAN 16.97 0.00 -0.02 521.70 -0.18 521.70 0.45 0.68

 HUB 14.32 0.00 -0.02 521.70 -0.18 521.70 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.01 46.36 5.65 667.89 847.64 8.39 569.63 516.95 0.82

 MEAN 48.45 43.80 4.65 588.50 786.59 8.39 569.63 516.95 0.82

 HUB 43.60 37.84 5.76 496.58 720.38 8.39 569.63 516.95 0.82

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 592.40 283.11 520.37 1185.46 0.50 2.16 1.89 8.34

 MEAN 16.57 606.85 298.94 528.11 1181.89 0.51 2.24 1.97 6.35

 HUB 13.89 658.39 381.64 536.50 1178.57 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.71 639.43 371.60 0.54 5348.57 0.92 0.91

 MEAN 574.74 595.79 275.80 0.50 4957.72 0.92 0.91 0.91 1.43

 HUB 481.67 545.75 100.04 0.46 5303.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.31 1.18 9.56 621.18 1.05 593.05 527.60 0.51

 MEAN 11.18 1.16 9.36 619.01 1.05 589.48 526.91 0.55

 HUB 11.30 1.18 9.16 620.93 1.05 586.18 527.73 0.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.55 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.51 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.43 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 660.7454 300.6257 588.3950 1177.7018 0.5610 -0.1349 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2428 9.1050 585.3826 527.5208 0.5972 27.0636 32.4000 5.3364

 

NASA/TM—2013-218094 H–76
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 583.0784 130.7674 568.2256 1185.4624 0.4919 0.0842 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.2090 9.5211 593.1203 527.2117 432.2457 0.0278 0.2887

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 578.3818 0.0000 578.3818 1185.8589 0.4877 0.1928 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5171 593.5525 527.1498 0.0000 0.0600 0.0462 0.0821

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8651 11.1740 1.1624 620.3545 28.9247 264.3607 2.0493

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180502.063 0.421 753.485 685141.750 0.827912E-03

 

Melt Ratio at Stator LE, Throat, TE

0.30886E+00 0.34380E+00 0.43447E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.249 EfDer = 0.998 SH = 0.890226E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.869 3973.766 11.174 620.350 1.000 1.000 0.980

 W Kg/sec = 33.577 Wdry = 73.803 WH2O = 0.066 lbm/sec H2O = 0.645g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.275 3633.628 1.379 0.249 53.377 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 98189.766 57940.777 1.637 509.668 311.313 384.739 1.236

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 462.37 -0.16 462.37 0.39 0.66 580.90

 MEAN 15.91 0.00 -0.02 462.37 -0.16 462.37 0.39 0.60

 HUB 13.07 0.00 -0.02 462.37 -0.16 462.37 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.96 47.36 6.60 635.29 785.87 10.09 603.23 526.98 0.46

 MEAN 50.05 44.80 5.25 551.83 720.05 10.09 603.23 526.98 0.46

 HUB 44.44 38.84 5.60 453.24 647.57 10.09 603.23 526.98 0.46

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 547.24 288.31 465.13 1216.91 0.45 2.05 1.78 7.43

 MEAN 15.50 554.76 289.64 473.15 1212.55 0.46 2.13 1.86 5.75

 HUB 12.59 593.84 347.39 481.62 1208.41 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.12 572.52 333.81 0.47 5175.21 0.92 0.91

 MEAN 537.42 534.11 247.78 0.44 4491.23 0.92 0.91 0.91 1.48

 HUB 436.59 489.81 89.20 0.41 4375.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.99 1.16 11.33 649.09 1.05 625.10 536.61 0.31

 MEAN 12.74 1.14 11.06 645.29 1.04 620.64 535.41 0.33

 HUB 12.70 1.14 10.79 644.65 1.04 616.41 535.30 0.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.79 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.47 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.80 10.49 6.50 3.99 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 622.5938 294.9493 548.2955 1207.2584 0.5157 -0.2150 2.0437

 

NASA/TM—2013-218094 H–77
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7732 10.6804 615.3036 535.8494 0.3680 28.2775 33.0000 4.7225

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 555.3951 126.8249 540.7209 1213.4598 0.4577 -0.0093 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.7228 11.0415 621.6352 535.5975 410.5396 0.0488 0.3091

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 536.8154 0.0000 536.8154 1214.9980 0.4418 0.2266 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1546 623.2483 535.5881 0.0000 0.0600 0.0442 0.0553

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8723 12.7309 1.1393 646.3146 25.9902 268.5062 2.0814

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 162346.813 0.419 677.698 690319.188 0.929721E-03

 

Melt Ratio at Stator LE, Throat, TE

0.70757E+00 0.74651E+00 0.85654E+00

 trTOT = 1.3401 Tt4 = 646.3146 T1 = 482.2704

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1022786.00 4269.5044 202.6338 2.4638 0.8287 2.9979 1.3401 37.3740

NASA/TM—2013-218094 H–78
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.364 EfDer = 0.998 SH = 0.259859E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.173 3705.867 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 29.624 Wdry = 65.156 WH2O = 0.017 lbm/sec H2O = 0.111g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 178.780 3843.266 1.381 0.249 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146384.203 51132.582 1.589 831.557 523.383 619.754 1.184

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 422.49 -0.15 422.49 0.40 0.75 691.89

 MEAN 17.06 0.00 -0.02 422.49 -0.15 422.49 0.40 0.66

 HUB 12.51 0.00 -0.02 422.49 -0.15 422.49 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.66 50.47 7.19 667.17 789.81 4.63 467.92 465.86 6.02

 MEAN 52.56 47.20 5.36 551.72 695.02 4.63 467.92 465.86 6.02

 HUB 43.77 38.62 5.15 404.57 585.06 4.63 467.92 465.86 6.02

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 659.25 369.89 545.71 1074.58 0.61 7.29 6.52 16.04

 MEAN 18.04 695.29 411.64 560.35 1069.05 0.65 7.43 6.80 12.53

 HUB 15.00 802.64 543.74 590.41 1058.89 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.17 621.43 297.28 0.58 7633.83 0.92 0.91

 MEAN 583.28 586.04 171.64 0.55 7426.81 0.92 0.91 0.91 1.32

 HUB 485.10 593.31 58.64 0.56 8157.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.30 5.23 521.95 1.08 487.02 488.58 3.79

 MEAN 6.67 1.29 5.04 520.88 1.08 482.02 488.35 4.50

 HUB 6.84 1.32 4.69 524.68 1.09 472.90 491.32 6.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.13 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.30 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.64 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 736.8060 410.8391 611.6326 1065.5482 0.6915 -0.0771 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7250 4.9030 478.8795 489.5419 5.1661 33.8896 35.4000 1.5104

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 579.9757 141.8798 562.3539 1083.8419 0.5351 0.3051 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6939 5.5216 495.4758 488.3897 554.9116 0.0277 0.4177

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 575.8903 0.0000 575.8903 1084.2290 0.5312 0.3370 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5170 495.8586 488.4764 0.0000 0.0600 0.0415 0.3024

NASA/TM—2013-218094 H–79
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8743 6.6697 1.2908 522.5020 40.2346 220.9220 1.7126

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 250381.000 0.563 922.147 699863.000 0.389405E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.353 EfDer = 1.000 SH = 0.553209E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.173 3705.867 6.670 522.502 1.000 1.000 0.980

 W Kg/sec = 29.624 Wdry = 65.137 WH2O = 0.036 lbm/sec H2O = 0.274g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.167 3692.359 1.381 0.249 53.366 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126621.617 51126.691 1.399 590.487 422.135 468.502 1.110 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 514.64 -0.18 514.64 0.47 0.77 662.14

 MEAN 18.08 0.00 -0.02 514.64 -0.18 514.64 0.47 0.71

 HUB 15.21 0.00 -0.02 514.64 -0.18 514.64 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.25 46.36 5.89 664.58 840.69 5.74 501.24 488.81 3.95

 MEAN 48.65 42.30 6.35 584.65 779.02 5.74 501.24 488.81 3.95

 HUB 43.72 37.84 5.88 491.89 712.03 5.74 501.24 488.81 3.95

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 590.78 298.61 509.76 1116.82 0.53 2.33 2.04 9.02

 MEAN 18.01 606.28 313.31 519.05 1112.72 0.54 2.40 2.13 7.35

 HUB 15.22 660.28 395.13 529.00 1108.93 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.38 625.08 361.76 0.56 6101.34 0.92 0.91

 MEAN 582.44 584.67 269.13 0.53 5645.94 0.92 0.91 0.91 1.44

 HUB 492.31 537.85 97.18 0.49 6017.73 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.11 1.22 6.72 554.18 1.06 526.16 503.25 1.96

 MEAN 8.00 1.20 6.55 551.82 1.06 522.31 502.35 2.19

 HUB 8.09 1.21 6.38 553.75 1.06 518.75 503.48 2.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.36 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 31.12 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.76 10.41 6.50 3.91 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 676.5714 314.1917 599.1931 1106.4912 0.6115 -0.1828 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0517 6.2751 516.5098 503.3958 2.6140 27.6706 30.6000 2.9294

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 565.2650 119.8402 552.4154 1118.3148 0.5055 0.1355 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0276 6.7577 527.6036 502.7080 491.5697 0.0259 0.2927

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 591.2593 0.0000 591.2593 1115.7310 0.5299 0.1989 0.5911

NASA/TM—2013-218094 H–80
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6284 525.1942 502.8745 0.0000 0.0600 0.0402 0.0501

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8771 8.0060 1.2004 553.2487 30.7485 251.1532 1.9469

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191575.078 0.439 705.566 629029.875 0.629227E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.555 EfDer = 1.000 SH = 0.743594E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.173 3705.867 8.006 553.248 1.000 1.000 0.980

 W Kg/sec = 29.624 Wdry = 65.124 WH2O = 0.048 lbm/sec H2O = 0.426g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.586 3588.292 1.380 0.249 53.372 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109611.445 51122.875 1.507 545.479 361.935 424.468 1.173

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 482.26 -0.17 482.26 0.43 0.72 628.45

 MEAN 17.74 0.00 -0.02 482.26 -0.17 482.26 0.43 0.67

 HUB 15.05 0.00 -0.02 482.26 -0.17 482.26 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.39 46.36 7.03 649.06 808.75 7.07 534.59 502.70 1.97

 MEAN 49.96 43.40 6.56 573.66 749.57 7.07 534.59 502.70 1.97

 HUB 45.27 38.84 6.43 486.71 685.30 7.07 534.59 502.70 1.97

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 566.51 297.88 481.87 1150.15 0.49 2.26 1.98 8.75

 MEAN 17.51 580.21 311.45 489.54 1146.44 0.51 2.34 2.07 6.78

 HUB 14.85 631.07 387.87 497.80 1142.98 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.65 591.34 342.77 0.51 5904.42 0.92 0.91

 MEAN 566.16 551.84 254.71 0.48 5455.37 0.92 0.91 0.91 1.47

 HUB 480.25 506.30 92.37 0.44 5762.40 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.58 1.20 8.13 583.88 1.06 558.14 515.16 1.13

 MEAN 9.45 1.18 7.95 581.55 1.05 554.55 514.34 1.24

 HUB 9.54 1.19 7.77 583.14 1.05 551.20 515.18 1.34

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.72 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.47 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.92 10.51 6.50 4.01 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 641.9476 313.4942 560.1947 1141.4835 0.5624 -0.1669 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.5073 7.6917 549.8125 515.1198 1.4015 29.2321 31.5000 2.2679

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 540.4314 117.8915 527.4161 1151.4325 0.4694 0.1405 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4867 8.1741 559.4352 514.6384 451.3937 0.0231 0.3165

 

NASA/TM—2013-218094 H–81
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 551.5056 0.0000 551.5056 1150.4000 0.4794 0.2262 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1024 558.4649 514.6765 0.0000 0.0600 0.0384 0.0949

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8804 9.4628 1.1820 582.8484 29.6080 240.2138 1.8621

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184654.719 0.450 680.078 602077.688 0.826142E-03

 

Melt Ratio at Stator LE, Throat, TE

0.65340E-01 0.86235E-01 0.14722E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.886 EfDer = 1.000 SH = 0.917763E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.173 3705.867 9.463 582.846 1.000 1.000 0.980

 W Kg/sec = 29.624 Wdry = 65.113 WH2O = 0.060 lbm/sec H2O = 0.599g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.321 3495.989 1.380 0.249 53.378 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96156.383 51119.371 1.633 513.330 314.353 395.845 1.259

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 449.56 -0.15 449.56 0.39 0.66 587.57

 MEAN 16.97 0.00 -0.02 449.56 -0.15 449.56 0.39 0.61

 HUB 14.32 0.00 -0.02 449.56 -0.15 449.56 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.19 46.36 7.83 622.86 768.28 8.54 566.65 514.52 1.08

 MEAN 50.69 43.80 6.89 548.83 709.57 8.54 566.65 514.52 1.08

 HUB 45.86 37.84 8.02 463.11 645.53 8.54 566.65 514.52 1.08

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 536.26 289.26 451.56 1180.50 0.45 2.16 1.89 8.34

 MEAN 16.57 546.53 297.63 458.37 1176.85 0.46 2.24 1.97 6.35

 HUB 13.89 590.60 363.25 465.67 1173.39 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 610.58 554.21 321.32 0.47 5464.19 0.92 0.91

 MEAN 536.00 516.65 238.36 0.44 4935.57 0.92 0.91 0.91 1.49

 HUB 449.20 473.54 85.94 0.40 5047.83 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.08 1.17 9.64 611.16 1.05 588.12 525.05 0.69

 MEAN 10.92 1.15 9.44 608.42 1.04 584.49 524.12 0.74

 HUB 10.95 1.16 9.23 609.00 1.04 581.05 524.48 0.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.64 35.43 31.50 3.93 0.93 0.41 1.40

 MEAN 33.00 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.96 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 589.1646 299.3075 507.4741 1174.0012 0.5018 -0.1160 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9686 9.2566 581.7205 524.6359 0.7926 30.5320 32.4000 1.8680

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 502.3299 112.6579 489.5340 1181.6305 0.4251 0.1633 2.2705

 

NASA/TM—2013-218094 H–82
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9526 9.6888 589.3093 524.3372 432.2457 0.0203 0.3376

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 498.1774 0.0000 498.1774 1181.9225 0.4215 0.2503 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6851 589.6347 524.2942 0.0000 0.0600 0.0378 0.1609

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8815 10.9256 1.1546 609.5109 26.6827 243.0674 1.8842

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 166572.969 0.447 613.484 596196.750 0.975931E-03

 

Melt Ratio at Stator LE, Throat, TE

0.35617E+00 0.39416E+00 0.49204E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.137 EfDer = 1.000 SH = 0.104289E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.173 3705.867 10.926 609.506 1.000 1.000 0.980

 W Kg/sec = 29.624 Wdry = 65.105 WH2O = 0.068 lbm/sec H2O = 0.765g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.054 3418.669 1.379 0.250 53.382 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85602.305 51116.852 1.830 509.668 278.466 384.739 1.382

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 403.09 -0.14 403.09 0.34 0.60 546.53

 MEAN 15.91 0.00 -0.02 403.09 -0.14 403.09 0.34 0.55

 HUB 13.07 0.00 -0.02 403.09 -0.14 403.09 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.78 47.36 8.42 592.46 716.70 10.10 596.50 524.18 0.64

 MEAN 51.94 44.80 7.14 514.62 653.81 10.10 596.50 524.18 0.64

 HUB 46.37 38.84 7.53 422.68 584.18 10.10 596.50 524.18 0.64

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 499.70 288.06 408.31 1208.28 0.41 2.05 1.78 7.43

 MEAN 15.50 503.22 284.65 414.97 1204.16 0.42 2.13 1.86 5.75

 HUB 12.59 535.47 329.60 422.01 1200.18 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 580.18 502.04 292.11 0.42 5170.42 0.92 0.91

 MEAN 501.19 468.07 216.54 0.39 4413.60 0.92 0.91 0.91 1.54

 HUB 407.16 429.08 77.56 0.36 4151.48 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.61 1.15 11.23 636.27 1.04 616.28 533.48 0.44

 MEAN 12.35 1.13 10.97 632.35 1.04 612.08 532.20 0.48

 HUB 12.26 1.12 10.72 630.99 1.04 608.04 531.83 0.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.20 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.45 27.56 23.50 4.06 0.93 0.42 1.64

 HUB 37.99 10.41 6.50 3.91 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 558.7830 289.8694 477.7177 1200.2886 0.4655 -0.1941 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3780 10.6916 608.2114 532.5746 0.5129 31.2485 33.0000 1.7515

 

NASA/TM—2013-218094 H–83
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 482.8365 110.2561 470.0794 1206.5131 0.4002 0.0751 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3528 11.0788 614.5370 532.3433 410.5396 0.0376 0.3503

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 467.9264 0.0000 467.9264 1207.5790 0.3875 0.2741 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1539 615.6580 532.3252 0.0000 0.0600 0.0377 0.1274

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8836 12.3527 1.1306 633.1782 23.6993 250.4996 1.9419

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 148082.281 0.440 545.383 606799.063 0.108618E-02

 

Melt Ratio at Stator LE, Throat, TE

0.76847E+00 0.80930E+00 0.92249E+00

 trTOT = 1.3129 Tt4 = 633.1782 T1 = 482.2695

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 941266.00 3466.6582 178.7795 2.3906 0.8667 5.3638 1.3129 37.3740

NASA/TM—2013-218094 H–84
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.708 EfDer = 0.999 SH = 0.263523E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.054 3676.041 5.167 482.269 1.000 1.000 0.980

 W Kg/sec = 29.116 Wdry = 64.038 WH2O = 0.017 lbm/sec H2O = 0.113g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 175.712 3812.334 1.381 0.249 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143407.625 50255.051 1.617 831.557 514.402 619.754 1.205 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 413.90 -0.14 413.90 0.39 0.74 686.32

 MEAN 17.06 0.00 -0.02 413.90 -0.14 413.90 0.39 0.65

 HUB 12.51 0.00 -0.02 413.90 -0.14 413.90 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.98 50.47 7.51 661.80 780.69 4.65 468.50 465.86 5.98

 MEAN 52.91 47.20 5.71 547.28 686.28 4.65 468.50 465.86 5.98

 HUB 44.13 38.62 5.51 401.31 576.61 4.65 468.50 465.86 5.98

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 650.24 370.97 534.03 1075.40 0.60 7.29 6.52 16.04

 MEAN 18.04 685.06 410.69 548.30 1069.87 0.64 7.43 6.80 12.53

 HUB 15.00 789.04 538.48 576.74 1060.00 0.74 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.80 608.09 290.83 0.57 7656.00 0.92 0.91

 MEAN 578.59 573.43 167.89 0.54 7409.73 0.92 0.91 0.91 1.33

 HUB 481.19 579.57 57.29 0.55 8078.97 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.26 521.75 1.08 487.77 488.46 3.76

 MEAN 6.66 1.29 5.07 520.48 1.08 482.76 488.12 4.46

 HUB 6.81 1.32 4.73 523.93 1.09 473.89 490.84 6.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.79 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.83 17.02 12.70 4.32 0.92 0.30 2.22

 HUB 43.04 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 724.7039 409.8969 597.6456 1066.6249 0.6794 -0.0744 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7074 4.9416 479.8505 489.2549 5.0831 34.4444 35.4000 0.9556

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 567.4122 138.8064 550.1722 1084.6125 0.5231 0.3143 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6786 5.5550 496.1832 488.1530 554.9116 0.0269 0.4251

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 563.1907 0.0000 563.1907 1085.0039 0.5191 0.3460 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5526 496.5700 488.2468 0.0000 0.0600 0.0395 0.3129

NASA/TM—2013-218094 H–85
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8774 6.6570 1.2883 522.0505 39.7832 218.7431 1.6957

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 247578.922 0.565 896.179 685631.813 0.397243E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.710 EfDer = 1.000 SH = 0.566132E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.054 3676.041 6.657 522.050 1.000 1.000 0.980

 W Kg/sec = 29.116 Wdry = 64.018 WH2O = 0.036 lbm/sec H2O = 0.282g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 141.901 3664.226 1.381 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124029.164 50249.082 1.421 590.487 415.504 468.502 1.128

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 504.10 -0.17 504.10 0.46 0.76 657.10

 MEAN 18.08 0.00 -0.02 504.10 -0.17 504.10 0.46 0.70

 HUB 15.21 0.00 -0.02 504.10 -0.17 504.10 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.60 46.36 6.24 659.23 830.02 5.76 501.65 488.61 4.00

 MEAN 49.01 42.30 6.71 579.94 768.54 5.76 501.65 488.61 4.00

 HUB 44.08 37.84 6.24 487.93 701.68 5.76 501.65 488.61 4.00

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 583.25 300.52 499.87 1117.03 0.52 2.33 2.04 9.02

 MEAN 18.01 598.08 313.99 509.03 1112.90 0.54 2.40 2.13 7.35

 HUB 15.22 651.00 393.19 518.85 1109.05 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 655.06 612.83 354.54 0.55 6140.25 0.92 0.91

 MEAN 577.75 573.31 263.76 0.52 5658.13 0.92 0.91 0.91 1.45

 HUB 488.35 527.50 95.16 0.48 5988.19 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.74 553.68 1.06 526.37 503.07 2.00

 MEAN 7.98 1.20 6.57 551.19 1.06 522.48 502.12 2.23

 HUB 8.06 1.21 6.40 552.89 1.06 518.87 503.14 2.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.01 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.67 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.16 10.39 6.50 3.89 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 665.7557 314.8741 586.5875 1107.0276 0.6014 -0.1779 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0281 6.3061 517.0134 503.1207 2.6407 28.2264 30.6000 2.3736

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 553.5706 117.3609 540.9869 1118.7222 0.4948 0.1481 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0062 6.7871 527.9917 502.4470 491.5697 0.0248 0.3007

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 578.4926 0.0000 578.4926 1116.2969 0.5182 0.2086 0.5911

NASA/TM—2013-218094 H–86
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6653 525.7307 502.6084 0.0000 0.0600 0.0385 0.0654

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8794 7.9860 1.1996 552.5854 30.5367 247.8415 1.9213

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 190263.984 0.443 688.712 615909.563 0.644137E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.873 EfDer = 1.000 SH = 0.761152E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.054 3676.041 7.986 552.585 1.000 1.000 0.980

 W Kg/sec = 29.116 Wdry = 64.006 WH2O = 0.049 lbm/sec H2O = 0.437g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.697 3561.548 1.380 0.249 53.373 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107507.922 50245.230 1.531 545.479 356.405 424.468 1.191

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 473.01 -0.16 473.01 0.42 0.71 623.76

 MEAN 17.74 0.00 -0.02 473.01 -0.16 473.01 0.42 0.66

 HUB 15.05 0.00 -0.02 473.01 -0.16 473.01 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.70 46.36 7.34 643.84 799.04 7.08 534.64 502.46 2.02

 MEAN 50.27 43.40 6.87 569.04 740.09 7.08 534.64 502.46 2.02

 HUB 45.60 38.84 6.76 482.80 676.01 7.08 534.64 502.46 2.02

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 559.73 299.15 473.08 1149.97 0.49 2.26 1.98 8.75

 MEAN 17.51 572.85 311.67 480.64 1146.24 0.50 2.34 2.07 6.78

 HUB 14.85 622.68 385.78 488.78 1142.74 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.50 580.46 336.35 0.50 5929.33 0.92 0.91

 MEAN 561.60 541.74 249.93 0.47 5459.22 0.92 0.91 0.91 1.48

 HUB 476.38 497.10 90.60 0.44 5731.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.55 1.20 8.14 583.09 1.06 557.97 514.91 1.17

 MEAN 9.42 1.18 7.96 580.68 1.05 554.36 514.06 1.27

 HUB 9.49 1.19 7.78 582.08 1.05 550.98 514.82 1.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.31 35.41 31.50 3.91 0.93 0.41 1.40

 MEAN 32.96 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.28 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 632.6321 313.7190 549.3667 1141.5293 0.5542 -0.1633 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4727 7.7094 549.8591 514.8147 1.4350 29.7288 31.5000 1.7712

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 530.0499 115.6268 517.2845 1151.4136 0.4603 0.1517 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4538 8.1910 559.4204 514.3361 451.3937 0.0224 0.3236

 

NASA/TM—2013-218094 H–87
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 540.7575 0.0000 540.7575 1150.4327 0.4700 0.2341 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1222 558.5000 514.3733 0.0000 0.0600 0.0377 0.1068

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8816 9.4304 1.1809 581.9411 29.3641 237.4420 1.8406

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183143.359 0.453 662.937 590279.438 0.844853E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.67384E-01 0.88803E-01 0.15112E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.163 EfDer = 1.000 SH = 0.937514E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.054 3676.041 9.430 581.939 1.000 1.000 0.980

 W Kg/sec = 29.116 Wdry = 63.994 WH2O = 0.060 lbm/sec H2O = 0.612g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 105.759 3470.555 1.380 0.249 53.379 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94444.617 50241.746 1.657 513.330 309.783 395.845 1.278

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 441.56 -0.15 441.56 0.38 0.66 583.30

 MEAN 16.97 0.00 -0.02 441.56 -0.15 441.56 0.38 0.61

 HUB 14.32 0.00 -0.02 441.56 -0.15 441.56 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.45 46.36 8.09 617.85 759.54 8.54 566.32 514.23 1.11

 MEAN 50.96 43.80 7.16 544.41 701.09 8.54 566.32 514.23 1.11

 HUB 46.14 37.84 8.30 459.38 637.29 8.54 566.32 514.23 1.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 530.20 289.91 443.92 1179.94 0.45 2.16 1.89 8.34

 MEAN 16.57 539.95 297.49 450.60 1176.29 0.46 2.24 1.97 6.35

 HUB 13.89 583.10 361.17 457.77 1172.82 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 605.66 544.76 315.75 0.46 5476.39 0.92 0.91

 MEAN 531.68 507.83 234.20 0.43 4933.08 0.92 0.91 0.91 1.50

 HUB 445.58 465.49 84.41 0.40 5018.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.04 1.17 9.63 610.09 1.05 587.56 524.73 0.71

 MEAN 10.87 1.15 9.43 607.29 1.04 583.93 523.79 0.77

 HUB 10.90 1.16 9.22 607.73 1.04 580.49 524.09 0.83

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.15 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.43 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.27 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 581.4450 299.1591 498.5801 1173.5641 0.4955 -0.1140 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9187 9.2533 581.2891 524.2855 0.8189 30.9647 32.4000 1.4353

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 493.5076 110.6793 480.9364 1181.1750 0.4178 0.1726 2.2705

 

NASA/TM—2013-218094 H–88
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9039 9.6854 588.8574 523.9855 432.2457 0.0198 0.3438

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 489.4287 0.0000 489.4287 1181.4554 0.4143 0.2571 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6815 589.1709 523.9442 0.0000 0.0600 0.0373 0.1700

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8823 10.8775 1.1535 608.3541 26.4333 240.6343 1.8654

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 165025.078 0.450 597.353 585159.750 0.996526E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.36153E+00 0.39986E+00 0.49860E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.372 EfDer = 0.999 SH = 0.106435E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.054 3676.041 10.878 608.349 1.000 1.000 0.980

 W Kg/sec = 29.116 Wdry = 63.986 WH2O = 0.068 lbm/sec H2O = 0.780g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 93.747 3394.378 1.379 0.250 53.383 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84196.813 50239.238 1.856 509.668 274.638 384.739 1.401

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 396.48 -0.14 396.48 0.33 0.60 542.65

 MEAN 15.91 0.00 -0.02 396.48 -0.14 396.48 0.33 0.54

 HUB 13.07 0.00 -0.02 396.48 -0.14 396.48 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.00 47.36 8.64 587.70 709.04 10.08 595.77 523.83 0.66

 MEAN 52.17 44.80 7.37 510.48 646.47 10.08 595.77 523.83 0.66

 HUB 46.61 38.84 7.77 419.28 577.15 10.08 595.77 523.83 0.66

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.50 288.06 401.94 1207.34 0.41 2.05 1.78 7.43

 MEAN 15.50 497.53 284.09 408.45 1203.24 0.41 2.13 1.86 5.75

 HUB 12.59 528.98 327.60 415.32 1199.28 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 575.51 494.15 287.45 0.41 5170.23 0.92 0.91

 MEAN 497.16 460.68 213.06 0.38 4404.93 0.92 0.91 0.91 1.54

 HUB 403.88 422.27 76.28 0.35 4126.31 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.54 1.15 11.19 634.89 1.04 615.32 533.10 0.46

 MEAN 12.28 1.13 10.94 630.96 1.04 611.15 531.80 0.50

 HUB 12.19 1.12 10.69 629.53 1.03 607.13 531.41 0.54

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.63 35.57 31.50 4.07 0.93 0.45 1.40

 MEAN 34.82 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.27 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 551.8159 289.3020 469.8991 1199.5121 0.4600 -0.1918 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3105 10.6693 607.4245 532.1727 0.5326 31.6193 33.0000 1.3807

 

NASA/TM—2013-218094 H–89
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 474.8709 108.4372 462.3243 1205.7313 0.3938 0.0848 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2871 11.0571 613.7412 531.9410 410.5396 0.0367 0.3555

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 460.3155 0.0000 460.3155 1206.7534 0.3814 0.2799 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1286 614.8168 531.9224 0.0000 0.0600 0.0373 0.1359

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8841 12.2864 1.1295 631.7708 23.4490 248.3965 1.9256

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 146525.219 0.442 530.388 596180.750 0.110828E-02

 

Melt Ratio at Stator LE, Throat, TE

0.77552E+00 0.81657E+00 0.93020E+00

 trTOT = 1.3100 Tt4 = 631.7708 T1 = 482.2694

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 932536.50 3375.5701 175.7116 2.3778 0.8687 5.7078 1.3100 37.3740

NASA/TM—2013-218094 H–90
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.047 EfDer = 0.999 SH = 0.267217E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.941 3645.648 5.167 482.269 1.000 1.000 0.980

 W Kg/sec = 28.610 Wdry = 62.924 WH2O = 0.017 lbm/sec H2O = 0.115g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.658 3780.815 1.381 0.249 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140477.078 49381.598 1.645 831.557 505.464 619.754 1.226

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 405.44 -0.14 405.44 0.38 0.73 680.64

 MEAN 17.06 0.00 -0.02 405.44 -0.14 405.44 0.38 0.64

 HUB 12.51 0.00 -0.02 405.44 -0.14 405.44 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.30 50.47 7.83 656.33 771.58 4.67 469.06 465.85 5.94

 MEAN 53.25 47.20 6.05 542.76 677.58 4.67 469.06 465.85 5.94

 HUB 44.48 38.62 5.86 398.00 568.24 4.67 469.06 465.85 5.94

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 641.43 371.73 522.73 1076.14 0.60 7.29 6.52 16.04

 MEAN 18.04 675.04 409.55 536.61 1070.61 0.63 7.43 6.80 12.53

 HUB 15.00 775.81 533.20 563.54 1061.02 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.33 595.18 284.59 0.55 7671.77 0.92 0.91

 MEAN 573.80 561.18 164.25 0.52 7389.08 0.92 0.91 0.91 1.34

 HUB 477.21 566.32 55.98 0.53 7999.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.29 521.50 1.08 488.43 488.32 3.74

 MEAN 6.64 1.29 5.10 520.06 1.08 483.43 487.87 4.44

 HUB 6.77 1.31 4.77 523.18 1.08 474.80 490.38 6.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.42 28.57 24.20 4.37 0.93 0.36 1.80

 MEAN 37.35 17.02 12.70 4.32 0.93 0.31 2.22

 HUB 43.42 -5.67 -9.30 3.63 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 712.9751 408.7568 584.1672 1067.6029 0.6678 -0.0719 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6885 4.9769 480.7333 488.9636 5.0162 34.9815 35.4000 0.4185

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 555.3280 135.8502 538.4551 1085.2847 0.5117 0.3231 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6616 5.5842 496.8008 487.9067 554.9116 0.0262 0.4321

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 551.0238 0.0000 551.0238 1085.6748 0.5075 0.3544 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5835 497.1865 488.0070 0.0000 0.0600 0.0380 0.3227

NASA/TM—2013-218094 H–91
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8799 6.6422 1.2855 521.5773 39.3102 216.6372 1.6794

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244641.438 0.568 870.156 671621.063 0.405074E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.052 EfDer = 1.000 SH = 0.578866E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.941 3645.648 6.642 521.577 1.000 1.000 0.980

 W Kg/sec = 28.610 Wdry = 62.905 WH2O = 0.036 lbm/sec H2O = 0.289g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.682 3635.578 1.381 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121528.141 49375.559 1.444 590.487 409.012 468.502 1.145

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 493.94 -0.17 493.94 0.45 0.75 651.96

 MEAN 18.08 0.00 -0.02 493.94 -0.17 493.94 0.45 0.70 

 HUB 15.21 0.00 -0.02 493.94 -0.17 493.94 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.94 46.36 6.58 653.78 819.53 5.78 501.99 488.39 4.05 

 MEAN 49.35 42.30 7.05 575.15 758.26 5.78 501.99 488.39 4.05

 HUB 44.42 37.84 6.58 483.90 691.59 5.78 501.99 488.39 4.05

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 575.93 301.99 490.41 1117.14 0.52 2.33 2.04 9.02

 MEAN 18.01 590.13 314.37 499.42 1112.98 0.53 2.40 2.13 7.35

 HUB 15.22 641.96 391.10 509.08 1109.10 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 649.65 601.14 347.65 0.54 6170.20 0.92 0.91

 MEAN 572.97 562.41 258.61 0.51 5664.80 0.92 0.91 0.91 1.46

 HUB 484.31 517.54 93.21 0.47 5956.24 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.07 1.22 6.75 553.09 1.06 526.46 502.85 2.04

 MEAN 7.95 1.20 6.58 550.51 1.06 522.56 501.85 2.28

 HUB 8.02 1.21 6.41 552.00 1.06 518.92 502.78 2.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.62 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.19 27.38 23.50 3.88 0.93 0.39 1.63

 HUB 37.53 10.38 6.50 3.88 0.93 0.40 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 655.3909 315.2486 574.5916 1107.4333 0.5918 -0.1735 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9999 6.3306 517.3950 502.8204 2.6743 28.7513 30.6000 1.8487

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 542.4855 115.0108 530.1537 1118.9912 0.4848 0.1596 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9799 6.8088 528.2490 502.1588 491.5697 0.0240 0.3081

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 566.5323 0.0000 566.5323 1116.6982 0.5073 0.2169 0.5911

NASA/TM—2013-218094 H–92
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6926 526.1119 502.3145 0.0000 0.0600 0.0378 0.0786

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8806 7.9601 1.1984 551.8665 30.2909 244.7732 1.8975

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188740.281 0.447 671.324 603099.688 0.658780E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.166 EfDer = 1.000 SH = 0.778304E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.941 3645.648 7.960 551.866 1.000 1.000 0.980

 W Kg/sec = 28.610 Wdry = 62.892 WH2O = 0.049 lbm/sec H2O = 0.447g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 119.893 3534.401 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105516.695 49371.688 1.554 545.479 351.128 424.468 1.209

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 464.25 -0.16 464.25 0.41 0.70 619.01

 MEAN 17.74 0.00 -0.02 464.25 -0.16 464.25 0.41 0.65

 HUB 15.05 0.00 -0.02 464.25 -0.16 464.25 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.99 46.36 7.63 638.51 789.57 7.09 534.58 502.19 2.07

 MEAN 50.57 43.40 7.17 564.34 730.88 7.09 534.58 502.19 2.07

 HUB 45.89 38.84 7.05 478.80 667.03 7.09 534.58 502.19 2.07

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 553.19 299.89 464.85 1149.64 0.48 2.26 1.98 8.75

 MEAN 17.51 565.75 311.50 472.27 1145.91 0.49 2.34 2.07 6.78

 HUB 14.85 614.63 383.55 480.27 1142.40 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.24 570.28 330.35 0.50 5944.06 0.92 0.91

 MEAN 556.96 532.25 245.45 0.46 5456.19 0.92 0.91 0.91 1.49

 HUB 472.44 488.43 88.89 0.43 5698.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.51 1.19 8.13 582.20 1.05 557.65 514.61 1.20

 MEAN 9.38 1.18 7.95 579.71 1.05 554.04 513.73 1.31

 HUB 9.44 1.19 7.77 580.94 1.05 550.65 514.42 1.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.83 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.41 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.61 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 623.7644 313.5476 539.2308 1141.4178 0.5465 -0.1601 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4289 7.7164 549.7540 514.4660 1.4729 30.1768 31.5000 1.3232

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 520.3900 113.5196 507.8574 1151.2198 0.4520 0.1617 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4114 8.1954 559.2352 513.9894 451.3937 0.0218 0.3299

 

NASA/TM—2013-218094 H–93
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 530.7734 0.0000 530.7734 1150.2844 0.4614 0.2411 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1292 558.3589 514.0262 0.0000 0.0600 0.0372 0.1172

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8823 9.3884 1.1794 580.9412 29.0832 234.9673 1.8215

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 181400.219 0.457 645.216 578774.250 0.863279E-03

 

Melt Ratio at Stator LE, Throat, TE

0.68656E-01 0.90440E-01 0.15371E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.410 EfDer = 0.999 SH = 0.957159E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.941 3645.648 9.388 580.939 1.000 1.000 0.980

 W Kg/sec = 28.610 Wdry = 62.881 WH2O = 0.060 lbm/sec H2O = 0.625g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.296 3444.822 1.380 0.249 53.379 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 92843.328 49368.215 1.680 513.330 305.501 395.845 1.296

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 434.07 -0.15 434.07 0.37 0.65 578.97

 MEAN 16.97 0.00 -0.02 434.07 -0.15 434.07 0.37 0.60

 HUB 14.32 0.00 -0.02 434.07 -0.15 434.07 0.37 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.69 46.36 8.33 612.74 751.04 8.53 565.84 513.90 1.15

 MEAN 51.21 43.80 7.41 539.91 692.88 8.53 565.84 513.90 1.15

 HUB 46.39 37.84 8.55 455.58 629.37 8.53 565.84 513.90 1.15

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 524.37 290.07 436.83 1179.21 0.44 2.16 1.89 8.34

 MEAN 16.57 533.62 296.94 443.38 1175.57 0.45 2.24 1.97 6.35

 HUB 13.89 575.94 358.95 450.40 1172.10 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 600.65 535.98 310.58 0.45 5479.47 0.92 0.91

 MEAN 527.29 499.65 230.35 0.43 4923.90 0.92 0.91 0.91 1.51

 HUB 441.90 457.98 82.95 0.39 4987.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.98 1.17 9.60 608.87 1.05 586.84 524.35 0.74

 MEAN 10.81 1.15 9.40 606.04 1.04 583.22 523.39 0.80

 HUB 10.83 1.15 9.20 606.36 1.04 579.79 523.65 0.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.59 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.81 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 38.55 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 574.0943 298.6048 490.3259 1172.9562 0.4894 -0.1122 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8559 9.2361 580.6879 523.8795 0.8483 31.3411 32.4000 1.0589

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 485.3725 108.8549 473.0085 1180.5276 0.4111 0.1805 2.2705

 

NASA/TM—2013-218094 H–94
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8421 9.6661 588.2133 523.5779 432.2457 0.0194 0.3491

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 481.3651 0.0000 481.3651 1180.7972 0.4077 0.2629 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6620 588.5157 523.5381 0.0000 0.0600 0.0370 0.1777

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8828 10.8163 1.1521 607.0710 26.1505 238.5211 1.8490

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 163267.281 0.453 580.720 574395.125 0.101714E-02

 

Melt Ratio at Stator LE, Throat, TE

0.36491E+00 0.40347E+00 0.50278E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.574 EfDer = 0.999 SH = 0.108602E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.941 3645.648 10.816 607.066 1.000 1.000 0.980

 W Kg/sec = 28.610 Wdry = 62.873 WH2O = 0.068 lbm/sec H2O = 0.794g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.541 3369.870 1.379 0.250 53.384 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 82895.313 49365.711 1.880 509.668 271.110 384.739 1.419

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 390.35 -0.13 390.35 0.33 0.59 538.73

 MEAN 15.91 0.00 -0.02 390.35 -0.13 390.35 0.33 0.54

 HUB 13.07 0.00 -0.02 390.35 -0.13 390.35 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.19 47.36 8.83 582.84 701.59 10.05 594.87 523.43 0.69

 MEAN 52.37 44.80 7.57 506.26 639.38 10.05 594.87 523.43 0.69

 HUB 46.82 38.84 7.98 415.81 570.42 10.05 594.87 523.43 0.69

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.47 287.57 396.08 1206.21 0.41 2.05 1.78 7.43

 MEAN 15.50 492.09 283.20 402.44 1202.15 0.41 2.13 1.86 5.75

 HUB 12.59 522.79 325.44 409.15 1198.22 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 570.75 486.90 283.18 0.40 5161.50 0.92 0.91 

 MEAN 493.05 453.86 209.85 0.38 4390.99 0.92 0.91 0.91 1.55

 HUB 400.54 415.99 75.11 0.35 4098.98 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.46 1.15 11.14 633.35 1.04 614.17 532.64 0.48

 MEAN 12.20 1.13 10.89 629.42 1.04 610.04 531.34 0.52

 HUB 12.10 1.12 10.64 627.94 1.03 606.06 530.93 0.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.98 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 35.13 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.50 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 545.2303 288.3882 462.7185 1198.5415 0.4549 -0.1899 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2265 10.6295 606.4407 531.7057 0.5549 31.9331 33.0000 1.0669

 

NASA/TM—2013-218094 H–95
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 467.6028 106.7775 455.2482 1204.7355 0.3881 0.0928 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2046 11.0157 612.7272 531.4735 410.5396 0.0361 0.3598

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 453.3641 0.0000 453.3641 1205.7195 0.3760 0.2846 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0840 613.7626 531.4545 0.0000 0.0600 0.0370 0.1429

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8844 12.2033 1.1282 630.2078 23.1691 246.6353 1.9119

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 144782.156 0.444 514.970 585811.000 0.113072E-02

 

Melt Ratio at Stator LE, Throat, TE

0.77967E+00 0.82085E+00 0.93470E+00

 trTOT = 1.3068 Tt4 = 630.2078 T1 = 482.2693

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 922831.38 3282.3857 172.6579 2.3617 0.8702 6.0474 1.3068 37.3740

NASA/TM—2013-218094 H–96
 25μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.948 EfDer = 0.985 SH = 0.469724E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.571 3889.248 5.167 462.092 1.000 1.000 0.980

 W Kg/sec = 34.350 Wdry = 75.567 WH2O = 0.004 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.916 4120.575 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 167507.391 59295.645 1.400 831.557 593.965 619.754 1.043

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 483.45 -0.17 483.45 0.47 0.83 741.81

 MEAN 17.06 0.00 -0.02 483.45 -0.17 483.45 0.47 0.74

 HUB 12.51 0.00 -0.02 483.45 -0.17 483.45 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.38 50.47 4.91 700.18 851.01 4.45 443.29 452.61 3.41

 MEAN 50.15 47.20 2.95 579.02 754.44 4.45 443.29 452.61 3.41

 HUB 41.30 38.62 2.68 424.59 643.54 4.45 443.29 452.61 3.41

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 726.09 354.63 633.59 1043.99 0.70 7.29 6.52 16.04

 MEAN 18.04 770.86 412.33 651.31 1038.60 0.74 7.43 6.80 12.53

 HUB 15.00 909.87 579.49 701.46 1024.88 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.18 721.70 345.55 0.69 7319.48 0.92 0.90

 MEAN 612.14 681.27 199.81 0.66 7439.72 0.92 0.90 0.90 1.21

 HUB 509.10 704.99 70.39 0.69 8694.43 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 502.05 1.09 459.65 478.45 1.83

 MEAN 6.81 1.32 4.74 502.71 1.09 454.92 478.95 2.20

 HUB 7.12 1.38 4.29 509.56 1.10 442.97 483.37 3.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.24 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.34 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.56 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 832.5673 411.5339 723.7458 1031.8522 0.8069 -0.1061 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8819 4.5042 449.0211 480.3107 2.8296 29.6233 35.4000 5.7767

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 677.7724 165.8038 657.1792 1053.2300 0.6435 0.2307 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8113 5.1721 467.8262 479.7078 554.9116 0.0413 0.3608

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 679.3276 0.0000 679.3276 1053.0200 0.6451 0.2564 1.3089

NASA/TM—2013-218094 H–97
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1138 467.6601 479.5954 0.0000 0.0600 0.0715 0.2048

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8257 6.7433 1.3050 504.7716 42.6812 237.4391 1.8406

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 265365.656 0.541 1133.267 863373.250 0.532208E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.581 EfDer = 0.990 SH = 0.599554E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.571 3889.248 6.743 504.771 1.000 1.000 0.980

 W Kg/sec = 34.350 Wdry = 75.566 WH2O = 0.005 lbm/sec H2O = 0.030g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.513 3942.542 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146440.594 59295.340 1.241 590.487 475.709 468.502 0.985

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 595.20 -0.20 595.20 0.56 0.86 707.01

 MEAN 18.08 0.00 -0.02 595.20 -0.20 595.20 0.56 0.80

 HUB 15.21 0.00 -0.02 595.20 -0.20 595.20 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.53 46.36 3.17 697.47 917.07 5.46 476.28 479.51 1.13

 MEAN 45.88 42.30 3.58 613.58 854.98 5.46 476.28 479.51 1.13

 HUB 40.95 37.84 3.11 516.23 788.01 5.46 476.28 479.51 1.13

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 646.69 276.15 584.76 1090.92 0.59 2.33 2.04 9.02

 MEAN 18.01 666.37 301.29 594.36 1087.40 0.61 2.40 2.13 7.35

 HUB 15.22 727.44 403.97 604.96 1084.23 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 693.06 718.16 416.91 0.66 5643.21 0.92 0.91

 MEAN 611.26 670.33 309.97 0.62 5429.99 0.92 0.91 0.91 1.37

 HUB 516.67 615.37 112.70 0.57 6152.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.19 1.22 6.48 535.57 1.06 501.95 495.29 0.48

 MEAN 8.14 1.21 6.33 534.41 1.06 498.70 494.75 0.53

 HUB 8.34 1.24 6.19 538.35 1.07 495.80 496.69 0.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.28 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.88 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.73 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 763.3330 302.1395 700.9914 1077.0278 0.7087 -0.2346 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2028 5.8896 489.2650 495.6675 0.7238 23.3169 30.6000 7.2831

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 659.3419 139.7852 644.3538 1090.0507 0.6049 0.0247 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1440 6.3791 501.1576 495.4046 491.5697 0.0411 0.2231

 

NASA/TM—2013-218094 H–98
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 701.4002 0.0000 701.4002 1085.0177 0.6464 0.1012 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1237 496.5592 495.3409 0.0000 0.0600 0.0731 -0.1104

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8265 8.0837 1.1988 536.1110 31.3412 279.7914 2.1689

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 194933.641 0.406 832.481 781240.563 0.626304E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.942 EfDer = 0.992 SH = 0.670532E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.571 3889.248 8.084 536.111 1.000 1.000 0.980

 W Kg/sec = 34.350 Wdry = 75.566 WH2O = 0.005 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.711 3825.573 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126121.117 59295.180 1.334 545.479 408.982 424.468 1.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 554.91 -0.19 554.91 0.50 0.80 670.01

 MEAN 17.74 0.00 -0.02 554.91 -0.19 554.91 0.50 0.74

 HUB 15.05 0.00 -0.02 554.91 -0.19 554.91 0.50 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.84 46.36 4.48 681.18 878.74 6.81 511.36 495.22 0.39

 MEAN 47.34 43.40 3.94 602.05 818.91 6.81 511.36 495.22 0.39

 HUB 42.64 38.84 3.80 510.80 754.34 6.81 511.36 495.22 0.39

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 617.31 279.02 550.66 1126.90 0.55 2.26 1.98 8.75

 MEAN 17.51 635.10 301.98 558.71 1123.63 0.57 2.34 2.07 6.78

 HUB 14.85 692.86 397.33 567.61 1120.65 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.35 676.71 393.34 0.60 5531.15 0.92 0.91

 MEAN 594.17 630.50 292.20 0.56 5289.95 0.92 0.91 0.91 1.40

 HUB 504.01 577.55 106.68 0.52 5903.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.68 1.20 7.92 566.29 1.06 535.66 508.63 0.20

 MEAN 9.61 1.19 7.76 564.98 1.05 532.55 508.09 0.21

 HUB 9.80 1.21 7.59 568.32 1.06 529.73 509.53 0.23

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.87 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.39 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 34.99 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 715.9479 303.9574 648.2216 1115.9476 0.6416 -0.2038 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6781 7.3613 525.3329 508.7699 0.2619 25.1223 31.5000 6.3777

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 625.4100 136.4290 610.3481 1126.2764 0.5553 0.0383 2.3726

 

NASA/TM—2013-218094 H–99
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6305 7.8305 535.0913 508.6089 451.3937 0.0345 0.2556

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 642.2648 0.0000 642.2648 1124.4451 0.5712 0.1469 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7016 533.3770 508.5310 0.0000 0.0600 0.0590 -0.0281

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8471 9.5830 1.1855 566.5280 30.4192 265.4645 2.0579

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189267.000 0.419 808.281 738890.563 0.710208E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.513 EfDer = 0.995 SH = 0.784810E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.571 3889.248 9.583 566.527 1.000 1.000 0.980

 W Kg/sec = 34.350 Wdry = 75.565 WH2O = 0.006 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.151 3721.458 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109747.586 59294.914 1.447 513.330 354.670 395.845 1.116

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 513.11 -0.18 513.11 0.45 0.73 625.47

 MEAN 16.97 0.00 -0.02 513.11 -0.18 513.11 0.45 0.68

 HUB 14.32 0.00 -0.02 513.11 -0.18 513.11 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.88 46.36 5.52 653.69 831.15 8.35 545.37 508.48 0.17

 MEAN 48.31 43.80 4.51 575.99 771.52 8.35 545.37 508.48 0.17

 HUB 43.46 37.84 5.62 486.02 706.87 8.35 545.37 508.48 0.17

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 581.30 275.04 512.12 1160.04 0.50 2.16 1.89 8.34

 MEAN 16.57 595.60 291.10 519.62 1156.60 0.51 2.24 1.97 6.35

 HUB 13.89 646.26 372.99 527.76 1153.41 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.79 629.31 365.75 0.54 5196.16 0.92 0.91

 MEAN 562.52 586.24 271.42 0.51 4827.66 0.92 0.91 0.91 1.42

 HUB 471.43 536.86 98.43 0.47 5183.41 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.26 1.18 9.51 594.87 1.05 567.72 519.79 0.10

 MEAN 11.14 1.16 9.31 592.86 1.05 564.35 519.03 0.11

 HUB 11.26 1.17 9.12 594.80 1.05 561.24 519.80 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.24 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.26 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.25 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 648.8963 292.7375 579.1124 1152.4419 0.5631 -0.1362 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.1998 9.0554 560.3492 519.5266 0.1236 26.8163 32.4000 5.5837

 

NASA/TM—2013-218094 H–100
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 574.1721 128.7700 559.5461 1159.9696 0.4950 0.0782 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1647 9.4633 567.6902 519.4277 432.2457 0.0284 0.2849

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 569.6044 0.0000 569.6044 1160.3737 0.4909 0.1880 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4585 568.1121 519.3638 0.0000 0.0600 0.0471 0.0757

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8629 11.1291 1.1613 594.1732 27.6476 265.9333 2.0615

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 172104.078 0.419 734.985 724008.813 0.853981E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.093 EfDer = 0.997 SH = 0.993038E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.571 3889.248 11.129 594.173 1.000 1.000 0.980

 W Kg/sec = 34.350 Wdry = 75.563 WH2O = 0.008 lbm/sec H2O = 0.075g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.834 3633.853 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96633.797 59294.426 1.629 509.668 312.783 384.739 1.230

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 455.04 -0.16 455.04 0.39 0.66 580.93

 MEAN 15.91 0.00 -0.02 455.04 -0.16 455.04 0.39 0.60

 HUB 13.07 0.00 -0.02 455.04 -0.16 455.04 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.81 47.36 6.45 621.78 770.63 10.04 577.54 519.35 0.10

 MEAN 49.89 44.80 5.09 540.09 706.35 10.04 577.54 519.35 0.10

 HUB 44.28 38.84 5.44 443.60 635.60 10.04 577.54 519.35 0.10

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 536.88 280.16 457.99 1190.90 0.45 2.05 1.78 7.43

 MEAN 15.50 544.52 282.02 465.80 1186.67 0.46 2.13 1.86 5.75

 HUB 12.59 583.05 339.44 474.06 1182.65 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.89 563.75 328.72 0.47 5028.96 0.92 0.91

 MEAN 525.99 525.83 243.97 0.44 4373.09 0.92 0.91 0.91 1.47

 HUB 427.31 482.13 87.86 0.41 4275.63 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.92 1.16 11.26 621.59 1.05 598.44 529.44 0.07

 MEAN 12.68 1.14 11.00 618.01 1.04 594.20 528.18 0.07

 HUB 12.64 1.14 10.73 617.48 1.04 590.18 528.00 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.45 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.19 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.60 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 611.6030 287.1888 539.9822 1181.4098 0.5177 -0.2169 2.0437

 

NASA/TM—2013-218094 H–101
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7141 10.6152 588.9925 528.5021 0.0818 28.0062 33.0000 4.9938

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 547.3007 124.9766 532.8404 1187.3997 0.4609 -0.0172 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6615 10.9660 594.9742 528.3849 410.5396 0.0500 0.3050

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 528.9415 0.0000 528.9415 1188.9554 0.4449 0.2215 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0801 596.5615 528.3980 0.0000 0.0600 0.0450 0.0479

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8700 12.6702 1.1385 619.0217 24.8522 270.1905 2.0945

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154792.781 0.418 661.056 729403.563 0.107762E-03

 

Melt Ratio at Stator LE, Throat, TE

0.50478E-01 0.58862E-01 0.82333E-01

 trTOT = 1.3396 Tt4 = 619.0217 T1 = 462.0915 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 976463.13 4170.0693 202.9162 2.4520 0.8266 2.9481 1.3396 37.3740

NASA/TM—2013-218094 H–102
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.297 EfDer = 0.998 SH = 0.493950E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.709 3626.421 5.167 462.091 1.000 1.000 0.980

 W Kg/sec = 30.322 Wdry = 66.705 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 179.119 3842.115 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143591.359 52341.773 1.586 831.557 524.310 619.754 1.182

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 414.43 -0.14 414.43 0.40 0.75 691.68

 MEAN 17.06 0.00 -0.02 414.43 -0.14 414.43 0.40 0.66

 HUB 12.51 0.00 -0.02 414.43 -0.14 414.43 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.60 50.47 7.13 652.87 773.42 4.63 448.28 452.56 2.90

 MEAN 52.50 47.20 5.30 539.89 680.73 4.63 448.28 452.56 2.90

 HUB 43.70 38.62 5.08 395.90 573.23 4.63 448.28 452.56 2.90

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 646.00 361.07 535.67 1051.69 0.61 7.29 6.52 16.04

 MEAN 18.04 681.40 402.31 549.97 1046.30 0.65 7.43 6.80 12.53

 HUB 15.00 786.86 532.27 579.51 1036.34 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.87 609.99 291.79 0.58 7451.89 0.92 0.91

 MEAN 570.78 575.19 168.47 0.55 7258.43 0.92 0.91 0.91 1.31

 HUB 474.70 582.36 57.58 0.56 7985.90 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.22 500.02 1.08 466.46 477.22 1.52

 MEAN 6.67 1.29 5.03 499.04 1.08 461.70 476.72 1.82

 HUB 6.84 1.32 4.69 502.74 1.09 452.95 479.12 2.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.98 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.19 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.57 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 722.2761 401.5242 600.3841 1042.8372 0.6926 -0.0776 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7220 4.8957 458.6449 477.6890 2.0783 33.7738 35.4000 1.6262

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 569.4250 139.2987 552.1238 1060.7289 0.5368 0.3027 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6906 5.5121 474.5242 477.3631 554.9116 0.0278 0.4159

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 565.4493 0.0000 565.4493 1061.1149 0.5329 0.3348 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5070 474.8890 477.3253 0.0000 0.0600 0.0418 0.2999

NASA/TM—2013-218094 H–103
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 6.6660 1.2901 500.5993 38.5102 221.4025 1.7163

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 239451.484 0.562 902.674 740104.250 0.579543E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.267 EfDer = 1.000 SH = 0.674552E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.709 3626.421 6.666 500.599 1.000 1.000 0.980

 W Kg/sec = 30.322 Wdry = 66.704 WH2O = 0.004 lbm/sec H2O = 0.035g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.517 3691.402 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124277.852 52341.402 1.396 590.487 423.036 468.502 1.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 505.12 -0.17 505.12 0.47 0.77 661.97

 MEAN 18.08 0.00 -0.02 505.12 -0.17 505.12 0.47 0.72

 HUB 15.21 0.00 -0.02 505.12 -0.17 505.12 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.17 46.36 5.81 650.34 823.59 5.73 480.08 477.31 1.13

 MEAN 48.57 42.30 6.27 572.11 763.32 5.73 480.08 477.31 1.13

 HUB 43.63 37.84 5.79 481.34 697.86 5.73 480.08 477.31 1.13

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 578.97 291.00 500.53 1093.04 0.53 2.33 2.04 9.02

 MEAN 18.01 594.24 305.71 509.57 1089.06 0.55 2.40 2.13 7.35

 HUB 15.22 647.22 386.33 519.27 1085.37 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 646.22 613.77 355.23 0.56 5945.71 0.92 0.91

 MEAN 569.95 574.01 264.24 0.53 5509.01 0.92 0.91 0.91 1.44

 HUB 481.75 527.96 95.42 0.49 5883.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.71 530.86 1.06 503.90 493.28 0.52

 MEAN 7.99 1.20 6.54 528.63 1.06 500.24 492.20 0.58

 HUB 8.08 1.21 6.37 530.54 1.06 496.86 493.19 0.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.17 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 30.96 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.65 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 663.4968 306.5702 588.4239 1082.8969 0.6127 -0.1840 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0429 6.2613 494.6186 492.9309 0.7031 27.5196 30.6000 3.0804

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 555.2404 117.7149 542.6188 1094.4501 0.5073 0.1319 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0184 6.7410 505.2248 492.7729 491.5697 0.0262 0.2902

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 580.8914 0.0000 580.8914 1091.8911 0.5320 0.1958 0.5911

NASA/TM—2013-218094 H–104
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6102 502.8837 492.7574 0.0000 0.0600 0.0407 0.0457

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8765 7.9963 1.1996 530.0098 29.4122 252.0497 1.9539

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182945.813 0.438 689.661 664989.000 0.713650E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.458 EfDer = 1.000 SH = 0.776016E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.709 3626.421 7.996 530.009 1.000 1.000 0.980

 W Kg/sec = 30.322 Wdry = 66.703 WH2O = 0.005 lbm/sec H2O = 0.046g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.964 3587.521 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107630.617 52341.188 1.503 545.479 362.887 424.468 1.170

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 473.55 -0.16 473.55 0.43 0.72 628.31

 MEAN 17.74 0.00 -0.02 473.55 -0.16 473.55 0.43 0.67

 HUB 15.05 0.00 -0.02 473.55 -0.16 473.55 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.30 46.36 6.94 635.15 792.38 7.05 511.98 492.70 0.45

 MEAN 49.86 43.40 6.46 561.36 734.55 7.05 511.98 492.70 0.45

 HUB 45.17 38.84 6.33 476.28 671.75 7.05 511.98 492.70 0.45

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 555.22 290.20 473.34 1125.67 0.49 2.26 1.98 8.75

 MEAN 17.51 568.77 303.85 480.81 1122.07 0.51 2.34 2.07 6.78

 HUB 14.85 618.69 379.21 488.85 1118.71 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 626.92 580.89 336.72 0.52 5752.15 0.92 0.91 

 MEAN 554.02 542.00 250.17 0.48 5322.20 0.92 0.91 0.91 1.47

 HUB 469.95 497.20 90.74 0.44 5633.67 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.56 1.20 8.11 559.27 1.06 534.49 506.18 0.24

 MEAN 9.44 1.18 7.93 557.09 1.05 531.08 505.23 0.27

 HUB 9.53 1.19 7.76 558.67 1.05 527.90 505.96 0.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.51 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.29 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.80 10.52 6.50 4.02 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 629.6006 305.8401 550.3260 1117.1680 0.5636 -0.1680 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4911 7.6708 526.4857 505.7970 0.3061 29.0628 31.5000 2.4372

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.0481 115.8446 518.2587 1126.8822 0.4713 0.1365 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4701 8.1494 535.6777 505.6934 451.3937 0.0233 0.3139

 

NASA/TM—2013-218094 H–105
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 541.9781 0.0000 541.9781 1125.8671 0.4814 0.2232 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0770 534.7369 505.6586 0.0000 0.0600 0.0386 0.0905

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 9.4461 1.1813 558.3417 28.3340 241.1620 1.8695

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176300.547 0.449 664.610 636311.813 0.833251E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.779 EfDer = 1.000 SH = 0.935676E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.709 3626.421 9.446 558.341 1.000 1.000 0.980

 W Kg/sec = 30.322 Wdry = 66.702 WH2O = 0.006 lbm/sec H2O = 0.064g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.706 3495.315 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94453.492 52340.863 1.628 513.330 315.313 395.845 1.255

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 441.60 -0.15 441.60 0.39 0.66 587.46

 MEAN 16.97 0.00 -0.02 441.60 -0.15 441.60 0.39 0.61

 HUB 14.32 0.00 -0.02 441.60 -0.15 441.60 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.08 46.36 7.72 609.51 752.80 8.52 542.67 505.64 0.23

 MEAN 50.58 43.80 6.78 537.06 695.42 8.52 542.67 505.64 0.23

 HUB 45.75 37.84 7.91 453.18 632.87 8.52 542.67 505.64 0.23

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 525.60 281.74 443.71 1155.43 0.45 2.16 1.89 8.34

 MEAN 16.57 535.80 290.29 450.35 1151.88 0.47 2.24 1.97 6.35

 HUB 13.89 579.12 355.12 457.46 1148.52 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 597.49 544.59 315.75 0.47 5322.18 0.92 0.91

 MEAN 524.51 507.61 234.22 0.44 4813.79 0.92 0.91 0.91 1.49

 HUB 439.57 465.19 84.45 0.41 4934.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.06 1.17 9.61 585.41 1.05 563.21 516.86 0.14

 MEAN 10.89 1.15 9.41 582.82 1.04 559.75 515.84 0.16

 HUB 10.93 1.16 9.21 583.44 1.04 556.49 516.10 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.41 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 32.81 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.82 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 577.8166 291.9215 498.6521 1149.0677 0.5029 -0.1168 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9447 9.2290 557.0670 516.2567 0.1671 30.3456 32.4000 2.0544

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 493.7222 110.7274 481.1455 1156.5072 0.4269 0.1594 2.2705

 

NASA/TM—2013-218094 H–106
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9284 9.6568 564.3055 516.1898 432.2457 0.0205 0.3347

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 489.6731 0.0000 489.6731 1156.8101 0.4233 0.2470 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6527 564.6268 516.1437 0.0000 0.0600 0.0381 0.1567

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 10.9012 1.1540 583.8862 25.5468 244.0816 1.8921

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 159028.000 0.445 599.497 629968.000 0.102909E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.92996E-02

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.022 EfDer = 1.000 SH = 0.118128E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.709 3626.421 10.901 583.886 1.000 1.000 0.980

 W Kg/sec = 30.322 Wdry = 66.701 WH2O = 0.008 lbm/sec H2O = 0.090g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.440 3418.001 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 84113.250 52340.363 1.824 509.668 279.425 384.739 1.377

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 396.08 -0.14 396.08 0.34 0.60 546.43

 MEAN 15.91 0.00 -0.02 396.08 -0.14 396.08 0.34 0.55

 HUB 13.07 0.00 -0.02 396.08 -0.14 396.08 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.67 47.36 8.31 579.76 702.26 10.07 571.29 516.14 0.14

 MEAN 51.82 44.80 7.02 503.59 640.80 10.07 571.29 516.14 0.14

 HUB 46.25 38.84 7.41 413.62 572.78 10.07 571.29 516.14 0.14

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.69 280.61 401.31 1182.72 0.41 2.05 1.78 7.43

 MEAN 15.50 493.33 277.60 407.82 1178.69 0.42 2.13 1.86 5.75

 HUB 12.59 525.15 322.20 414.69 1174.81 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 567.74 493.45 287.13 0.42 5036.60 0.92 0.91

 MEAN 490.44 460.02 212.85 0.39 4304.26 0.92 0.91 0.91 1.53

 HUB 398.43 421.64 76.23 0.36 4058.31 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.57 1.15 11.19 609.49 1.04 590.23 525.94 0.10

 MEAN 12.32 1.13 10.94 605.76 1.04 586.22 524.57 0.11

 HUB 12.23 1.12 10.69 604.51 1.04 582.37 524.12 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.96 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.24 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.85 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 548.0867 282.6870 469.5605 1174.8690 0.4665 -0.1952 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3462 10.6563 582.4670 524.8497 0.1163 31.0490 33.0000 1.9510

 

NASA/TM—2013-218094 H–107
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 474.7195 108.4026 462.1769 1180.9292 0.4020 0.0703 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3205 11.0385 588.4915 524.7764 410.5396 0.0379 0.3472

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 460.0695 0.0000 460.0695 1182.0057 0.3892 0.2706 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1136 589.5911 524.7751 0.0000 0.0600 0.0379 0.1226

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8825 12.3205 1.1302 606.5837 22.7012 251.5679 1.9501

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 141387.453 0.439 532.996 641081.563 0.127592E-03

 

Melt Ratio at Stator LE, Throat, TE

 0.63526E-01 0.72301E-01 0.95974E-01

 trTOT = 1.3127 Tt4 = 606.5837 T1 = 462.0905

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 899113.31 3389.4395 179.1194 2.3843 0.8662 5.2972 1.3127 37.3740

NASA/TM—2013-218094 H–108
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.641 EfDer = 0.999 SH = 0.497307E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.563 3597.110 5.167 462.090 1.000 1.000 0.980

 W Kg/sec = 29.802 Wdry = 65.560 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 176.045 3811.061 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140668.266 51443.359 1.614 831.557 515.311 619.754 1.203

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 405.99 -0.14 405.99 0.39 0.74 686.09

 MEAN 17.06 0.00 -0.02 405.99 -0.14 405.99 0.39 0.65

 HUB 12.51 0.00 -0.02 405.99 -0.14 405.99 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.92 50.47 7.45 647.59 764.45 4.65 448.83 452.55 2.85

 MEAN 52.84 47.20 5.64 535.53 672.14 4.65 448.83 452.55 2.85

 HUB 44.06 38.62 5.44 392.70 564.93 4.65 448.83 452.55 2.85

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 637.10 362.14 524.17 1052.50 0.61 7.29 6.52 16.04

 MEAN 18.04 671.32 401.39 538.11 1047.11 0.64 7.43 6.80 12.53

 HUB 15.00 773.45 527.08 566.04 1037.44 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.59 596.86 285.45 0.57 7473.78 0.92 0.91 

 MEAN 566.16 562.77 164.78 0.54 7241.78 0.92 0.91 0.91 1.33

 HUB 470.86 568.83 56.22 0.55 7907.94 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 499.83 1.08 467.18 477.10 1.49

 MEAN 6.65 1.29 5.06 498.66 1.08 462.41 476.49 1.79

 HUB 6.80 1.32 4.72 502.02 1.09 453.91 478.68 2.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.64 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.72 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.96 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 710.3480 400.6056 586.6085 1043.9047 0.6805 -0.0748 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7045 4.9347 459.5856 477.4208 2.0241 34.3299 35.4000 1.0701

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 557.0417 136.2694 540.1168 1061.4962 0.5248 0.3121 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6755 5.5459 475.2123 477.1132 554.9116 0.0270 0.4232

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 552.9229 0.0000 552.9229 1061.8872 0.5207 0.3438 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5432 475.5817 477.0807 0.0000 0.0600 0.0398 0.3105

NASA/TM—2013-218094 H–109
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8772 6.6536 1.2876 500.1653 38.0763 219.2196 1.6994

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 236755.875 0.565 877.193 725038.000 0.586584E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.627 EfDer = 1.000 SH = 0.685497E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.563 3597.110 6.654 500.165 1.000 1.000 0.980

 W Kg/sec = 29.802 Wdry = 65.559 WH2O = 0.004 lbm/sec H2O = 0.036g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.241 3663.153 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121723.406 51442.973 1.418 590.487 416.374 468.502 1.125

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 494.74 -0.17 494.74 0.46 0.76 656.90

 MEAN 18.08 0.00 -0.02 494.74 -0.17 494.74 0.46 0.71

 HUB 15.21 0.00 -0.02 494.74 -0.17 494.74 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.52 46.36 6.16 645.08 813.09 5.75 480.48 477.07 1.14

 MEAN 48.93 42.30 6.63 567.49 753.00 5.75 480.48 477.07 1.14

 HUB 43.99 37.84 6.15 477.45 687.67 5.75 480.48 477.07 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 571.52 292.89 490.77 1093.26 0.52 2.33 2.04 9.02

 MEAN 18.01 586.15 306.40 499.70 1089.24 0.54 2.40 2.13 7.35

 HUB 15.22 638.07 384.44 509.26 1085.51 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 641.00 601.70 348.11 0.55 5984.26 0.92 0.91

 MEAN 565.34 562.81 258.95 0.52 5521.25 0.92 0.91 0.91 1.45

 HUB 477.86 517.76 93.42 0.48 5854.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.08 1.22 6.73 530.37 1.06 504.11 493.06 0.53

 MEAN 7.97 1.20 6.56 528.04 1.06 500.41 491.92 0.59

 HUB 8.05 1.21 6.39 529.72 1.06 496.98 492.81 0.66

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.83 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.52 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.05 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 652.8002 307.2556 575.9706 1083.4402 0.6025 -0.1790 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0196 6.2932 495.1156 492.6302 0.7048 28.0780 30.6000 2.5220

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 543.6786 115.2637 531.3198 1094.8674 0.4966 0.1446 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9974 6.7714 505.6114 492.4792 491.5697 0.0250 0.2984

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 568.2239 0.0000 568.2239 1092.4708 0.5201 0.2059 0.5911

NASA/TM—2013-218094 H–110
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6486 503.4190 492.4658 0.0000 0.0600 0.0388 0.0614

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 7.9771 1.1989 529.3747 29.2112 248.7049 1.9279

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 181696.156 0.442 673.194 651088.438 0.726518E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.780 EfDer = 1.000 SH = 0.791765E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.563 3597.110 7.977 529.374 1.000 1.000 0.980

 W Kg/sec = 29.802 Wdry = 65.558 WH2O = 0.005 lbm/sec H2O = 0.047g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.055 3560.658 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105547.398 51442.766 1.527 545.479 357.301 424.468 1.188 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 464.39 -0.16 464.39 0.42 0.71 623.61

 MEAN 17.74 0.00 -0.02 464.39 -0.16 464.39 0.42 0.66

 HUB 15.05 0.00 -0.02 464.39 -0.16 464.39 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.61 46.36 7.25 630.01 782.80 7.07 512.04 492.42 0.46

 MEAN 50.18 43.40 6.78 556.82 725.18 7.07 512.04 492.42 0.46

 HUB 45.50 38.84 6.66 472.43 662.57 7.07 512.04 492.42 0.46

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 548.50 291.50 464.63 1125.52 0.49 2.26 1.98 8.75

 MEAN 17.51 561.47 304.10 471.98 1121.89 0.50 2.34 2.07 6.78

 HUB 14.85 610.39 377.17 479.91 1118.49 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 621.85 570.10 330.35 0.51 5777.77 0.92 0.91

 MEAN 549.54 531.99 245.44 0.47 5326.57 0.92 0.91 0.91 1.48

 HUB 466.15 488.09 88.98 0.44 5603.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.53 1.19 8.12 558.53 1.06 534.35 505.88 0.25

 MEAN 9.40 1.18 7.94 556.25 1.05 530.91 504.90 0.28

 HUB 9.48 1.19 7.76 557.65 1.05 527.70 505.54 0.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.10 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.79 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.16 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 620.3490 306.0950 539.5727 1117.2365 0.5553 -0.1643 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4577 7.6903 526.5505 505.4506 0.3128 29.5659 31.5000 1.9341

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 520.7269 113.5931 508.1861 1126.8895 0.4621 0.1480 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4385 8.1684 535.6856 505.3504 451.3937 0.0225 0.3210

 

NASA/TM—2013-218094 H–111
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 531.2872 0.0000 531.2872 1125.9269 0.4719 0.2312 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0990 534.7944 505.3166 0.0000 0.0600 0.0379 0.1026

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 9.4150 1.1803 557.4770 28.1044 238.3357 1.8476

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 174872.625 0.452 647.912 623803.938 0.851785E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.061 EfDer = 1.000 SH = 0.958072E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.563 3597.110 9.415 557.477 1.000 1.000 0.980

 W Kg/sec = 29.802 Wdry = 65.557 WH2O = 0.006 lbm/sec H2O = 0.065g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.124 3469.751 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 92753.508 51442.430 1.652 513.330 310.681 395.845 1.274

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 433.65 -0.15 433.65 0.38 0.66 583.16

 MEAN 16.97 0.00 -0.02 433.65 -0.15 433.65 0.38 0.61

 HUB 14.32 0.00 -0.02 433.65 -0.15 433.65 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.36 46.36 8.00 604.59 744.15 8.52 542.37 505.30 0.24

 MEAN 50.86 43.80 7.06 532.72 687.03 8.52 542.37 505.30 0.24

 HUB 46.04 37.84 8.20 449.51 624.70 8.52 542.37 505.30 0.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 519.57 282.44 436.10 1154.91 0.45 2.16 1.89 8.34

 MEAN 16.57 529.26 290.18 442.62 1151.35 0.46 2.24 1.97 6.35

 HUB 13.89 571.68 353.09 449.61 1147.98 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 592.66 535.18 310.22 0.46 5335.36 0.92 0.91

 MEAN 520.27 498.85 230.09 0.43 4811.94 0.92 0.91 0.91 1.50

 HUB 436.02 457.19 82.92 0.40 4906.59 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.01 1.17 9.60 584.39 1.05 562.70 516.50 0.15

 MEAN 10.85 1.15 9.40 581.75 1.04 559.24 515.45 0.16

 HUB 10.88 1.16 9.20 582.23 1.04 555.97 515.66 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.93 35.43 31.50 3.93 0.93 0.42 1.40

 MEAN 33.25 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.14 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 570.1380 291.8116 489.7993 1148.6647 0.4963 -0.1147 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8967 9.2280 556.6755 515.8603 0.1733 30.7856 32.4000 1.6144

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 484.9305 108.7557 472.5778 1156.0891 0.4195 0.1689 2.2705

 

NASA/TM—2013-218094 H–112
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8817 9.6562 563.8972 515.7952 432.2457 0.0199 0.3410

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 480.9526 0.0000 480.9526 1156.3806 0.4159 0.2540 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6518 564.2071 515.7505 0.0000 0.0600 0.0375 0.1660

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8817 10.8552 1.1530 582.7866 25.3119 241.5880 1.8728

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 157565.813 0.449 583.790 618264.313 0.105457E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.10646E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.263 EfDer = 1.000 SH = 0.120875E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.563 3597.110 10.855 582.786 1.000 1.000 0.980

 W Kg/sec = 29.802 Wdry = 65.556 WH2O = 0.008 lbm/sec H2O = 0.092g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.111 3393.572 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 82713.867 51441.922 1.850 509.668 275.532 384.739 1.396

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 389.49 -0.13 389.49 0.33 0.60 542.52

 MEAN 15.91 0.00 -0.02 389.49 -0.13 389.49 0.33 0.54

 HUB 13.07 0.00 -0.02 389.49 -0.13 389.49 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.90 47.36 8.54 575.08 694.68 10.05 570.60 515.75 0.15

 MEAN 52.06 44.80 7.26 499.52 633.53 10.05 570.60 515.75 0.15

 HUB 46.50 38.84 7.66 410.28 565.81 10.05 570.60 515.75 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 484.53 280.68 394.95 1181.82 0.41 2.05 1.78 7.43

 MEAN 15.50 487.70 277.13 401.31 1177.82 0.41 2.13 1.86 5.75

 HUB 12.59 518.71 320.26 408.03 1173.96 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 563.15 485.57 282.47 0.41 5037.83 0.92 0.91

 MEAN 486.48 452.64 209.35 0.38 4296.98 0.92 0.91 0.91 1.54

 HUB 395.21 414.86 74.95 0.35 4033.85 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.51 1.15 11.16 608.18 1.04 589.33 525.51 0.10

 MEAN 12.25 1.13 10.91 604.45 1.04 585.35 524.13 0.11

 HUB 12.17 1.12 10.66 603.12 1.03 581.52 523.64 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.40 35.57 31.50 4.07 0.93 0.44 1.40

 MEAN 34.63 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.13 10.41 6.50 3.91 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 541.1706 282.2110 461.7603 1174.1355 0.4609 -0.1929 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2815 10.6370 581.7374 524.4024 0.1212 31.4317 33.0000 1.5683

 

NASA/TM—2013-218094 H–113
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 466.7558 106.5841 454.4236 1180.1962 0.3955 0.0804 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2577 11.0205 587.7590 524.3317 410.5396 0.0370 0.3526

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 452.4622 0.0000 452.4622 1181.2286 0.3830 0.2766 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0919 588.8140 524.3295 0.0000 0.0600 0.0374 0.1314

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8831 12.2570 1.1291 605.2493 22.4665 249.3876 1.9332

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 139924.703 0.441 518.428 629820.250 0.130511E-03

 

Melt Ratio at Stator LE, Throat, TE

0.64793E-01 0.73608E-01 0.97299E-01

 trTOT = 1.3098 Tt4 = 605.2493 T1 = 462.0904

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 890815.13 3300.5173 176.0450 2.3720 0.8684 5.6411 1.3098 37.3740

NASA/TM—2013-218094 H–114
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.977 EfDer = 0.999 SH = 0.500823E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.431 3567.207 5.167 462.090 1.000 1.000 0.980

 W Kg/sec = 29.287 Wdry = 64.428 WH2O = 0.003 lbm/sec H2O = 0.023g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 173.004 3779.379 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 137808.578 50554.750 1.642 831.557 506.411 619.754 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 397.74 -0.14 397.74 0.39 0.73 680.38

 MEAN 17.06 0.00 -0.02 397.74 -0.14 397.74 0.39 0.64

 HUB 12.51 0.00 -0.02 397.74 -0.14 397.74 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.23 50.47 7.76 642.21 755.51 4.67 449.37 452.55 2.81

 MEAN 53.18 47.20 5.98 531.08 663.61 4.67 449.37 452.55 2.81

 HUB 44.41 38.62 5.79 389.43 556.74 4.67 449.37 452.55 2.81

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 628.46 362.85 513.13 1053.22 0.60 7.29 6.52 16.04

 MEAN 18.04 661.52 400.26 526.69 1047.84 0.63 7.43 6.80 12.53

 HUB 15.00 760.48 521.89 553.14 1038.44 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 642.21 584.24 279.35 0.55 7488.48 0.92 0.91

 MEAN 561.46 550.80 161.20 0.53 7221.35 0.92 0.91 0.91 1.34

 HUB 466.95 555.87 54.94 0.54 7830.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 499.59 1.08 467.82 476.95 1.47

 MEAN 6.64 1.28 5.09 498.25 1.08 463.05 476.24 1.76

 HUB 6.77 1.31 4.76 501.30 1.08 454.78 478.24 2.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.27 28.56 24.20 4.36 0.93 0.36 1.80

 MEAN 37.23 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.33 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 698.8624 399.4778 573.4337 1044.8633 0.6689 -0.0724 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6855 4.9700 460.4312 477.1411 1.9791 34.8627 35.4000 0.5373

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 545.2269 133.3791 528.6609 1062.1549 0.5133 0.3208 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6585 5.5752 475.8034 476.8494 554.9116 0.0263 0.4302

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 541.0205 0.0000 541.0205 1062.5455 0.5092 0.3522 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5742 476.1725 476.8210 0.0000 0.0600 0.0382 0.3202

NASA/TM—2013-218094 H–115
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8798 6.6388 1.2848 499.7089 37.6201 217.1292 1.6832

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 233920.625 0.567 851.718 710298.375 0.593300E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.965 EfDer = 1.000 SH = 0.696226E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.431 3567.207 6.639 499.708 1.000 1.000 0.980

 W Kg/sec = 29.287 Wdry = 64.427 WH2O = 0.004 lbm/sec H2O = 0.036g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.031 3634.360 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 119279.008 50554.363 1.441 590.487 409.907 468.502 1.143

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 484.80 -0.17 484.80 0.45 0.75 651.74

 MEAN 18.08 0.00 -0.02 484.80 -0.17 484.80 0.45 0.70

 HUB 15.21 0.00 -0.02 484.80 -0.17 484.80 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.85 46.36 6.49 639.72 802.80 5.77 480.81 476.82 1.14

 MEAN 49.26 42.30 6.97 562.77 742.92 5.77 480.81 476.82 1.14

 HUB 44.33 37.84 6.49 473.48 677.77 5.77 480.81 476.82 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 564.34 294.30 481.52 1093.36 0.52 2.33 2.04 9.02

 MEAN 18.01 578.35 306.74 490.30 1089.32 0.53 2.40 2.13 7.35

 HUB 15.22 629.22 382.37 499.71 1085.55 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.67 590.25 341.37 0.54 6013.09 0.92 0.91

 MEAN 560.65 552.15 253.91 0.51 5527.34 0.92 0.91 0.91 1.46

 HUB 473.89 508.02 91.52 0.47 5823.29 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.21 6.74 529.81 1.06 504.20 492.79 0.54

 MEAN 7.94 1.20 6.57 527.38 1.06 500.48 491.61 0.60

 HUB 8.01 1.21 6.40 528.86 1.06 497.03 492.39 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.43 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.03 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.42 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 642.6294 307.5981 564.2303 1083.8396 0.5929 -0.1746 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9915 6.3179 495.4812 492.2968 0.7090 28.5976 30.6000 2.0024

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 532.8276 112.9632 520.7154 1095.1320 0.4865 0.1560 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9712 6.7932 505.8569 492.1517 491.5697 0.0241 0.3057

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 556.5084 0.0000 556.5084 1092.8665 0.5092 0.2141 0.5911

NASA/TM—2013-218094 H–116
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6762 503.7846 492.1378 0.0000 0.0600 0.0380 0.0746

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 7.9513 1.1977 528.6808 28.9737 245.6466 1.9042

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180220.078 0.446 656.191 637613.438 0.739079E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.069 EfDer = 1.000 SH = 0.806936E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.431 3567.207 7.951 528.680 1.000 1.000 0.980

 W Kg/sec = 29.287 Wdry = 64.426 WH2O = 0.005 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.258 3533.374 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 103600.094 50554.148 1.549 545.479 352.040 424.468 1.206

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 455.82 -0.16 455.82 0.41 0.70 618.83

 MEAN 17.74 0.00 -0.02 455.82 -0.16 455.82 0.41 0.65

 HUB 15.05 0.00 -0.02 455.82 -0.16 455.82 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.89 46.36 7.53 624.77 773.51 7.08 511.98 492.09 0.47

 MEAN 50.47 43.40 7.07 552.19 716.15 7.08 511.98 492.09 0.47

 HUB 45.80 38.84 6.96 468.50 653.77 7.08 511.98 492.09 0.47

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 542.06 292.19 456.57 1125.20 0.48 2.26 1.98 8.75

 MEAN 17.51 554.50 303.91 463.80 1121.57 0.49 2.34 2.07 6.78

 HUB 14.85 602.49 374.97 471.59 1118.15 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 616.68 560.13 324.49 0.50 5791.50 0.92 0.91

 MEAN 544.97 522.71 241.06 0.47 5323.26 0.92 0.91 0.91 1.49

 HUB 462.28 479.60 87.31 0.43 5570.66 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.49 1.19 8.12 557.66 1.05 534.04 505.53 0.26

 MEAN 9.36 1.18 7.94 555.32 1.05 530.60 504.51 0.28

 HUB 9.43 1.19 7.76 556.56 1.05 527.38 505.09 0.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.62 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.24 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.49 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 611.6456 305.9076 529.6516 1117.1273 0.5475 -0.1612 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4141 7.6975 526.4473 505.0501 0.3205 30.0092 31.5000 1.4908

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 511.2688 111.5298 498.9557 1126.6995 0.4538 0.1578 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.3963 8.1730 535.5052 504.9527 451.3937 0.0219 0.3273

 

NASA/TM—2013-218094 H–117
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 521.5078 0.0000 521.5078 1125.7820 0.4632 0.2381 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1063 534.6569 504.9198 0.0000 0.0600 0.0374 0.1130

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 9.3733 1.1788 556.5120 27.8333 235.8721 1.8285

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 173186.094 0.455 630.580 611708.063 0.869558E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.304 EfDer = 1.000 SH = 0.979396E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.431 3567.207 9.373 556.512 1.000 1.000 0.980

 W Kg/sec = 29.287 Wdry = 64.425 WH2O = 0.006 lbm/sec H2O = 0.067g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.665 3443.889 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91187.086 50553.805 1.675 513.330 306.411 395.845 1.292

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 426.33 -0.15 426.33 0.38 0.65 578.82

 MEAN 16.97 0.00 -0.02 426.33 -0.15 426.33 0.38 0.60

 HUB 14.32 0.00 -0.02 426.33 -0.15 426.33 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.59 46.36 8.23 599.56 735.80 8.51 541.91 504.90 0.25

 MEAN 51.10 43.80 7.30 528.29 678.98 8.51 541.91 504.90 0.25

 HUB 46.29 37.84 8.45 445.78 616.93 8.51 541.91 504.90 0.25

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 513.83 282.57 429.16 1154.19 0.45 2.16 1.89 8.34

 MEAN 16.57 523.07 289.65 435.55 1150.65 0.45 2.24 1.97 6.35

 HUB 13.89 564.66 350.90 442.40 1147.27 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 587.73 526.60 305.16 0.46 5337.69 0.92 0.91

 MEAN 515.94 490.83 226.30 0.43 4803.04 0.92 0.91 0.91 1.50

 HUB 432.39 449.84 81.49 0.39 4876.10 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.95 1.17 9.58 583.21 1.05 562.00 516.06 0.15

 MEAN 10.79 1.15 9.38 580.54 1.04 558.55 514.99 0.17

 HUB 10.81 1.15 9.18 580.90 1.04 555.28 515.16 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.36 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.62 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 38.42 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 562.9362 291.2742 481.7224 1148.0660 0.4903 -0.1130 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8342 9.2110 556.0938 515.3956 0.1801 31.1593 32.4000 1.2407

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 476.9647 106.9692 464.8149 1155.4529 0.4128 0.1768 2.2705

 

NASA/TM—2013-218094 H–118
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8202 9.6372 563.2755 515.3317 432.2457 0.0195 0.3462

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 473.0550 0.0000 473.0550 1155.7343 0.4093 0.2598 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6327 563.5751 515.2883 0.0000 0.0600 0.0371 0.1737

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8822 10.7943 1.1516 581.5494 25.0397 239.4826 1.8565

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 155870.922 0.451 567.534 606952.313 0.107882E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.11460E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.462 EfDer = 0.999 SH = 0.123533E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.431 3567.207 10.794 581.549 1.000 1.000 0.980

 W Kg/sec = 29.287 Wdry = 64.423 WH2O = 0.008 lbm/sec H2O = 0.094g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.908 3368.938 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 81440.305 50553.297 1.874 509.668 272.012 384.739 1.414

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 383.50 -0.13 383.50 0.33 0.59 538.58

 MEAN 15.91 0.00 -0.02 383.50 -0.13 383.50 0.33 0.54

 HUB 13.07 0.00 -0.02 383.50 -0.13 383.50 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.09 47.36 8.73 570.30 687.36 10.02 569.74 515.29 0.16

 MEAN 52.26 44.80 7.46 495.37 626.57 10.02 569.74 515.29 0.16

 HUB 46.70 38.84 7.86 406.87 559.21 10.02 569.74 515.29 0.16

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 479.57 280.17 389.22 1180.71 0.41 2.05 1.78 7.43

 MEAN 15.50 482.35 276.21 395.43 1176.74 0.41 2.13 1.86 5.75

 HUB 12.59 512.64 318.13 401.99 1172.91 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 558.47 478.48 278.30 0.41 5028.63 0.92 0.91

 MEAN 482.44 445.98 206.22 0.38 4282.73 0.92 0.91 0.91 1.55

 HUB 391.92 408.71 73.80 0.35 4006.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.42 1.15 11.11 606.69 1.04 588.22 524.99 0.11

 MEAN 12.17 1.13 10.86 602.96 1.04 584.28 523.61 0.12

 HUB 12.08 1.12 10.61 601.58 1.03 580.48 523.10 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.75 35.57 31.50 4.07 0.93 0.45 1.40

 MEAN 34.93 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.36 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 534.6923 281.2770 454.7297 1173.1816 0.4558 -0.1909 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.1977 10.5976 580.7891 523.8748 0.1266 31.7392 33.0000 1.2608

 

NASA/TM—2013-218094 H–119
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 459.6380 104.9587 447.4938 1179.2167 0.3898 0.0883 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1755 10.9795 586.7806 523.8063 410.5396 0.0363 0.3568

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 445.6555 0.0000 445.6555 1180.2114 0.3776 0.2813 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0477 587.7970 523.8033 0.0000 0.0600 0.0371 0.1382

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8835 12.1743 1.1278 603.7416 22.1959 247.6451 1.9197

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 138238.250 0.443 503.333 618927.188 0.133362E-03

 

Melt Ratio at Stator LE, Throat, TE

0.65233E-01 0.74029E-01 0.97620E-01

 trTOT = 1.3065 Tt4 = 603.7416 T1 = 462.0903

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 881435.94 3209.3562 173.0041 2.3560 0.8700 5.9767 1.3065 37.3740

NASA/TM—2013-218094 H–120
 25μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.969 EfDer = 0.985 SH = 0.114976E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 5.167 482.271 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.921 WH2O = 0.009 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.801 4120.825 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171010.438 58006.203 1.401 831.557 593.652 619.754 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 493.56 -0.17 493.56 0.47 0.83 741.85

 MEAN 17.06 0.00 -0.02 493.56 -0.17 493.56 0.47 0.74

 HUB 12.51 0.00 -0.02 493.56 -0.17 493.56 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.40 50.47 4.93 715.35 869.24 4.45 462.68 465.30 3.25

 MEAN 50.17 47.20 2.97 591.57 770.56 4.45 462.68 465.30 3.25

 HUB 41.32 38.62 2.70 433.79 657.21 4.45 462.68 465.30 3.25

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 741.37 362.70 646.58 1066.64 0.70 7.29 6.52 16.04

 MEAN 18.04 787.07 421.49 664.70 1061.12 0.74 7.43 6.80 12.53

 HUB 15.00 928.87 591.96 715.81 1047.12 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.35 736.50 352.65 0.69 7486.10 0.92 0.90

 MEAN 625.41 695.28 203.92 0.66 7604.87 0.92 0.90 0.90 1.21

 HUB 520.13 719.40 71.83 0.69 8881.49 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 524.02 1.09 479.82 488.58 1.80

 MEAN 6.81 1.32 4.75 524.68 1.09 474.87 489.10 2.15

 HUB 7.12 1.38 4.29 531.80 1.10 462.42 493.50 3.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.29 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.38 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.59 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 849.9094 420.6696 738.5005 1054.2638 0.8062 -0.1057 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8831 4.5082 468.7473 490.4814 2.7130 29.6670 35.4000 5.7330

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 691.5118 169.1649 670.5012 1076.1078 0.6426 0.2318 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8130 5.1774 488.3825 489.5546 554.9116 0.0412 0.3616

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 692.9905 0.0000 692.9905 1075.9021 0.6441 0.2576 1.3089

NASA/TM—2013-218094 H–121
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1200 488.2229 489.4227 0.0000 0.0600 0.0711 0.2063

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8263 6.7456 1.3055 526.8323 44.5619 237.2687 1.8393

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 277116.969 0.542 1157.747 817600.875 0.128803E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.618 EfDer = 0.990 SH = 0.143046E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 6.746 526.832 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.919 WH2O = 0.011 lbm/sec H2O = 0.068g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.364 3942.716 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 149419.844 58005.563 1.242 590.487 475.303 468.502 0.986

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 607.31 -0.21 607.31 0.56 0.86 707.04

 MEAN 18.08 0.00 -0.02 607.31 -0.21 607.31 0.56 0.80

 HUB 15.21 0.00 -0.02 607.31 -0.21 607.31 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.57 46.36 3.21 712.58 936.42 5.47 497.18 489.28 1.14

 MEAN 45.92 42.30 3.62 626.87 872.95 5.47 497.18 489.28 1.14

 HUB 40.98 37.84 3.14 527.41 804.49 5.47 497.18 489.28 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 660.13 282.82 596.47 1114.63 0.59 2.33 2.04 9.02

 MEAN 18.01 680.22 308.30 606.34 1111.00 0.61 2.40 2.13 7.35

 HUB 15.22 742.59 412.91 617.20 1107.74 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.07 732.54 425.25 0.66 5779.52 0.92 0.91

 MEAN 624.50 683.83 316.20 0.62 5556.27 0.92 0.91 0.91 1.37

 HUB 527.86 627.82 114.96 0.57 6288.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.20 1.22 6.49 559.05 1.06 524.02 503.64 0.51

 MEAN 8.14 1.21 6.34 557.81 1.06 520.61 503.15 0.56

 HUB 8.34 1.24 6.19 561.89 1.07 517.56 504.97 0.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.37 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 26.95 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.78 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 778.8822 309.1667 714.8940 1100.4677 0.7078 -0.2337 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2084 5.8989 510.8253 504.0860 0.7459 23.3868 30.6000 7.2132

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 672.3079 142.5341 657.0251 1113.7885 0.6036 0.0268 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1502 6.3903 523.2526 503.7094 491.5697 0.0408 0.2245

 

NASA/TM—2013-218094 H–122
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 714.9500 0.0000 714.9500 1108.6941 0.6449 0.1032 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1372 518.5026 503.6655 0.0000 0.0600 0.0724 -0.1073

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8276 8.0907 1.1994 559.5821 32.7515 279.2954 2.1651

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 203777.172 0.406 851.346 740021.500 0.148649E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.993 EfDer = 0.992 SH = 0.157590E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 8.091 559.582 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.918 WH2O = 0.012 lbm/sec H2O = 0.087g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.516 3825.601 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 128622.125 58005.234 1.336 545.479 408.441 424.468 1.039 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 565.91 -0.19 565.91 0.50 0.80 670.01

 MEAN 17.74 0.00 -0.02 565.91 -0.19 565.91 0.50 0.74

 HUB 15.05 0.00 -0.02 565.91 -0.19 565.91 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.89 46.36 4.53 695.93 897.14 6.82 533.85 503.46 0.41

 MEAN 47.39 43.40 3.99 615.09 835.96 6.82 533.85 503.46 0.41

 HUB 42.69 38.84 3.85 521.86 769.94 6.82 533.85 503.46 0.41

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 630.01 285.92 561.39 1151.43 0.55 2.26 1.98 8.75

 MEAN 17.51 648.14 309.11 569.68 1148.06 0.56 2.34 2.07 6.78

 HUB 14.85 707.10 406.18 578.81 1144.99 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 689.90 401.00 0.60 5667.99 0.92 0.91

 MEAN 607.05 642.88 297.93 0.56 5414.96 0.92 0.91 0.91 1.40

 HUB 514.93 588.93 108.75 0.51 6034.66 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.70 1.20 7.93 591.17 1.06 559.27 515.92 0.22

 MEAN 9.62 1.19 7.77 589.76 1.05 556.00 515.42 0.24

 HUB 9.81 1.21 7.61 593.21 1.06 553.03 516.77 0.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.99 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.48 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 35.06 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 730.3590 311.1412 660.7689 1140.2560 0.6405 -0.2029 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6901 7.3770 548.5259 516.0888 0.2850 25.2147 31.5000 6.2853

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 637.3753 139.0391 622.0253 1150.8380 0.5538 0.0409 2.3726

 

NASA/TM—2013-218094 H–123
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6431 7.8492 558.7398 515.8715 451.3937 0.0342 0.2572

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 654.4291 0.0000 654.4291 1148.9849 0.5696 0.1491 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7219 556.9743 515.7950 0.0000 0.0600 0.0583 -0.0247

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8482 9.5963 1.1861 591.3758 31.7958 264.8535 2.0531

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 197926.875 0.419 826.905 699976.250 0.165407E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.577 EfDer = 0.995 SH = 0.179594E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 9.596 591.375 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.916 WH2O = 0.013 lbm/sec H2O = 0.114g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.921 3721.344 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111872.602 58004.734 1.450 513.330 354.033 395.845 1.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 523.04 -0.18 523.04 0.45 0.73 625.45

 MEAN 16.97 0.00 -0.02 523.04 -0.18 523.04 0.45 0.68

 HUB 14.32 0.00 -0.02 523.04 -0.18 523.04 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.94 46.36 5.58 667.85 848.43 8.37 569.41 515.71 0.19

 MEAN 48.38 43.80 4.58 588.47 787.45 8.37 569.41 515.71 0.19

 HUB 43.52 37.84 5.68 496.55 721.33 8.37 569.41 515.71 0.19

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 593.18 281.97 521.88 1185.30 0.50 2.16 1.89 8.34

 MEAN 16.57 607.72 298.11 529.58 1181.76 0.51 2.24 1.97 6.35

 HUB 13.89 659.39 381.34 537.93 1178.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.67 641.30 372.70 0.54 5327.01 0.92 0.91

 MEAN 574.70 597.46 276.60 0.51 4943.89 0.92 0.91 0.91 1.43

 HUB 481.64 547.20 100.30 0.46 5299.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.28 1.18 9.53 621.04 1.05 592.79 526.39 0.12

 MEAN 11.16 1.16 9.34 618.91 1.05 589.25 525.66 0.13

 HUB 11.28 1.17 9.14 620.89 1.05 585.97 526.38 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.38 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.38 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.33 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 661.9050 299.7860 590.1241 1177.5358 0.5621 -0.1356 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2195 9.0781 585.1064 526.1412 0.1381 26.9308 32.4000 5.4692

 

NASA/TM—2013-218094 H–124
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 584.9426 131.1855 570.0422 1185.2654 0.4935 0.0811 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1851 9.4900 592.8094 526.0141 432.2457 0.0281 0.2866

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 580.2761 0.0000 580.2761 1185.6703 0.4894 0.1902 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4854 593.2487 525.9433 0.0000 0.0600 0.0467 0.0787

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8637 11.1497 1.1619 620.2776 28.9048 265.1896 2.0557

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180042.766 0.420 752.188 685883.063 0.189766E-03

 

Melt Ratio at Stator LE, Throat, TE

0.22326E-01 0.30146E-01 0.49383E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.165 EfDer = 0.998 SH = 0.203628E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 11.150 620.277 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.915 WH2O = 0.015 lbm/sec H2O = 0.147g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.588 3633.612 1.380 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98474.133 58004.184 1.633 509.668 312.097 384.739 1.233

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 463.71 -0.16 463.71 0.39 0.66 580.90

 MEAN 15.91 0.00 -0.02 463.71 -0.16 463.71 0.39 0.60

 HUB 13.07 0.00 -0.02 463.71 -0.16 463.71 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.88 47.36 6.52 635.25 786.62 10.06 603.02 525.90 0.10

 MEAN 49.97 44.80 5.17 551.79 720.88 10.06 603.02 525.90 0.10

 HUB 44.35 38.84 5.51 453.21 648.51 10.06 603.02 525.90 0.10

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 547.90 287.18 466.60 1216.81 0.45 2.05 1.78 7.43

 MEAN 15.50 555.58 288.83 474.60 1212.48 0.46 2.13 1.86 5.75

 HUB 12.59 594.80 347.06 483.05 1208.35 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 574.34 334.89 0.47 5154.96 0.92 0.91

 MEAN 537.38 535.75 248.56 0.44 4478.71 0.92 0.91 0.91 1.47

 HUB 436.56 491.27 89.50 0.41 4371.60 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.96 1.16 11.29 648.96 1.05 624.87 535.53 0.07

 MEAN 12.71 1.14 11.02 645.20 1.04 620.43 534.31 0.08

 HUB 12.67 1.14 10.76 644.61 1.04 616.21 534.14 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.61 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.32 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.70 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 623.7801 294.1259 550.0832 1207.1307 0.5167 -0.2160 2.0437

 

NASA/TM—2013-218094 H–125
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7416 10.6454 615.0401 534.6289 0.0843 28.1331 33.0000 4.8669

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 557.3695 127.2758 542.6432 1213.2960 0.4594 -0.0133 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6900 11.0014 621.3315 534.4940 410.5396 0.0494 0.3069

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 538.7160 0.0000 538.7160 1214.8634 0.4434 0.2239 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1147 622.9728 534.5038 0.0000 0.0600 0.0446 0.0513

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8708 12.6984 1.1389 646.2527 25.9803 269.3834 2.0882

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161940.484 0.418 676.560 690968.938 0.211928E-03

 

Melt Ratio at Stator LE, Throat, TE

0.12172E+00 0.13243E+00 0.16199E+00

 trTOT = 1.3400 Tt4 = 646.2527 T1 = 482.2715

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1020804.25 4264.7456 202.8008 2.4575 0.8275 2.9688 1.3400 37.3740

NASA/TM—2013-218094 H–126
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.316 EfDer = 0.998 SH = 0.120376E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl 

 65.262 3705.060 5.167 482.271 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.254 WH2O = 0.008 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 179.024 3842.429 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146607.906 51205.289 1.587 831.557 524.054 619.754 1.183

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 423.13 -0.15 423.13 0.40 0.75 691.73

 MEAN 17.06 0.00 -0.02 423.13 -0.15 423.13 0.40 0.66

 HUB 12.51 0.00 -0.02 423.13 -0.15 423.13 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.62 50.47 7.15 667.02 790.04 4.63 467.87 465.21 2.80

 MEAN 52.52 47.20 5.32 551.60 695.32 4.63 467.87 465.21 2.80

 HUB 43.72 38.62 5.10 404.48 585.46 4.63 467.87 465.21 2.80

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 659.76 369.15 546.82 1074.45 0.61 7.29 6.52 16.04

 MEAN 18.04 695.89 411.17 561.43 1068.94 0.65 7.43 6.80 12.53

 HUB 15.00 803.52 543.76 591.58 1058.77 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.02 622.69 297.87 0.58 7618.59 0.92 0.91

 MEAN 583.15 587.18 171.98 0.55 7418.41 0.92 0.91 0.91 1.31

 HUB 484.99 594.49 58.77 0.56 8158.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.22 521.88 1.08 486.88 487.37 1.51

 MEAN 6.67 1.29 5.03 520.84 1.08 481.90 486.98 1.79

 HUB 6.84 1.32 4.69 524.69 1.09 472.78 489.34 2.48

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.02 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.22 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.59 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 737.5757 410.3744 612.8709 1065.4132 0.6923 -0.0774 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7227 4.8976 478.7310 487.9099 2.0269 33.8060 35.4000 1.5940

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 581.2339 142.1875 563.5739 1083.6951 0.5363 0.3034 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6914 5.5147 495.3102 487.3918 554.9116 0.0278 0.4164

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 577.1659 0.0000 577.1659 1084.0847 0.5324 0.3354 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5097 495.6920 487.3470 0.0000 0.0600 0.0417 0.3006

NASA/TM—2013-218094 H–127
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8741 6.6669 1.2903 522.4712 40.2020 221.2746 1.7153

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 250031.047 0.562 922.117 700932.563 0.138611E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.292 EfDer = 1.000 SH = 0.158126E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 6.667 522.471 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.252 WH2O = 0.010 lbm/sec H2O = 0.078g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.419 3691.664 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126862.750 51204.535 1.397 590.487 422.776 468.502 1.108

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 515.63 -0.18 515.63 0.47 0.77 662.02

 MEAN 18.08 0.00 -0.02 515.63 -0.18 515.63 0.47 0.72

 HUB 15.21 0.00 -0.02 515.63 -0.18 515.63 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.19 46.36 5.83 664.44 841.18 5.73 501.10 487.32 1.13

 MEAN 48.59 42.30 6.29 584.52 779.58 5.73 501.10 487.32 1.13

 HUB 43.65 37.84 5.81 491.78 712.67 5.73 501.10 487.32 1.13

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 591.28 297.67 510.88 1116.70 0.53 2.33 2.04 9.02

 MEAN 18.01 606.84 312.60 520.13 1112.63 0.55 2.40 2.13 7.35

 HUB 15.22 660.92 394.80 530.05 1108.85 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.23 626.46 362.56 0.56 6082.10 0.92 0.91

 MEAN 582.31 585.90 269.71 0.53 5633.10 0.92 0.91 0.91 1.44

 HUB 492.20 538.92 97.40 0.49 6012.79 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.71 554.08 1.06 525.98 501.82 0.55

 MEAN 7.99 1.20 6.54 551.75 1.06 522.15 500.85 0.61

 HUB 8.09 1.21 6.38 553.72 1.06 518.61 501.79 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.23 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 31.01 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.68 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 677.4536 313.4760 600.5632 1106.3429 0.6123 -0.1836 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0453 6.2652 516.3025 501.5639 0.7211 27.5632 30.6000 3.0368

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 566.6553 120.1349 553.7741 1118.1534 0.5068 0.1330 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0209 6.7457 527.3795 501.3245 491.5697 0.0261 0.2909

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 592.7982 0.0000 592.7982 1115.5443 0.5314 0.1967 0.5911

NASA/TM—2013-218094 H–128
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6153 524.9463 501.3198 0.0000 0.0600 0.0406 0.0470

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8767 7.9990 1.1998 553.1844 30.7150 251.7875 1.9518

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191120.688 0.438 704.855 630043.000 0.165919E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.487 EfDer = 1.000 SH = 0.178012E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 7.999 553.184 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.250 WH2O = 0.012 lbm/sec H2O = 0.102g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.857 3587.719 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109851.781 51204.137 1.504 545.479 362.604 424.468 1.171

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 483.33 -0.17 483.33 0.43 0.72 628.35

 MEAN 17.74 0.00 -0.02 483.33 -0.17 483.33 0.43 0.67

 HUB 15.05 0.00 -0.02 483.33 -0.17 483.33 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.33 46.36 6.97 648.92 809.27 7.06 534.41 501.22 0.47

 MEAN 49.89 43.40 6.49 573.53 750.16 7.06 534.41 501.22 0.47

 HUB 45.20 38.84 6.36 486.61 685.97 7.06 534.41 501.22 0.47

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 567.00 296.89 483.05 1150.03 0.49 2.26 1.98 8.75

 MEAN 17.51 580.80 310.72 490.69 1146.35 0.51 2.34 2.07 6.78

 HUB 14.85 631.75 387.53 498.93 1142.90 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.51 592.80 343.62 0.52 5884.78 0.92 0.91

 MEAN 566.03 553.14 255.32 0.48 5442.51 0.92 0.91 0.91 1.47

 HUB 480.14 507.45 92.61 0.44 5757.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.57 1.20 8.12 583.76 1.06 557.93 513.69 0.26

 MEAN 9.44 1.18 7.94 581.46 1.05 554.36 512.82 0.29

 HUB 9.53 1.19 7.76 583.10 1.05 551.03 513.51 0.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.58 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.34 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.84 10.52 6.50 4.02 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 642.8152 312.7542 561.6015 1141.3477 0.5632 -0.1676 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4957 7.6768 549.5794 513.3654 0.3262 29.1133 31.5000 2.3867

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 541.8835 118.2082 528.8333 1151.2821 0.4707 0.1378 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4749 8.1566 559.1836 513.2144 451.3937 0.0233 0.3147

 

NASA/TM—2013-218094 H–129
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 553.0262 0.0000 553.0262 1150.2433 0.4808 0.2241 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0844 558.2064 513.1807 0.0000 0.0600 0.0386 0.0918

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 9.4509 1.1815 582.7703 29.5879 240.8769 1.8673

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184193.906 0.449 679.309 602994.688 0.188743E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.811 EfDer = 1.000 SH = 0.207102E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 9.451 582.770 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.248 WH2O = 0.014 lbm/sec H2O = 0.135g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.596 3495.462 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96390.492 51203.551 1.629 513.330 315.023 395.845 1.257

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 450.66 -0.16 450.66 0.39 0.66 587.48

 MEAN 16.97 0.00 -0.02 450.66 -0.16 450.66 0.39 0.61

 HUB 14.32 0.00 -0.02 450.66 -0.16 450.66 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.11 46.36 7.75 622.73 768.82 8.53 566.46 513.14 0.24

 MEAN 50.61 43.80 6.81 548.71 710.17 8.53 566.46 513.14 0.24

 HUB 45.78 37.84 7.94 463.00 646.23 8.53 566.46 513.14 0.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 536.74 288.26 452.76 1180.42 0.45 2.16 1.89 8.34

 MEAN 16.57 547.11 296.89 459.55 1176.79 0.46 2.24 1.97 6.35

 HUB 13.89 591.30 362.91 466.83 1173.34 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 610.44 555.69 322.18 0.47 5445.33 0.92 0.91

 MEAN 535.88 517.98 238.99 0.44 4923.26 0.92 0.91 0.91 1.49

 HUB 449.10 474.72 86.19 0.40 5043.10 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.06 1.17 9.62 611.05 1.05 587.91 523.67 0.16

 MEAN 10.90 1.15 9.42 608.33 1.04 584.30 522.71 0.17

 HUB 10.94 1.16 9.22 608.96 1.04 580.88 522.97 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.48 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 32.86 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.86 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 589.9496 298.5599 508.8246 1173.9149 0.5025 -0.1165 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9517 9.2371 581.5042 523.1137 0.1789 30.4029 32.4000 1.9971

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 503.7490 112.9762 490.9170 1181.5269 0.4264 0.1606 2.2705

 

NASA/TM—2013-218094 H–130
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9356 9.6664 589.0724 523.0191 432.2457 0.0204 0.3356

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 499.6151 0.0000 499.6151 1181.8290 0.4227 0.2480 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6623 589.4069 522.9662 0.0000 0.0600 0.0380 0.1580

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8809 10.9084 1.1542 609.4429 26.6757 243.7628 1.8896

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 166161.391 0.446 612.805 597037.063 0.218711E-03

 

Melt Ratio at Stator LE, Throat, TE

0.38448E-01 0.47042E-01 0.67898E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.057 EfDer = 1.000 SH = 0.233673E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 10.908 609.442 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.247 WH2O = 0.015 lbm/sec H2O = 0.171g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.329 3418.116 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85828.719 51203.020 1.826 509.668 279.132 384.739 1.378

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 404.16 -0.14 404.16 0.34 0.60 546.45

 MEAN 15.91 0.00 -0.02 404.16 -0.14 404.16 0.34 0.55

 HUB 13.07 0.00 -0.02 404.16 -0.14 404.16 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.70 47.36 8.34 592.34 717.20 10.08 596.33 522.94 0.14

 MEAN 51.86 44.80 7.06 514.51 654.38 10.08 596.33 522.94 0.14

 HUB 46.29 38.84 7.45 422.59 584.85 10.08 596.33 522.94 0.14

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.08 287.10 409.46 1208.27 0.41 2.05 1.78 7.43

 MEAN 15.50 503.74 283.91 416.12 1204.15 0.42 2.13 1.86 5.75

 HUB 12.59 536.16 329.28 423.14 1200.18 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 580.05 503.47 292.95 0.42 5153.07 0.92 0.91

 MEAN 501.08 469.38 217.17 0.39 4402.17 0.92 0.91 0.91 1.53

 HUB 407.07 430.23 77.79 0.36 4147.41 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.58 1.15 11.20 636.18 1.04 616.11 532.24 0.10

 MEAN 12.33 1.13 10.95 632.29 1.04 611.92 530.93 0.11

 HUB 12.24 1.12 10.69 630.96 1.04 607.89 530.50 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.04 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.31 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.89 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 559.5643 289.1178 479.0857 1200.2535 0.4662 -0.1949 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3558 10.6670 608.0218 531.1992 0.1151 31.1101 33.0000 1.8899

 

NASA/TM—2013-218094 H–131
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.3023 110.5908 471.5065 1206.4578 0.4014 0.0719 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3303 11.0509 614.3241 531.1083 410.5396 0.0378 0.3481

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 469.3644 0.0000 469.3644 1207.5466 0.3887 0.2717 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1258 615.4670 531.1039 0.0000 0.0600 0.0378 0.1240

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8826 12.3302 1.1303 633.1395 23.7019 251.2256 1.9475

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 147729.500 0.439 544.828 607569.188 0.242960E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14124E+00 0.15256E+00 0.18273E+00

 trTOT = 1.3128 Tt4 = 633.1395 T1 = 482.2706 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 939236.50 3463.9131 179.0239 2.3862 0.8663 5.3155 1.3128 37.3740

NASA/TM—2013-218094 H–132
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.657 EfDer = 0.999 SH = 0.121111E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.139 WH2O = 0.008 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 175.965 3811.473 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143637.328 50330.277 1.614 831.557 515.100 619.754 1.203

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 414.56 -0.14 414.56 0.39 0.74 686.16

 MEAN 17.06 0.00 -0.02 414.56 -0.14 414.56 0.39 0.65

 HUB 12.51 0.00 -0.02 414.56 -0.14 414.56 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.94 50.47 7.47 661.65 780.92 4.65 468.45 465.20 2.75

 MEAN 52.86 47.20 5.66 547.16 686.58 4.65 468.45 465.20 2.75

 HUB 44.07 38.62 5.45 401.22 577.02 4.65 468.45 465.20 2.75

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 650.72 370.21 535.15 1075.27 0.61 7.29 6.52 16.04

 MEAN 18.04 685.65 410.22 549.39 1069.76 0.64 7.43 6.80 12.53

 HUB 15.00 789.89 538.48 577.91 1059.88 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.65 609.36 291.44 0.57 7640.32 0.92 0.91

 MEAN 578.46 574.57 168.24 0.54 7401.19 0.92 0.91 0.91 1.33

 HUB 481.08 580.75 57.39 0.55 8078.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 521.68 1.08 487.63 487.26 1.49

 MEAN 6.65 1.29 5.06 520.44 1.08 482.64 486.76 1.76

 HUB 6.80 1.32 4.73 523.94 1.09 473.77 488.91 2.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.67 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.75 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.98 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 725.4619 409.4241 598.8881 1066.4929 0.6802 -0.0747 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7052 4.9363 479.7035 487.6528 1.9765 34.3581 35.4000 1.0419

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 568.6710 139.1143 551.3927 1084.4683 0.5244 0.3126 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6762 5.5481 496.0190 487.1621 554.9116 0.0269 0.4237

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 564.4603 0.0000 564.4603 1084.8628 0.5203 0.3444 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5455 496.4052 487.1236 0.0000 0.0600 0.0397 0.3111

NASA/TM—2013-218094 H–133
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8773 6.6544 1.2878 522.0181 39.7491 219.1088 1.6985

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 247217.250 0.565 896.160 686730.188 0.139987E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.648 EfDer = 1.000 SH = 0.160264E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 6.654 522.018 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.136 WH2O = 0.010 lbm/sec H2O = 0.080g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.158 3663.511 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124270.961 50329.504 1.419 590.487 416.157 468.502 1.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 505.09 -0.17 505.09 0.46 0.76 656.97

 MEAN 18.08 0.00 -0.02 505.09 -0.17 505.09 0.46 0.71

 HUB 15.21 0.00 -0.02 505.09 -0.17 505.09 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.54 46.36 6.18 659.08 830.51 5.75 501.51 487.11 1.14

 MEAN 48.95 42.30 6.65 579.81 769.09 5.75 501.51 487.11 1.14

 HUB 44.01 37.84 6.17 487.82 702.32 5.75 501.51 487.11 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 583.72 299.56 500.99 1116.92 0.52 2.33 2.04 9.02

 MEAN 18.01 598.63 313.28 510.12 1112.80 0.54 2.40 2.13 7.35

 HUB 15.22 651.64 392.86 519.90 1108.98 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.92 614.22 355.35 0.55 6120.68 0.92 0.91

 MEAN 577.62 574.54 264.34 0.52 5645.27 0.92 0.91 0.91 1.45

 HUB 488.24 528.57 95.37 0.48 5983.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.09 1.22 6.73 553.57 1.06 526.19 501.62 0.55

 MEAN 7.97 1.20 6.56 551.12 1.06 522.32 500.59 0.61

 HUB 8.05 1.21 6.39 552.87 1.06 518.73 501.43 0.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.88 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.56 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.08 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 666.6125 314.1573 587.9434 1106.8849 0.6022 -0.1787 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0218 6.2965 516.8093 501.2869 0.7218 28.1170 30.6000 2.4830

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 554.9428 117.6518 542.3279 1118.5668 0.4961 0.1455 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9997 6.7754 527.7711 501.0569 491.5697 0.0250 0.2990

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 579.9785 0.0000 579.9785 1116.1204 0.5196 0.2066 0.5911

NASA/TM—2013-218094 H–134
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6529 525.4903 501.0533 0.0000 0.0600 0.0387 0.0625

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 7.9794 1.1991 552.5200 30.5035 248.4767 1.9262

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189806.906 0.443 688.048 616939.813 0.168387E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.805 EfDer = 1.000 SH = 0.180922E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 7.979 552.520 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.135 WH2O = 0.012 lbm/sec H2O = 0.104g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.965 3560.954 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107742.344 50329.098 1.528 545.479 357.066 424.468 1.189

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 474.04 -0.16 474.04 0.42 0.71 623.66

 MEAN 17.74 0.00 -0.02 474.04 -0.16 474.04 0.42 0.66

 HUB 15.05 0.00 -0.02 474.04 -0.16 474.04 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.64 46.36 7.28 643.69 799.54 7.07 534.46 500.97 0.48

 MEAN 50.21 43.40 6.81 568.91 740.65 7.07 534.46 500.97 0.48

 HUB 45.53 38.84 6.69 482.69 676.66 7.07 534.46 500.97 0.48

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 560.18 298.17 474.24 1149.86 0.49 2.26 1.98 8.75

 MEAN 17.51 573.40 310.95 481.77 1146.15 0.50 2.34 2.07 6.78

 HUB 14.85 623.36 385.48 489.88 1142.68 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.35 581.88 337.18 0.51 5910.06 0.92 0.91

 MEAN 561.47 543.01 250.52 0.47 5446.59 0.92 0.91 0.91 1.48

 HUB 476.27 498.22 90.79 0.44 5726.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.54 1.20 8.13 582.98 1.06 557.76 513.42 0.27

 MEAN 9.41 1.18 7.95 580.59 1.05 554.17 512.51 0.30

 HUB 9.49 1.19 7.77 582.03 1.05 550.81 513.13 0.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.16 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.84 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.20 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 633.4512 312.9921 550.7236 1141.4048 0.5550 -0.1640 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4619 7.6955 549.6346 513.0459 0.3320 29.6108 31.5000 1.8892

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.4478 115.9317 518.6488 1151.2759 0.4616 0.1491 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4427 8.1746 559.1786 512.8990 451.3937 0.0225 0.3218

 

NASA/TM—2013-218094 H–135
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 542.2184 0.0000 542.2184 1150.2898 0.4714 0.2320 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1053 558.2524 512.8662 0.0000 0.0600 0.0378 0.1038

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8813 9.4193 1.1804 581.8654 29.3474 238.0829 1.8456

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182697.922 0.453 662.278 591207.375 0.192073E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.090 EfDer = 1.000 SH = 0.210894E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 9.419 581.865 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.133 WH2O = 0.014 lbm/sec H2O = 0.138g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.030 3469.997 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94671.078 50328.504 1.654 513.330 310.438 395.845 1.275

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 442.62 -0.15 442.62 0.38 0.66 583.20

 MEAN 16.97 0.00 -0.02 442.62 -0.15 442.62 0.38 0.61

 HUB 14.32 0.00 -0.02 442.62 -0.15 442.62 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.38 46.36 8.02 617.71 760.04 8.53 566.13 512.83 0.25

 MEAN 50.89 43.80 7.09 544.29 701.66 8.53 566.13 512.83 0.25

 HUB 46.07 37.84 8.23 459.27 637.95 8.53 566.13 512.83 0.25

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 530.64 288.94 445.08 1179.87 0.45 2.16 1.89 8.34

 MEAN 16.57 540.49 296.74 451.74 1176.24 0.46 2.24 1.97 6.35

 HUB 13.89 583.79 360.88 458.89 1172.78 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 605.52 546.19 316.59 0.46 5458.05 0.92 0.91

 MEAN 531.56 509.13 234.82 0.43 4920.73 0.92 0.91 0.91 1.50

 HUB 445.48 466.62 84.60 0.40 5014.83 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.02 1.17 9.61 609.98 1.05 587.37 523.33 0.16

 MEAN 10.85 1.15 9.41 607.21 1.04 583.75 522.35 0.17

 HUB 10.88 1.16 9.21 607.70 1.04 580.33 522.56 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.99 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.30 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.18 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 582.1722 298.4095 499.8763 1173.4929 0.4961 -0.1145 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9031 9.2352 581.0850 522.7441 0.1842 30.8358 32.4000 1.5642

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 494.8693 110.9847 482.2634 1181.0870 0.4190 0.1700 2.2705

 

NASA/TM—2013-218094 H–136
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8881 9.6646 588.6333 522.6514 432.2457 0.0199 0.3418

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 490.8081 0.0000 490.8081 1181.3777 0.4155 0.2549 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6602 588.9559 522.5999 0.0000 0.0600 0.0374 0.1671

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8817 10.8616 1.1531 608.2917 26.4296 241.3040 1.8706

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 164628.641 0.449 596.777 586009.438 0.222703E-03

 

Melt Ratio at Stator LE, Throat, TE

0.40180E-01 0.48859E-01 0.69882E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.294 EfDer = 1.000 SH = 0.237854E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 10.862 608.291 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.131 WH2O = 0.015 lbm/sec H2O = 0.174g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.015 3393.785 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 84414.961 50327.969 1.851 509.668 275.284 384.739 1.398

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 397.51 -0.14 397.51 0.33 0.60 542.56

 MEAN 15.91 0.00 -0.02 397.51 -0.14 397.51 0.33 0.54

 HUB 13.07 0.00 -0.02 397.51 -0.14 397.51 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.93 47.36 8.57 587.56 709.51 10.06 595.61 522.57 0.15

 MEAN 52.09 44.80 7.29 510.37 647.01 10.06 595.61 522.57 0.15

 HUB 46.53 38.84 7.69 419.18 577.79 10.06 595.61 522.57 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.85 287.12 403.04 1207.34 0.41 2.05 1.78 7.43

 MEAN 15.50 498.04 283.40 409.54 1203.25 0.41 2.13 1.86 5.75

 HUB 12.59 529.64 327.28 416.41 1199.30 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 575.38 495.52 288.26 0.41 5153.41 0.92 0.91

 MEAN 497.04 461.92 213.65 0.38 4394.15 0.92 0.91 0.91 1.54

 HUB 403.79 423.38 76.51 0.35 4122.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.52 1.15 11.17 634.82 1.04 615.17 531.83 0.10

 MEAN 12.26 1.13 10.92 630.91 1.04 611.00 530.51 0.11

 HUB 12.17 1.12 10.67 629.51 1.03 607.00 530.06 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.47 35.57 31.50 4.07 0.93 0.44 1.40

 MEAN 34.68 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.17 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 552.5645 288.5931 471.2128 1199.4927 0.4607 -0.1926 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2900 10.6464 607.2479 530.7774 0.1192 31.4853 33.0000 1.5147

 

NASA/TM—2013-218094 H–137
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 476.2717 108.7571 463.6881 1205.6948 0.3950 0.0818 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2663 11.0312 613.5446 530.6893 410.5396 0.0369 0.3534

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 461.6923 0.0000 461.6923 1206.7394 0.3826 0.2775 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1025 614.6416 530.6838 0.0000 0.0600 0.0374 0.1326

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8832 12.2656 1.1293 631.7411 23.4547 249.0926 1.9310

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 146188.078 0.442 529.930 596961.438 0.247301E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14334E+00 0.15473E+00 0.18498E+00

 trTOT = 1.3099 Tt4 = 631.7411 T1 = 482.2704

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 930538.75 3373.1919 175.9648 2.3738 0.8684 5.6575 1.3099 37.3740

NASA/TM—2013-218094 H–138
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.995 EfDer = 0.999 SH = 0.121864E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.027 WH2O = 0.008 lbm/sec H2O = 0.053g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.914 3779.859 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140707.375 49457.773 1.643 831.557 506.171 619.754 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 406.10 -0.14 406.10 0.39 0.73 680.47

 MEAN 17.06 0.00 -0.02 406.10 -0.14 406.10 0.39 0.64

 HUB 12.51 0.00 -0.02 406.10 -0.14 406.10 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.25 50.47 7.78 656.16 771.79 4.67 469.01 465.19 2.71

 MEAN 53.20 47.20 6.00 542.62 677.87 4.67 469.01 465.19 2.71

 HUB 44.43 38.62 5.81 397.90 568.64 4.67 469.01 465.19 2.71

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 641.89 370.98 523.83 1076.01 0.60 7.29 6.52 16.04

 MEAN 18.04 675.62 409.09 537.69 1070.51 0.63 7.43 6.80 12.53

 HUB 15.00 776.63 533.18 564.69 1060.91 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.16 596.43 285.19 0.55 7656.14 0.92 0.91

 MEAN 573.66 562.31 164.57 0.53 7380.67 0.92 0.91 0.91 1.34

 HUB 477.09 567.47 56.08 0.53 7999.43 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 521.43 1.08 488.30 487.12 1.47

 MEAN 6.64 1.28 5.09 520.02 1.08 483.32 486.53 1.74

 HUB 6.77 1.31 4.76 523.19 1.08 474.69 488.49 2.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.31 28.56 24.20 4.36 0.93 0.36 1.80

 MEAN 37.26 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.36 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 713.7106 408.2913 585.3896 1067.4764 0.6686 -0.0723 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6863 4.9718 480.5901 487.3879 1.9337 34.8946 35.4000 0.5054

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 556.5621 136.1521 539.6517 1085.1464 0.5129 0.3214 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6593 5.5775 496.6411 486.9215 554.9116 0.0263 0.4307

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 552.2631 0.0000 552.2631 1085.5403 0.5087 0.3528 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5767 497.0268 486.8884 0.0000 0.0600 0.0381 0.3209

NASA/TM—2013-218094 H–139
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8798 6.6397 1.2850 521.5445 39.2756 217.0037 1.6822

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244275.156 0.567 870.144 672722.125 0.141389E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.990 EfDer = 1.000 SH = 0.162418E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 6.640 521.544 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.024 WH2O = 0.010 lbm/sec H2O = 0.081g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.939 3634.774 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121765.500 49456.988 1.441 590.487 409.663 468.502 1.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 494.91 -0.17 494.91 0.45 0.75 651.81

 MEAN 18.08 0.00 -0.02 494.91 -0.17 494.91 0.45 0.70

 HUB 15.21 0.00 -0.02 494.91 -0.17 494.91 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.87 46.36 6.51 653.62 819.98 5.78 501.86 486.88 1.14

 MEAN 49.29 42.30 6.99 575.00 758.79 5.78 501.86 486.88 1.14

 HUB 44.36 37.84 6.52 483.77 692.20 5.78 501.86 486.88 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 576.37 301.05 491.50 1117.03 0.52 2.33 2.04 9.02

 MEAN 18.01 590.64 313.65 500.48 1112.89 0.53 2.40 2.13 7.35

 HUB 15.22 642.58 390.76 510.11 1109.03 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 649.48 602.48 348.43 0.54 6150.96 0.92 0.91 

 MEAN 572.83 563.61 259.18 0.51 5651.86 0.92 0.91 0.91 1.46

 HUB 484.19 518.59 93.43 0.47 5951.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.07 1.21 6.74 552.99 1.06 526.29 501.38 0.56

 MEAN 7.94 1.20 6.57 550.44 1.06 522.40 500.31 0.62

 HUB 8.02 1.21 6.40 551.97 1.06 518.78 501.06 0.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.49 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.07 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.45 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 656.1992 314.5280 575.9075 1107.3002 0.5926 -0.1742 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9939 6.3214 517.1979 500.9830 0.7247 28.6409 30.6000 1.9591

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 543.8175 115.2932 531.4555 1118.8447 0.4861 0.1570 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9736 6.7976 528.0350 500.7610 491.5697 0.0241 0.3064

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 567.9688 0.0000 567.9688 1116.5325 0.5087 0.2149 0.5911

NASA/TM—2013-218094 H–140
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6808 525.8796 500.7564 0.0000 0.0600 0.0379 0.0757

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 7.9538 1.1979 551.8012 30.2584 245.3979 1.9023

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188283.281 0.446 670.693 604122.313 0.170870E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.098 EfDer = 1.000 SH = 0.183868E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 7.954 551.801 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.023 WH2O = 0.012 lbm/sec H2O = 0.106g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.159 3533.717 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105745.320 49456.570 1.551 545.479 351.781 424.468 1.207

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 465.26 -0.16 465.26 0.41 0.70 618.89

 MEAN 17.74 0.00 -0.02 465.26 -0.16 465.26 0.41 0.65

 HUB 15.05 0.00 -0.02 465.26 -0.16 465.26 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.92 46.36 7.56 638.35 790.04 7.08 534.41 500.68 0.49

 MEAN 50.50 43.40 7.10 564.19 731.41 7.08 534.41 500.68 0.49

 HUB 45.82 38.84 6.98 478.68 667.65 7.08 534.41 500.68 0.49

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 553.61 298.93 465.97 1149.55 0.48 2.26 1.98 8.75

 MEAN 17.51 566.27 310.78 473.37 1145.83 0.49 2.34 2.07 6.78

 HUB 14.85 615.25 383.21 481.34 1142.33 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.08 571.66 331.16 0.50 5924.94 0.92 0.91

 MEAN 556.82 533.49 246.04 0.47 5443.56 0.92 0.91 0.91 1.49

 HUB 472.32 489.52 89.12 0.43 5693.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.50 1.19 8.12 582.08 1.05 557.46 513.10 0.28

 MEAN 9.37 1.18 7.94 579.62 1.05 553.86 512.16 0.30

 HUB 9.43 1.19 7.76 580.90 1.05 550.48 512.71 0.33

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.68 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.29 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.52 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 624.5403 312.8213 540.5492 1141.3019 0.5472 -0.1608 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4185 7.7030 549.5353 512.6795 0.3390 30.0584 31.5000 1.4416

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 521.7470 113.8156 509.1816 1151.0911 0.4533 0.1590 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4007 8.1796 558.9996 512.5361 451.3937 0.0219 0.3280

 

NASA/TM—2013-218094 H–141
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 532.1888 0.0000 532.1888 1150.1512 0.4627 0.2390 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1130 558.1181 512.5040 0.0000 0.0600 0.0373 0.1143

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 9.3777 1.1790 580.8654 29.0662 235.6037 1.8264

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180948.500 0.456 644.565 579694.813 0.195423E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.336 EfDer = 0.999 SH = 0.214678E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 9.378 580.865 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.021 WH2O = 0.014 lbm/sec H2O = 0.140g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.563 3444.176 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 93064.078 49455.973 1.677 513.330 306.145 395.845 1.293 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 435.11 -0.15 435.11 0.38 0.65 578.86

 MEAN 16.97 0.00 -0.02 435.11 -0.15 435.11 0.38 0.60

 HUB 14.32 0.00 -0.02 435.11 -0.15 435.11 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.62 46.36 8.26 612.59 751.51 8.52 565.66 512.47 0.26

 MEAN 51.14 43.80 7.34 539.77 693.42 8.52 565.66 512.47 0.26

 HUB 46.32 37.84 8.48 455.47 630.00 8.52 565.66 512.47 0.26

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 524.77 289.11 437.95 1179.15 0.45 2.16 1.89 8.34

 MEAN 16.57 534.15 296.22 444.49 1175.53 0.45 2.24 1.97 6.35

 HUB 13.89 576.58 358.61 451.49 1172.07 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 600.50 537.37 311.40 0.46 5461.22 0.92 0.91

 MEAN 527.15 500.90 230.94 0.43 4911.98 0.92 0.91 0.91 1.51

 HUB 441.79 459.09 83.18 0.39 4983.25 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.96 1.17 9.58 608.76 1.05 586.65 522.93 0.17

 MEAN 10.79 1.15 9.38 605.96 1.04 583.04 521.93 0.18

 HUB 10.81 1.15 9.18 606.32 1.04 579.62 522.09 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.43 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.68 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 38.46 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 574.7988 297.8811 491.5898 1172.8910 0.4901 -0.1128 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8409 9.2186 580.4873 522.3145 0.1903 31.2140 32.4000 1.1860

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 486.6958 109.1516 474.2981 1180.4478 0.4123 0.1780 2.2705

 

NASA/TM—2013-218094 H–142
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8269 9.6461 587.9949 522.2230 432.2457 0.0195 0.3471

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 482.7048 0.0000 482.7048 1180.7279 0.4088 0.2607 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6415 588.3066 522.1727 0.0000 0.0600 0.0371 0.1749

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8822 10.8010 1.1518 607.0092 26.1470 239.1834 1.8541

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 162868.422 0.452 580.161 575240.938 0.226708E-03

 

Melt Ratio at Stator LE, Throat, TE

0.41421E-01 0.50140E-01 0.71233E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.496 EfDer = 0.999 SH = 0.242102E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 10.801 607.008 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.019 WH2O = 0.015 lbm/sec H2O = 0.177g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.805 3369.190 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 83107.953 49455.438 1.876 509.668 271.743 384.739 1.416

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 391.35 -0.13 391.35 0.33 0.59 538.62

 MEAN 15.91 0.00 -0.02 391.35 -0.13 391.35 0.33 0.54

 HUB 13.07 0.00 -0.02 391.35 -0.13 391.35 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.12 47.36 8.76 582.69 702.03 10.03 594.72 522.15 0.15

 MEAN 52.30 44.80 7.50 506.13 639.89 10.03 594.72 522.15 0.15

 HUB 46.74 38.84 7.90 415.71 571.03 10.03 594.72 522.15 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.79 286.64 397.16 1206.22 0.41 2.05 1.78 7.43

 MEAN 15.50 492.57 282.50 403.51 1202.16 0.41 2.13 1.86 5.75

 HUB 12.59 523.46 325.16 410.21 1198.24 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 570.60 488.23 283.96 0.40 5144.77 0.92 0.91

 MEAN 492.92 455.07 210.42 0.38 4380.26 0.92 0.91 0.91 1.55

 HUB 400.44 417.06 75.28 0.35 4095.58 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.43 1.15 11.12 633.27 1.04 614.02 531.35 0.11

 MEAN 12.18 1.13 10.87 629.37 1.04 609.90 530.03 0.12

 HUB 12.09 1.12 10.62 627.91 1.03 605.93 529.55 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.82 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 35.00 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.40 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 545.9414 287.6828 463.9942 1198.5315 0.4555 -0.1906 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2068 10.6075 606.2706 530.2855 0.1239 31.7995 33.0000 1.2005

 

NASA/TM—2013-218094 H–143
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 468.9604 107.0875 456.5700 1204.7094 0.3893 0.0899 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1847 10.9910 612.5381 530.1994 410.5396 0.0362 0.3577

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 454.7002 0.0000 454.7002 1205.7153 0.3771 0.2823 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0590 613.5947 530.1933 0.0000 0.0600 0.0371 0.1397

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8835 12.1835 1.1280 630.1803 23.1765 247.3121 1.9171

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 144452.453 0.444 514.561 586591.063 0.251739E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14455E+00 0.15596E+00 0.18618E+00

 trTOT = 1.3067 Tt4 = 630.1803 T1 = 482.2704

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 920827.81 3280.1248 172.9144 2.3578 0.8699 5.9955 1.3067 37.3740

NASA/TM—2013-218094 H–144
 50μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.969 EfDer = 0.985 SH = 0.114976E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 5.167 482.271 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.921 WH2O = 0.009 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.801 4120.825 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171010.438 58006.203 1.401 831.557 593.652 619.754 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 493.56 -0.17 493.56 0.47 0.83 741.85

 MEAN 17.06 0.00 -0.02 493.56 -0.17 493.56 0.47 0.74

 HUB 12.51 0.00 -0.02 493.56 -0.17 493.56 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.40 50.47 4.93 715.35 869.24 4.45 462.68 465.30 3.25

 MEAN 50.17 47.20 2.97 591.57 770.56 4.45 462.68 465.30 3.25

 HUB 41.32 38.62 2.70 433.79 657.21 4.45 462.68 465.30 3.25

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 741.37 362.70 646.58 1066.64 0.70 7.29 6.52 16.04

 MEAN 18.04 787.07 421.49 664.70 1061.12 0.74 7.43 6.80 12.53

 HUB 15.00 928.87 591.96 715.81 1047.12 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.35 736.50 352.65 0.69 7486.10 0.92 0.90

 MEAN 625.41 695.28 203.92 0.66 7604.87 0.92 0.90 0.90 1.21

 HUB 520.13 719.40 71.83 0.69 8881.49 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 524.02 1.09 479.82 488.58 1.80

 MEAN 6.81 1.32 4.75 524.68 1.09 474.87 489.10 2.15

 HUB 7.12 1.38 4.29 531.80 1.10 462.42 493.50 3.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.29 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.38 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.59 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 849.9094 420.6696 738.5005 1054.2638 0.8062 -0.1057 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8831 4.5082 468.7473 490.4814 2.7130 29.6670 35.4000 5.7330

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 691.5118 169.1649 670.5012 1076.1078 0.6426 0.2318 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8130 5.1774 488.3825 489.5546 554.9116 0.0412 0.3616

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 692.9905 0.0000 692.9905 1075.9021 0.6441 0.2576 1.3089

NASA/TM—2013-218094 H–145
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1200 488.2229 489.4227 0.0000 0.0600 0.0711 0.2063

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8263 6.7456 1.3055 526.8323 44.5619 237.2687 1.8393

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 277116.969 0.542 1157.747 817600.875 0.128803E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.618 EfDer = 0.990 SH = 0.143046E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 6.746 526.832 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.919 WH2O = 0.011 lbm/sec H2O = 0.068g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.364 3942.716 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149419.844 58005.563 1.242 590.487 475.303 468.502 0.986

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 607.31 -0.21 607.31 0.56 0.86 707.04

 MEAN 18.08 0.00 -0.02 607.31 -0.21 607.31 0.56 0.80

 HUB 15.21 0.00 -0.02 607.31 -0.21 607.31 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.57 46.36 3.21 712.58 936.42 5.47 497.18 489.28 1.14

 MEAN 45.92 42.30 3.62 626.87 872.95 5.47 497.18 489.28 1.14

 HUB 40.98 37.84 3.14 527.41 804.49 5.47 497.18 489.28 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 660.13 282.82 596.47 1114.63 0.59 2.33 2.04 9.02

 MEAN 18.01 680.22 308.30 606.34 1111.00 0.61 2.40 2.13 7.35

 HUB 15.22 742.59 412.91 617.20 1107.74 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.07 732.54 425.25 0.66 5779.52 0.92 0.91

 MEAN 624.50 683.83 316.20 0.62 5556.27 0.92 0.91 0.91 1.37

 HUB 527.86 627.82 114.96 0.57 6288.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.20 1.22 6.49 559.05 1.06 524.02 503.64 0.51

 MEAN 8.14 1.21 6.34 557.81 1.06 520.61 503.15 0.56

 HUB 8.34 1.24 6.19 561.89 1.07 517.56 504.97 0.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.37 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 26.95 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.78 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 778.8822 309.1667 714.8940 1100.4677 0.7078 -0.2337 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2084 5.8989 510.8253 504.0860 0.7459 23.3868 30.6000 7.2132

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 672.3079 142.5341 657.0251 1113.7885 0.6036 0.0268 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1502 6.3903 523.2526 503.7094 491.5697 0.0408 0.2245

 

NASA/TM—2013-218094 H–146
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 714.9500 0.0000 714.9500 1108.6941 0.6449 0.1032 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1372 518.5026 503.6655 0.0000 0.0600 0.0724 -0.1073

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8276 8.0907 1.1994 559.5821 32.7515 279.2954 2.1651

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 203777.172 0.406 851.346 740021.500 0.148649E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.993 EfDer = 0.992 SH = 0.157590E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 8.091 559.582 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.918 WH2O = 0.012 lbm/sec H2O = 0.087g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.516 3825.601 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 128622.125 58005.234 1.336 545.479 408.441 424.468 1.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 565.91 -0.19 565.91 0.50 0.80 670.01

 MEAN 17.74 0.00 -0.02 565.91 -0.19 565.91 0.50 0.74

 HUB 15.05 0.00 -0.02 565.91 -0.19 565.91 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.89 46.36 4.53 695.93 897.14 6.82 533.85 503.46 0.41

 MEAN 47.39 43.40 3.99 615.09 835.96 6.82 533.85 503.46 0.41

 HUB 42.69 38.84 3.85 521.86 769.94 6.82 533.85 503.46 0.41

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 630.01 285.92 561.39 1151.43 0.55 2.26 1.98 8.75

 MEAN 17.51 648.14 309.11 569.68 1148.06 0.56 2.34 2.07 6.78

 HUB 14.85 707.10 406.18 578.81 1144.99 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 689.90 401.00 0.60 5667.99 0.92 0.91 

 MEAN 607.05 642.88 297.93 0.56 5414.96 0.92 0.91 0.91 1.40

 HUB 514.93 588.93 108.75 0.51 6034.66 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.70 1.20 7.93 591.17 1.06 559.27 515.92 0.22

 MEAN 9.62 1.19 7.77 589.76 1.05 556.00 515.42 0.24

 HUB 9.81 1.21 7.61 593.21 1.06 553.03 516.77 0.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.99 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.48 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 35.06 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 730.3590 311.1412 660.7689 1140.2560 0.6405 -0.2029 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6901 7.3770 548.5259 516.0888 0.2850 25.2147 31.5000 6.2853

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 637.3753 139.0391 622.0253 1150.8380 0.5538 0.0409 2.3726

 

NASA/TM—2013-218094 H–147
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6431 7.8492 558.7398 515.8715 451.3937 0.0342 0.2572

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 654.4291 0.0000 654.4291 1148.9849 0.5696 0.1491 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7219 556.9743 515.7950 0.0000 0.0600 0.0583 -0.0247

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8482 9.5963 1.1861 591.3758 31.7958 264.8535 2.0531

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 197926.875 0.419 826.905 699976.250 0.165407E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.577 EfDer = 0.995 SH = 0.179594E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 9.596 591.375 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.916 WH2O = 0.013 lbm/sec H2O = 0.114g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.921 3721.344 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111872.602 58004.734 1.450 513.330 354.033 395.845 1.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 523.04 -0.18 523.04 0.45 0.73 625.45

 MEAN 16.97 0.00 -0.02 523.04 -0.18 523.04 0.45 0.68

 HUB 14.32 0.00 -0.02 523.04 -0.18 523.04 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.94 46.36 5.58 667.85 848.43 8.37 569.41 515.71 0.19

 MEAN 48.38 43.80 4.58 588.47 787.45 8.37 569.41 515.71 0.19

 HUB 43.52 37.84 5.68 496.55 721.33 8.37 569.41 515.71 0.19

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 593.18 281.97 521.88 1185.30 0.50 2.16 1.89 8.34

 MEAN 16.57 607.72 298.11 529.58 1181.76 0.51 2.24 1.97 6.35

 HUB 13.89 659.39 381.34 537.93 1178.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.67 641.30 372.70 0.54 5327.01 0.92 0.91

 MEAN 574.70 597.46 276.60 0.51 4943.89 0.92 0.91 0.91 1.43

 HUB 481.64 547.20 100.30 0.46 5299.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.28 1.18 9.53 621.04 1.05 592.79 526.39 0.12

 MEAN 11.16 1.16 9.34 618.91 1.05 589.25 525.66 0.13

 HUB 11.28 1.17 9.14 620.89 1.05 585.97 526.38 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.38 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.38 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.33 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 661.9050 299.7860 590.1241 1177.5358 0.5621 -0.1356 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2195 9.0781 585.1064 526.1412 0.1381 26.9308 32.4000 5.4692

 

NASA/TM—2013-218094 H–148
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 584.9426 131.1855 570.0422 1185.2654 0.4935 0.0811 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1851 9.4900 592.8094 526.0141 432.2457 0.0281 0.2866

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 580.2761 0.0000 580.2761 1185.6703 0.4894 0.1902 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4854 593.2487 525.9433 0.0000 0.0600 0.0467 0.0787

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8637 11.1497 1.1619 620.2776 28.9048 265.1896 2.0557

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180042.766 0.420 752.188 685883.063 0.189766E-03

 

Melt Ratio at Stator LE, Throat, TE

0.22326E-01 0.30146E-01 0.49383E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.165 EfDer = 0.998 SH = 0.203628E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.930 3973.502 11.150 620.277 1.000 1.000 0.980

 W Kg/sec = 33.604 Wdry = 73.915 WH2O = 0.015 lbm/sec H2O = 0.147g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.588 3633.612 1.380 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98474.133 58004.184 1.633 509.668 312.097 384.739 1.233

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 463.71 -0.16 463.71 0.39 0.66 580.90

 MEAN 15.91 0.00 -0.02 463.71 -0.16 463.71 0.39 0.60

 HUB 13.07 0.00 -0.02 463.71 -0.16 463.71 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.88 47.36 6.52 635.25 786.62 10.06 603.02 525.90 0.10

 MEAN 49.97 44.80 5.17 551.79 720.88 10.06 603.02 525.90 0.10

 HUB 44.35 38.84 5.51 453.21 648.51 10.06 603.02 525.90 0.10

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 547.90 287.18 466.60 1216.81 0.45 2.05 1.78 7.43

 MEAN 15.50 555.58 288.83 474.60 1212.48 0.46 2.13 1.86 5.75

 HUB 12.59 594.80 347.06 483.05 1208.35 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 574.34 334.89 0.47 5154.96 0.92 0.91

 MEAN 537.38 535.75 248.56 0.44 4478.71 0.92 0.91 0.91 1.47

 HUB 436.56 491.27 89.50 0.41 4371.60 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.96 1.16 11.29 648.96 1.05 624.87 535.53 0.07

 MEAN 12.71 1.14 11.02 645.20 1.04 620.43 534.31 0.08

 HUB 12.67 1.14 10.76 644.61 1.04 616.21 534.14 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.61 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.32 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.70 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 623.7801 294.1259 550.0832 1207.1307 0.5167 -0.2160 2.0437

 

NASA/TM—2013-218094 H–149
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7416 10.6454 615.0401 534.6289 0.0843 28.1331 33.0000 4.8669

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 557.3695 127.2758 542.6432 1213.2960 0.4594 -0.0133 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6900 11.0014 621.3315 534.4940 410.5396 0.0494 0.3069

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 538.7160 0.0000 538.7160 1214.8634 0.4434 0.2239 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1147 622.9728 534.5038 0.0000 0.0600 0.0446 0.0513

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8708 12.6984 1.1389 646.2527 25.9803 269.3834 2.0882

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161940.484 0.418 676.560 690968.938 0.211928E-03

 

Melt Ratio at Stator LE, Throat, TE

0.12172E+00 0.13243E+00 0.16199E+00

 trTOT = 1.3400 Tt4 = 646.2527 T1 = 482.2715

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1020804.25 4264.7456 202.8008 2.4575 0.8275 2.9688 1.3400 37.3740

NASA/TM—2013-218094 H–150
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.316 EfDer = 0.998 SH = 0.120376E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 5.167 482.271 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.254 WH2O = 0.008 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 179.024 3842.429 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146607.906 51205.289 1.587 831.557 524.054 619.754 1.183

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 423.13 -0.15 423.13 0.40 0.75 691.73

 MEAN 17.06 0.00 -0.02 423.13 -0.15 423.13 0.40 0.66

 HUB 12.51 0.00 -0.02 423.13 -0.15 423.13 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH 

 TIP 57.62 50.47 7.15 667.02 790.04 4.63 467.87 465.21 2.80

 MEAN 52.52 47.20 5.32 551.60 695.32 4.63 467.87 465.21 2.80

 HUB 43.72 38.62 5.10 404.48 585.46 4.63 467.87 465.21 2.80

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 659.76 369.15 546.82 1074.45 0.61 7.29 6.52 16.04

 MEAN 18.04 695.89 411.17 561.43 1068.94 0.65 7.43 6.80 12.53

 HUB 15.00 803.52 543.76 591.58 1058.77 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.02 622.69 297.87 0.58 7618.59 0.92 0.91

 MEAN 583.15 587.18 171.98 0.55 7418.41 0.92 0.91 0.91 1.31

 HUB 484.99 594.49 58.77 0.56 8158.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.22 521.88 1.08 486.88 487.37 1.51

 MEAN 6.67 1.29 5.03 520.84 1.08 481.90 486.98 1.79

 HUB 6.84 1.32 4.69 524.69 1.09 472.78 489.34 2.48

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.02 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.22 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.59 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 737.5757 410.3744 612.8709 1065.4132 0.6923 -0.0774 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7227 4.8976 478.7310 487.9099 2.0269 33.8060 35.4000 1.5940

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 581.2339 142.1875 563.5739 1083.6951 0.5363 0.3034 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6914 5.5147 495.3102 487.3918 554.9116 0.0278 0.4164

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 577.1659 0.0000 577.1659 1084.0847 0.5324 0.3354 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5097 495.6920 487.3470 0.0000 0.0600 0.0417 0.3006

NASA/TM—2013-218094 H–151
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8741 6.6669 1.2903 522.4712 40.2020 221.2746 1.7153

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 250031.047 0.562 922.117 700932.563 0.138611E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.292 EfDer = 1.000 SH = 0.158126E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 6.667 522.471 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.252 WH2O = 0.010 lbm/sec H2O = 0.078g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.419 3691.664 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 126862.750 51204.535 1.397 590.487 422.776 468.502 1.108

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 515.63 -0.18 515.63 0.47 0.77 662.02

 MEAN 18.08 0.00 -0.02 515.63 -0.18 515.63 0.47 0.72

 HUB 15.21 0.00 -0.02 515.63 -0.18 515.63 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.19 46.36 5.83 664.44 841.18 5.73 501.10 487.32 1.13

 MEAN 48.59 42.30 6.29 584.52 779.58 5.73 501.10 487.32 1.13

 HUB 43.65 37.84 5.81 491.78 712.67 5.73 501.10 487.32 1.13

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 591.28 297.67 510.88 1116.70 0.53 2.33 2.04 9.02

 MEAN 18.01 606.84 312.60 520.13 1112.63 0.55 2.40 2.13 7.35

 HUB 15.22 660.92 394.80 530.05 1108.85 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.23 626.46 362.56 0.56 6082.10 0.92 0.91

 MEAN 582.31 585.90 269.71 0.53 5633.10 0.92 0.91 0.91 1.44

 HUB 492.20 538.92 97.40 0.49 6012.79 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.71 554.08 1.06 525.98 501.82 0.55

 MEAN 7.99 1.20 6.54 551.75 1.06 522.15 500.85 0.61

 HUB 8.09 1.21 6.38 553.72 1.06 518.61 501.79 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.23 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 31.01 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.68 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 677.4536 313.4760 600.5632 1106.3429 0.6123 -0.1836 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0453 6.2652 516.3025 501.5639 0.7211 27.5632 30.6000 3.0368

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 566.6553 120.1349 553.7741 1118.1534 0.5068 0.1330 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0209 6.7457 527.3795 501.3245 491.5697 0.0261 0.2909

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 592.7982 0.0000 592.7982 1115.5443 0.5314 0.1967 0.5911

NASA/TM—2013-218094 H–152
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6153 524.9463 501.3198 0.0000 0.0600 0.0406 0.0470

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8767 7.9990 1.1998 553.1844 30.7150 251.7875 1.9518

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191120.688 0.438 704.855 630043.000 0.165919E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.487 EfDer = 1.000 SH = 0.178012E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 7.999 553.184 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.250 WH2O = 0.012 lbm/sec H2O = 0.102g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.857 3587.719 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109851.781 51204.137 1.504 545.479 362.604 424.468 1.171 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 483.33 -0.17 483.33 0.43 0.72 628.35

 MEAN 17.74 0.00 -0.02 483.33 -0.17 483.33 0.43 0.67

 HUB 15.05 0.00 -0.02 483.33 -0.17 483.33 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.33 46.36 6.97 648.92 809.27 7.06 534.41 501.22 0.47

 MEAN 49.89 43.40 6.49 573.53 750.16 7.06 534.41 501.22 0.47

 HUB 45.20 38.84 6.36 486.61 685.97 7.06 534.41 501.22 0.47

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 567.00 296.89 483.05 1150.03 0.49 2.26 1.98 8.75

 MEAN 17.51 580.80 310.72 490.69 1146.35 0.51 2.34 2.07 6.78

 HUB 14.85 631.75 387.53 498.93 1142.90 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.51 592.80 343.62 0.52 5884.78 0.92 0.91

 MEAN 566.03 553.14 255.32 0.48 5442.51 0.92 0.91 0.91 1.47

 HUB 480.14 507.45 92.61 0.44 5757.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.57 1.20 8.12 583.76 1.06 557.93 513.69 0.26

 MEAN 9.44 1.18 7.94 581.46 1.05 554.36 512.82 0.29

 HUB 9.53 1.19 7.76 583.10 1.05 551.03 513.51 0.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.58 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.34 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.84 10.52 6.50 4.02 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 642.8152 312.7542 561.6015 1141.3477 0.5632 -0.1676 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4957 7.6768 549.5794 513.3654 0.3262 29.1133 31.5000 2.3867

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 541.8835 118.2082 528.8333 1151.2821 0.4707 0.1378 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4749 8.1566 559.1836 513.2144 451.3937 0.0233 0.3147

 

NASA/TM—2013-218094 H–153
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 553.0262 0.0000 553.0262 1150.2433 0.4808 0.2241 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0844 558.2064 513.1807 0.0000 0.0600 0.0386 0.0918

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 9.4509 1.1815 582.7703 29.5879 240.8769 1.8673

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184193.906 0.449 679.309 602994.688 0.188743E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.811 EfDer = 1.000 SH = 0.207102E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 9.451 582.770 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.248 WH2O = 0.014 lbm/sec H2O = 0.135g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.596 3495.462 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96390.492 51203.551 1.629 513.330 315.023 395.845 1.257

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 450.66 -0.16 450.66 0.39 0.66 587.48

 MEAN 16.97 0.00 -0.02 450.66 -0.16 450.66 0.39 0.61

 HUB 14.32 0.00 -0.02 450.66 -0.16 450.66 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.11 46.36 7.75 622.73 768.82 8.53 566.46 513.14 0.24

 MEAN 50.61 43.80 6.81 548.71 710.17 8.53 566.46 513.14 0.24

 HUB 45.78 37.84 7.94 463.00 646.23 8.53 566.46 513.14 0.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 536.74 288.26 452.76 1180.42 0.45 2.16 1.89 8.34

 MEAN 16.57 547.11 296.89 459.55 1176.79 0.46 2.24 1.97 6.35

 HUB 13.89 591.30 362.91 466.83 1173.34 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 610.44 555.69 322.18 0.47 5445.33 0.92 0.91

 MEAN 535.88 517.98 238.99 0.44 4923.26 0.92 0.91 0.91 1.49

 HUB 449.10 474.72 86.19 0.40 5043.10 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.06 1.17 9.62 611.05 1.05 587.91 523.67 0.16

 MEAN 10.90 1.15 9.42 608.33 1.04 584.30 522.71 0.17

 HUB 10.94 1.16 9.22 608.96 1.04 580.88 522.97 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.48 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 32.86 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.86 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 589.9496 298.5599 508.8246 1173.9149 0.5025 -0.1165 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9517 9.2371 581.5042 523.1137 0.1789 30.4029 32.4000 1.9971

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 503.7490 112.9762 490.9170 1181.5269 0.4264 0.1606 2.2705

 

NASA/TM—2013-218094 H–154
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9356 9.6664 589.0724 523.0191 432.2457 0.0204 0.3356

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 499.6151 0.0000 499.6151 1181.8290 0.4227 0.2480 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6623 589.4069 522.9662 0.0000 0.0600 0.0380 0.1580

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8809 10.9084 1.1542 609.4429 26.6757 243.7628 1.8896

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 166161.391 0.446 612.805 597037.063 0.218711E-03

 

Melt Ratio at Stator LE, Throat, TE

0.38448E-01 0.47042E-01 0.67898E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.057 EfDer = 1.000 SH = 0.233673E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.262 3705.060 10.908 609.442 1.000 1.000 0.980

 W Kg/sec = 29.664 Wdry = 65.247 WH2O = 0.015 lbm/sec H2O = 0.171g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.329 3418.116 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85828.719 51203.020 1.826 509.668 279.132 384.739 1.378

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 404.16 -0.14 404.16 0.34 0.60 546.45

 MEAN 15.91 0.00 -0.02 404.16 -0.14 404.16 0.34 0.55

 HUB 13.07 0.00 -0.02 404.16 -0.14 404.16 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.70 47.36 8.34 592.34 717.20 10.08 596.33 522.94 0.14

 MEAN 51.86 44.80 7.06 514.51 654.38 10.08 596.33 522.94 0.14

 HUB 46.29 38.84 7.45 422.59 584.85 10.08 596.33 522.94 0.14

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.08 287.10 409.46 1208.27 0.41 2.05 1.78 7.43

 MEAN 15.50 503.74 283.91 416.12 1204.15 0.42 2.13 1.86 5.75

 HUB 12.59 536.16 329.28 423.14 1200.18 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 580.05 503.47 292.95 0.42 5153.07 0.92 0.91

 MEAN 501.08 469.38 217.17 0.39 4402.17 0.92 0.91 0.91 1.53

 HUB 407.07 430.23 77.79 0.36 4147.41 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.58 1.15 11.20 636.18 1.04 616.11 532.24 0.10

 MEAN 12.33 1.13 10.95 632.29 1.04 611.92 530.93 0.11

 HUB 12.24 1.12 10.69 630.96 1.04 607.89 530.50 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.04 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.31 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.89 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 559.5643 289.1178 479.0857 1200.2535 0.4662 -0.1949 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3558 10.6670 608.0218 531.1992 0.1151 31.1101 33.0000 1.8899

 

NASA/TM—2013-218094 H–155
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.3023 110.5908 471.5065 1206.4578 0.4014 0.0719 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3303 11.0509 614.3241 531.1083 410.5396 0.0378 0.3481

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 469.3644 0.0000 469.3644 1207.5466 0.3887 0.2717 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1258 615.4670 531.1039 0.0000 0.0600 0.0378 0.1240

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8826 12.3302 1.1303 633.1395 23.7019 251.2256 1.9475

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 147729.500 0.439 544.828 607569.188 0.242960E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14124E+00 0.15256E+00 0.18273E+00

 trTOT = 1.3128 Tt4 = 633.1395 T1 = 482.2706

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 939236.50 3463.9131 179.0239 2.3862 0.8663 5.3155 1.3128 37.3740

NASA/TM—2013-218094 H–156
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.657 EfDer = 0.999 SH = 0.121111E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.139 WH2O = 0.008 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 175.965 3811.473 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143637.328 50330.277 1.614 831.557 515.100 619.754 1.203

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 414.56 -0.14 414.56 0.39 0.74 686.16

 MEAN 17.06 0.00 -0.02 414.56 -0.14 414.56 0.39 0.65

 HUB 12.51 0.00 -0.02 414.56 -0.14 414.56 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.94 50.47 7.47 661.65 780.92 4.65 468.45 465.20 2.75

 MEAN 52.86 47.20 5.66 547.16 686.58 4.65 468.45 465.20 2.75

 HUB 44.07 38.62 5.45 401.22 577.02 4.65 468.45 465.20 2.75

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 650.72 370.21 535.15 1075.27 0.61 7.29 6.52 16.04

 MEAN 18.04 685.65 410.22 549.39 1069.76 0.64 7.43 6.80 12.53

 HUB 15.00 789.89 538.48 577.91 1059.88 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.65 609.36 291.44 0.57 7640.32 0.92 0.91

 MEAN 578.46 574.57 168.24 0.54 7401.19 0.92 0.91 0.91 1.33

 HUB 481.08 580.75 57.39 0.55 8078.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 521.68 1.08 487.63 487.26 1.49

 MEAN 6.65 1.29 5.06 520.44 1.08 482.64 486.76 1.76

 HUB 6.80 1.32 4.73 523.94 1.09 473.77 488.91 2.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.67 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.75 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.98 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 725.4619 409.4241 598.8881 1066.4929 0.6802 -0.0747 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7052 4.9363 479.7035 487.6528 1.9765 34.3581 35.4000 1.0419

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 568.6710 139.1143 551.3927 1084.4683 0.5244 0.3126 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6762 5.5481 496.0190 487.1621 554.9116 0.0269 0.4237

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 564.4603 0.0000 564.4603 1084.8628 0.5203 0.3444 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5455 496.4052 487.1236 0.0000 0.0600 0.0397 0.3111

NASA/TM—2013-218094 H–157
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8773 6.6544 1.2878 522.0181 39.7491 219.1088 1.6985

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 247217.250 0.565 896.160 686730.188 0.139987E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.648 EfDer = 1.000 SH = 0.160264E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 6.654 522.018 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.136 WH2O = 0.010 lbm/sec H2O = 0.080g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.158 3663.511 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124270.961 50329.504 1.419 590.487 416.157 468.502 1.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 505.09 -0.17 505.09 0.46 0.76 656.97

 MEAN 18.08 0.00 -0.02 505.09 -0.17 505.09 0.46 0.71

 HUB 15.21 0.00 -0.02 505.09 -0.17 505.09 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.54 46.36 6.18 659.08 830.51 5.75 501.51 487.11 1.14

 MEAN 48.95 42.30 6.65 579.81 769.09 5.75 501.51 487.11 1.14

 HUB 44.01 37.84 6.17 487.82 702.32 5.75 501.51 487.11 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 583.72 299.56 500.99 1116.92 0.52 2.33 2.04 9.02

 MEAN 18.01 598.63 313.28 510.12 1112.80 0.54 2.40 2.13 7.35

 HUB 15.22 651.64 392.86 519.90 1108.98 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.92 614.22 355.35 0.55 6120.68 0.92 0.91

 MEAN 577.62 574.54 264.34 0.52 5645.27 0.92 0.91 0.91 1.45

 HUB 488.24 528.57 95.37 0.48 5983.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.09 1.22 6.73 553.57 1.06 526.19 501.62 0.55

 MEAN 7.97 1.20 6.56 551.12 1.06 522.32 500.59 0.61

 HUB 8.05 1.21 6.39 552.87 1.06 518.73 501.43 0.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.88 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.56 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.08 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 666.6125 314.1573 587.9434 1106.8849 0.6022 -0.1787 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0218 6.2965 516.8093 501.2869 0.7218 28.1170 30.6000 2.4830

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 554.9428 117.6518 542.3279 1118.5668 0.4961 0.1455 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9997 6.7754 527.7711 501.0569 491.5697 0.0250 0.2990

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 579.9785 0.0000 579.9785 1116.1204 0.5196 0.2066 0.5911

NASA/TM—2013-218094 H–158
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6529 525.4903 501.0533 0.0000 0.0600 0.0387 0.0625

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 7.9794 1.1991 552.5200 30.5035 248.4767 1.9262

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189806.906 0.443 688.048 616939.813 0.168387E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.805 EfDer = 1.000 SH = 0.180922E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 7.979 552.520 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.135 WH2O = 0.012 lbm/sec H2O = 0.104g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.965 3560.954 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107742.344 50329.098 1.528 545.479 357.066 424.468 1.189

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 474.04 -0.16 474.04 0.42 0.71 623.66

 MEAN 17.74 0.00 -0.02 474.04 -0.16 474.04 0.42 0.66

 HUB 15.05 0.00 -0.02 474.04 -0.16 474.04 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.64 46.36 7.28 643.69 799.54 7.07 534.46 500.97 0.48

 MEAN 50.21 43.40 6.81 568.91 740.65 7.07 534.46 500.97 0.48

 HUB 45.53 38.84 6.69 482.69 676.66 7.07 534.46 500.97 0.48

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 560.18 298.17 474.24 1149.86 0.49 2.26 1.98 8.75

 MEAN 17.51 573.40 310.95 481.77 1146.15 0.50 2.34 2.07 6.78

 HUB 14.85 623.36 385.48 489.88 1142.68 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.35 581.88 337.18 0.51 5910.06 0.92 0.91

 MEAN 561.47 543.01 250.52 0.47 5446.59 0.92 0.91 0.91 1.48

 HUB 476.27 498.22 90.79 0.44 5726.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.54 1.20 8.13 582.98 1.06 557.76 513.42 0.27

 MEAN 9.41 1.18 7.95 580.59 1.05 554.17 512.51 0.30

 HUB 9.49 1.19 7.77 582.03 1.05 550.81 513.13 0.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.16 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.84 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.20 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 633.4512 312.9921 550.7236 1141.4048 0.5550 -0.1640 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4619 7.6955 549.6346 513.0459 0.3320 29.6108 31.5000 1.8892

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.4478 115.9317 518.6488 1151.2759 0.4616 0.1491 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4427 8.1746 559.1786 512.8990 451.3937 0.0225 0.3218

 

NASA/TM—2013-218094 H–159
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 542.2184 0.0000 542.2184 1150.2898 0.4714 0.2320 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1053 558.2524 512.8662 0.0000 0.0600 0.0378 0.1038

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8813 9.4193 1.1804 581.8654 29.3474 238.0829 1.8456

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182697.922 0.453 662.278 591207.375 0.192073E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.090 EfDer = 1.000 SH = 0.210894E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 9.419 581.865 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.133 WH2O = 0.014 lbm/sec H2O = 0.138g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.030 3469.997 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94671.078 50328.504 1.654 513.330 310.438 395.845 1.275

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 442.62 -0.15 442.62 0.38 0.66 583.20

 MEAN 16.97 0.00 -0.02 442.62 -0.15 442.62 0.38 0.61

 HUB 14.32 0.00 -0.02 442.62 -0.15 442.62 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.38 46.36 8.02 617.71 760.04 8.53 566.13 512.83 0.25

 MEAN 50.89 43.80 7.09 544.29 701.66 8.53 566.13 512.83 0.25

 HUB 46.07 37.84 8.23 459.27 637.95 8.53 566.13 512.83 0.25

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 530.64 288.94 445.08 1179.87 0.45 2.16 1.89 8.34

 MEAN 16.57 540.49 296.74 451.74 1176.24 0.46 2.24 1.97 6.35

 HUB 13.89 583.79 360.88 458.89 1172.78 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 605.52 546.19 316.59 0.46 5458.05 0.92 0.91

 MEAN 531.56 509.13 234.82 0.43 4920.73 0.92 0.91 0.91 1.50

 HUB 445.48 466.62 84.60 0.40 5014.83 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.02 1.17 9.61 609.98 1.05 587.37 523.33 0.16

 MEAN 10.85 1.15 9.41 607.21 1.04 583.75 522.35 0.17

 HUB 10.88 1.16 9.21 607.70 1.04 580.33 522.56 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.99 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.30 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.18 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 582.1722 298.4095 499.8763 1173.4929 0.4961 -0.1145 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9031 9.2352 581.0850 522.7441 0.1842 30.8358 32.4000 1.5642

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 494.8693 110.9847 482.2634 1181.0870 0.4190 0.1700 2.2705

 

NASA/TM—2013-218094 H–160
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8881 9.6646 588.6333 522.6514 432.2457 0.0199 0.3418

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 490.8081 0.0000 490.8081 1181.3777 0.4155 0.2549 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6602 588.9559 522.5999 0.0000 0.0600 0.0374 0.1671

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8817 10.8616 1.1531 608.2917 26.4296 241.3040 1.8706

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 164628.641 0.449 596.777 586009.438 0.222703E-03

 

Melt Ratio at Stator LE, Throat, TE

0.40180E-01 0.48859E-01 0.69882E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.294 EfDer = 1.000 SH = 0.237854E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.147 3675.210 10.862 608.291 1.000 1.000 0.980

 W Kg/sec = 29.158 Wdry = 64.131 WH2O = 0.015 lbm/sec H2O = 0.174g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.015 3393.785 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84414.961 50327.969 1.851 509.668 275.284 384.739 1.398

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 397.51 -0.14 397.51 0.33 0.60 542.56

 MEAN 15.91 0.00 -0.02 397.51 -0.14 397.51 0.33 0.54

 HUB 13.07 0.00 -0.02 397.51 -0.14 397.51 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.93 47.36 8.57 587.56 709.51 10.06 595.61 522.57 0.15

 MEAN 52.09 44.80 7.29 510.37 647.01 10.06 595.61 522.57 0.15

 HUB 46.53 38.84 7.69 419.18 577.79 10.06 595.61 522.57 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.85 287.12 403.04 1207.34 0.41 2.05 1.78 7.43

 MEAN 15.50 498.04 283.40 409.54 1203.25 0.41 2.13 1.86 5.75

 HUB 12.59 529.64 327.28 416.41 1199.30 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 575.38 495.52 288.26 0.41 5153.41 0.92 0.91

 MEAN 497.04 461.92 213.65 0.38 4394.15 0.92 0.91 0.91 1.54

 HUB 403.79 423.38 76.51 0.35 4122.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.52 1.15 11.17 634.82 1.04 615.17 531.83 0.10

 MEAN 12.26 1.13 10.92 630.91 1.04 611.00 530.51 0.11

 HUB 12.17 1.12 10.67 629.51 1.03 607.00 530.06 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.47 35.57 31.50 4.07 0.93 0.44 1.40

 MEAN 34.68 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.17 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 552.5645 288.5931 471.2128 1199.4927 0.4607 -0.1926 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2900 10.6464 607.2479 530.7774 0.1192 31.4853 33.0000 1.5147

 

NASA/TM—2013-218094 H–161
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 476.2717 108.7571 463.6881 1205.6948 0.3950 0.0818 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2663 11.0312 613.5446 530.6893 410.5396 0.0369 0.3534

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 461.6923 0.0000 461.6923 1206.7394 0.3826 0.2775 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1025 614.6416 530.6838 0.0000 0.0600 0.0374 0.1326

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8832 12.2656 1.1293 631.7411 23.4547 249.0926 1.9310

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 146188.078 0.442 529.930 596961.438 0.247301E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14334E+00 0.15473E+00 0.18498E+00

 trTOT = 1.3099 Tt4 = 631.7411 T1 = 482.2704

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 930538.75 3373.1919 175.9648 2.3738 0.8684 5.6575 1.3099 37.3740

NASA/TM—2013-218094 H–162
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.995 EfDer = 0.999 SH = 0.121864E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 5.167 482.270 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.027 WH2O = 0.008 lbm/sec H2O = 0.053g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.914 3779.859 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140707.375 49457.773 1.643 831.557 506.171 619.754 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 406.10 -0.14 406.10 0.39 0.73 680.47

 MEAN 17.06 0.00 -0.02 406.10 -0.14 406.10 0.39 0.64

 HUB 12.51 0.00 -0.02 406.10 -0.14 406.10 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.25 50.47 7.78 656.16 771.79 4.67 469.01 465.19 2.71

 MEAN 53.20 47.20 6.00 542.62 677.87 4.67 469.01 465.19 2.71

 HUB 44.43 38.62 5.81 397.90 568.64 4.67 469.01 465.19 2.71

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 641.89 370.98 523.83 1076.01 0.60 7.29 6.52 16.04

 MEAN 18.04 675.62 409.09 537.69 1070.51 0.63 7.43 6.80 12.53

 HUB 15.00 776.63 533.18 564.69 1060.91 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.16 596.43 285.19 0.55 7656.14 0.92 0.91

 MEAN 573.66 562.31 164.57 0.53 7380.67 0.92 0.91 0.91 1.34

 HUB 477.09 567.47 56.08 0.53 7999.43 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 521.43 1.08 488.30 487.12 1.47

 MEAN 6.64 1.28 5.09 520.02 1.08 483.32 486.53 1.74

 HUB 6.77 1.31 4.76 523.19 1.08 474.69 488.49 2.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.31 28.56 24.20 4.36 0.93 0.36 1.80

 MEAN 37.26 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.36 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 713.7106 408.2913 585.3896 1067.4764 0.6686 -0.0723 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6863 4.9718 480.5901 487.3879 1.9337 34.8946 35.4000 0.5054

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 556.5621 136.1521 539.6517 1085.1464 0.5129 0.3214 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6593 5.5775 496.6411 486.9215 554.9116 0.0263 0.4307

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 552.2631 0.0000 552.2631 1085.5403 0.5087 0.3528 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5767 497.0268 486.8884 0.0000 0.0600 0.0381 0.3209

NASA/TM—2013-218094 H–163
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8798 6.6397 1.2850 521.5445 39.2756 217.0037 1.6822

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244275.156 0.567 870.144 672722.125 0.141389E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.990 EfDer = 1.000 SH = 0.162418E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 6.640 521.544 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.024 WH2O = 0.010 lbm/sec H2O = 0.081g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.939 3634.774 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121765.500 49456.988 1.441 590.487 409.663 468.502 1.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 494.91 -0.17 494.91 0.45 0.75 651.81

 MEAN 18.08 0.00 -0.02 494.91 -0.17 494.91 0.45 0.70

 HUB 15.21 0.00 -0.02 494.91 -0.17 494.91 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.87 46.36 6.51 653.62 819.98 5.78 501.86 486.88 1.14

 MEAN 49.29 42.30 6.99 575.00 758.79 5.78 501.86 486.88 1.14

 HUB 44.36 37.84 6.52 483.77 692.20 5.78 501.86 486.88 1.14

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 576.37 301.05 491.50 1117.03 0.52 2.33 2.04 9.02

 MEAN 18.01 590.64 313.65 500.48 1112.89 0.53 2.40 2.13 7.35

 HUB 15.22 642.58 390.76 510.11 1109.03 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 649.48 602.48 348.43 0.54 6150.96 0.92 0.91

 MEAN 572.83 563.61 259.18 0.51 5651.86 0.92 0.91 0.91 1.46

 HUB 484.19 518.59 93.43 0.47 5951.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.07 1.21 6.74 552.99 1.06 526.29 501.38 0.56

 MEAN 7.94 1.20 6.57 550.44 1.06 522.40 500.31 0.62

 HUB 8.02 1.21 6.40 551.97 1.06 518.78 501.06 0.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.49 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.07 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.45 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 656.1992 314.5280 575.9075 1107.3002 0.5926 -0.1742 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9939 6.3214 517.1979 500.9830 0.7247 28.6409 30.6000 1.9591

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 543.8175 115.2932 531.4555 1118.8447 0.4861 0.1570 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9736 6.7976 528.0350 500.7610 491.5697 0.0241 0.3064

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 567.9688 0.0000 567.9688 1116.5325 0.5087 0.2149 0.5911

NASA/TM—2013-218094 H–164
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6808 525.8796 500.7564 0.0000 0.0600 0.0379 0.0757

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 7.9538 1.1979 551.8012 30.2584 245.3979 1.9023

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188283.281 0.446 670.693 604122.313 0.170870E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.098 EfDer = 1.000 SH = 0.183868E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 7.954 551.801 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.023 WH2O = 0.012 lbm/sec H2O = 0.106g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.159 3533.717 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105745.320 49456.570 1.551 545.479 351.781 424.468 1.207

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 465.26 -0.16 465.26 0.41 0.70 618.89

 MEAN 17.74 0.00 -0.02 465.26 -0.16 465.26 0.41 0.65

 HUB 15.05 0.00 -0.02 465.26 -0.16 465.26 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.92 46.36 7.56 638.35 790.04 7.08 534.41 500.68 0.49

 MEAN 50.50 43.40 7.10 564.19 731.41 7.08 534.41 500.68 0.49

 HUB 45.82 38.84 6.98 478.68 667.65 7.08 534.41 500.68 0.49

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 553.61 298.93 465.97 1149.55 0.48 2.26 1.98 8.75

 MEAN 17.51 566.27 310.78 473.37 1145.83 0.49 2.34 2.07 6.78

 HUB 14.85 615.25 383.21 481.34 1142.33 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.08 571.66 331.16 0.50 5924.94 0.92 0.91

 MEAN 556.82 533.49 246.04 0.47 5443.56 0.92 0.91 0.91 1.49

 HUB 472.32 489.52 89.12 0.43 5693.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.50 1.19 8.12 582.08 1.05 557.46 513.10 0.28

 MEAN 9.37 1.18 7.94 579.62 1.05 553.86 512.16 0.30

 HUB 9.43 1.19 7.76 580.90 1.05 550.48 512.71 0.33

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.68 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.29 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.52 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 624.5403 312.8213 540.5492 1141.3019 0.5472 -0.1608 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4185 7.7030 549.5353 512.6795 0.3390 30.0584 31.5000 1.4416

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 521.7470 113.8156 509.1816 1151.0911 0.4533 0.1590 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4007 8.1796 558.9996 512.5361 451.3937 0.0219 0.3280

 

NASA/TM—2013-218094 H–165
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 532.1888 0.0000 532.1888 1150.1512 0.4627 0.2390 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1130 558.1181 512.5040 0.0000 0.0600 0.0373 0.1143

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 9.3777 1.1790 580.8654 29.0662 235.6037 1.8264

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180948.500 0.456 644.565 579694.813 0.195423E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.336 EfDer = 0.999 SH = 0.214678E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 9.378 580.865 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.021 WH2O = 0.014 lbm/sec H2O = 0.140g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.563 3444.176 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 93064.078 49455.973 1.677 513.330 306.145 395.845 1.293

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 435.11 -0.15 435.11 0.38 0.65 578.86

 MEAN 16.97 0.00 -0.02 435.11 -0.15 435.11 0.38 0.60

 HUB 14.32 0.00 -0.02 435.11 -0.15 435.11 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.62 46.36 8.26 612.59 751.51 8.52 565.66 512.47 0.26

 MEAN 51.14 43.80 7.34 539.77 693.42 8.52 565.66 512.47 0.26

 HUB 46.32 37.84 8.48 455.47 630.00 8.52 565.66 512.47 0.26

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 524.77 289.11 437.95 1179.15 0.45 2.16 1.89 8.34

 MEAN 16.57 534.15 296.22 444.49 1175.53 0.45 2.24 1.97 6.35

 HUB 13.89 576.58 358.61 451.49 1172.07 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 600.50 537.37 311.40 0.46 5461.22 0.92 0.91

 MEAN 527.15 500.90 230.94 0.43 4911.98 0.92 0.91 0.91 1.51

 HUB 441.79 459.09 83.18 0.39 4983.25 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.96 1.17 9.58 608.76 1.05 586.65 522.93 0.17

 MEAN 10.79 1.15 9.38 605.96 1.04 583.04 521.93 0.18

 HUB 10.81 1.15 9.18 606.32 1.04 579.62 522.09 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.43 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.68 27.45 23.50 3.95 0.93 0.41 1.62

 HUB 38.46 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 574.7988 297.8811 491.5898 1172.8910 0.4901 -0.1128 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8409 9.2186 580.4873 522.3145 0.1903 31.2140 32.4000 1.1860

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 486.6958 109.1516 474.2981 1180.4478 0.4123 0.1780 2.2705

 

NASA/TM—2013-218094 H–166
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8269 9.6461 587.9949 522.2230 432.2457 0.0195 0.3471

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 482.7048 0.0000 482.7048 1180.7279 0.4088 0.2607 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6415 588.3066 522.1727 0.0000 0.0600 0.0371 0.1749

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8822 10.8010 1.1518 607.0092 26.1470 239.1834 1.8541

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 162868.422 0.452 580.161 575240.938 0.226708E-03

 

Melt Ratio at Stator LE, Throat, TE

0.41421E-01 0.50140E-01 0.71233E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.496 EfDer = 0.999 SH = 0.242102E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.035 3644.727 10.801 607.008 1.000 1.000 0.980

 W Kg/sec = 28.652 Wdry = 63.019 WH2O = 0.015 lbm/sec H2O = 0.177g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.805 3369.190 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 83107.953 49455.438 1.876 509.668 271.743 384.739 1.416

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 391.35 -0.13 391.35 0.33 0.59 538.62

 MEAN 15.91 0.00 -0.02 391.35 -0.13 391.35 0.33 0.54

 HUB 13.07 0.00 -0.02 391.35 -0.13 391.35 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.12 47.36 8.76 582.69 702.03 10.03 594.72 522.15 0.15

 MEAN 52.30 44.80 7.50 506.13 639.89 10.03 594.72 522.15 0.15

 HUB 46.74 38.84 7.90 415.71 571.03 10.03 594.72 522.15 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.79 286.64 397.16 1206.22 0.41 2.05 1.78 7.43

 MEAN 15.50 492.57 282.50 403.51 1202.16 0.41 2.13 1.86 5.75

 HUB 12.59 523.46 325.16 410.21 1198.24 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 570.60 488.23 283.96 0.40 5144.77 0.92 0.91

 MEAN 492.92 455.07 210.42 0.38 4380.26 0.92 0.91 0.91 1.55

 HUB 400.44 417.06 75.28 0.35 4095.58 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.43 1.15 11.12 633.27 1.04 614.02 531.35 0.11

 MEAN 12.18 1.13 10.87 629.37 1.04 609.90 530.03 0.12

 HUB 12.09 1.12 10.62 627.91 1.03 605.93 529.55 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.82 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 35.00 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.40 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 545.9414 287.6828 463.9942 1198.5315 0.4555 -0.1906 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2068 10.6075 606.2706 530.2855 0.1239 31.7995 33.0000 1.2005

 

NASA/TM—2013-218094 H–167
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 468.9604 107.0875 456.5700 1204.7094 0.3893 0.0899 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1847 10.9910 612.5381 530.1994 410.5396 0.0362 0.3577

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 454.7002 0.0000 454.7002 1205.7153 0.3771 0.2823 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0590 613.5947 530.1933 0.0000 0.0600 0.0371 0.1397

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8835 12.1835 1.1280 630.1803 23.1765 247.3121 1.9171

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 144452.453 0.444 514.561 586591.063 0.251739E-03

 

Melt Ratio at Stator LE, Throat, TE

0.14455E+00 0.15596E+00 0.18618E+00

 trTOT = 1.3067 Tt4 = 630.1803 T1 = 482.2704

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 920827.81 3280.1248 172.9144 2.3578 0.8699 5.9955 1.3067 37.3740

NASA/TM—2013-218094 H–168
 50μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.966 EfDer = 0.985 SH = 0.952686E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.936 3973.478 5.167 482.273 1.000 1.000 0.980

 W Kg/sec = 33.607 Wdry = 73.929 WH2O = 0.007 lbm/sec H2O = 0.040g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.819 4120.799 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171028.000 58011.832 1.401 831.557 593.699 619.754 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 493.61 -0.17 493.61 0.47 0.83 741.85

 MEAN 17.06 0.00 -0.02 493.61 -0.17 493.61 0.47 0.74

 HUB 12.51 0.00 -0.02 493.61 -0.17 493.61 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.40 50.47 4.93 715.35 869.26 4.45 462.68 465.19 2.69

 MEAN 50.17 47.20 2.97 591.56 770.58 4.45 462.68 465.19 2.69

 HUB 41.32 38.62 2.70 433.79 657.25 4.45 462.68 465.19 2.69

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 741.43 362.64 646.69 1066.63 0.70 7.29 6.52 16.04

 MEAN 18.04 787.14 421.45 664.80 1061.11 0.74 7.43 6.80 12.53

 HUB 15.00 928.97 591.97 715.93 1047.11 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.35 736.62 352.70 0.69 7484.86 0.92 0.90

 MEAN 625.40 695.38 203.95 0.66 7604.25 0.92 0.90 0.90 1.21

 HUB 520.13 719.53 71.84 0.69 8881.64 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 524.02 1.09 479.81 488.37 1.42

 MEAN 6.81 1.32 4.75 524.68 1.09 474.86 488.85 1.69

 HUB 7.12 1.38 4.29 531.81 1.10 462.41 493.05 2.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.28 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.37 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.59 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 850.0022 420.6354 738.6268 1054.2488 0.8063 -0.1058 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8829 4.5077 468.7310 490.1416 2.1166 29.6608 35.4000 5.7392

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 691.6396 169.1962 670.6251 1076.0936 0.6427 0.2316 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8127 5.1766 488.3661 489.3766 554.9116 0.0412 0.3615

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 693.1349 0.0000 693.1349 1075.8868 0.6442 0.2574 1.3089

NASA/TM—2013-218094 H–169
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1191 488.2047 489.2301 0.0000 0.0600 0.0712 0.2061

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8263 6.7453 1.3054 526.8334 44.5611 237.2959 1.8395

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 277091.406 0.541 1157.744 817685.188 0.980437E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.613 EfDer = 0.990 SH = 0.100582E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.936 3973.478 6.745 526.833 1.000 1.000 0.980

 W Kg/sec = 33.607 Wdry = 73.929 WH2O = 0.007 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.387 3942.686 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149444.609 58011.707 1.242 590.487 475.357 468.502 0.986

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 607.41 -0.21 607.41 0.56 0.86 707.03

 MEAN 18.08 0.00 -0.02 607.41 -0.21 607.41 0.56 0.80

 HUB 15.21 0.00 -0.02 607.41 -0.21 607.41 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.56 46.36 3.20 712.57 936.49 5.47 497.17 489.08 0.80

 MEAN 45.91 42.30 3.61 626.87 873.02 5.47 497.17 489.08 0.80

 HUB 40.98 37.84 3.14 527.41 804.57 5.47 497.17 489.08 0.80

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 660.20 282.73 596.60 1114.62 0.59 2.33 2.04 9.02

 MEAN 18.01 680.29 308.24 606.45 1110.99 0.61 2.40 2.13 7.35

 HUB 15.22 742.66 412.88 617.31 1107.74 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.07 732.69 425.34 0.66 5777.63 0.92 0.91

 MEAN 624.50 683.96 316.26 0.62 5555.09 0.92 0.91 0.91 1.37

 HUB 527.86 627.93 114.98 0.57 6288.48 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.20 1.22 6.49 559.05 1.06 524.00 503.46 0.35

 MEAN 8.14 1.21 6.34 557.81 1.06 520.60 502.97 0.39

 HUB 8.34 1.24 6.19 561.90 1.07 517.55 504.76 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.36 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 26.94 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.78 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 779.0070 309.1008 715.0585 1100.4507 0.7079 -0.2338 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2077 5.8977 510.8023 503.8321 0.5164 23.3775 30.6000 7.2225

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 672.4756 142.5696 657.1890 1113.7714 0.6038 0.0265 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1494 6.3888 523.2289 503.5290 491.5697 0.0409 0.2243

 

NASA/TM—2013-218094 H–170
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 715.1625 0.0000 715.1625 1108.6698 0.6451 0.1029 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1354 518.4723 503.4525 0.0000 0.0600 0.0725 -0.1077

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8274 8.0898 1.1993 559.5820 32.7493 279.3593 2.1656

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 203736.063 0.406 851.250 740105.875 0.101347E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.987 EfDer = 0.992 SH = 0.102286E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.936 3973.478 8.090 559.582 1.000 1.000 0.980

 W Kg/sec = 33.607 Wdry = 73.929 WH2O = 0.008 lbm/sec H2O = 0.057g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.544 3825.578 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 128651.164 58011.668 1.335 545.479 408.510 424.468 1.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 566.04 -0.19 566.04 0.50 0.80 670.01

 MEAN 17.74 0.00 -0.02 566.04 -0.19 566.04 0.50 0.74

 HUB 15.05 0.00 -0.02 566.04 -0.19 566.04 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.88 46.36 4.52 695.93 897.21 6.82 533.83 503.30 0.27

 MEAN 47.39 43.40 3.99 615.08 836.04 6.82 533.83 503.30 0.27

 HUB 42.69 38.84 3.85 521.86 770.03 6.82 533.83 503.30 0.27

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 630.09 285.81 561.54 1151.42 0.55 2.26 1.98 8.75

 MEAN 17.51 648.23 309.05 569.82 1148.05 0.56 2.34 2.07 6.78

 HUB 14.85 707.20 406.14 578.94 1144.98 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.91 690.09 401.11 0.60 5665.77 0.92 0.91

 MEAN 607.04 643.03 297.99 0.56 5413.84 0.92 0.91 0.91 1.40

 HUB 514.93 589.07 108.78 0.51 6034.18 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.70 1.20 7.93 591.16 1.06 559.25 515.77 0.14

 MEAN 9.62 1.19 7.77 589.76 1.05 555.98 515.25 0.15

 HUB 9.81 1.21 7.61 593.21 1.06 553.02 516.59 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.97 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.47 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 35.05 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 730.5021 311.0770 660.9572 1140.2396 0.6407 -0.2031 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6886 7.3749 548.5002 515.8890 0.1811 25.2038 31.5000 6.2962

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 637.5698 139.0815 622.2151 1150.8209 0.5540 0.0406 2.3726

 

NASA/TM—2013-218094 H–171
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6416 7.8469 558.7129 515.7124 451.3937 0.0342 0.2570

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 654.6458 0.0000 654.6458 1148.9648 0.5698 0.1488 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7193 556.9446 515.6229 0.0000 0.0600 0.0584 -0.0251

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8480 9.5947 1.1860 591.3751 31.7943 264.9267 2.0537

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 197882.234 0.419 826.792 700055.375 0.103079E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.569 EfDer = 0.995 SH = 0.104302E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.936 3973.478 9.595 591.375 1.000 1.000 0.980

 W Kg/sec = 33.607 Wdry = 73.928 WH2O = 0.008 lbm/sec H2O = 0.066g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.953 3721.323 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111902.813 58011.621 1.450 513.330 354.110 395.845 1.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 523.19 -0.18 523.19 0.45 0.73 625.44

 MEAN 16.97 0.00 -0.02 523.19 -0.18 523.19 0.45 0.68 

 HUB 14.32 0.00 -0.02 523.19 -0.18 523.19 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.93 46.36 5.57 667.84 848.52 8.36 569.39 515.56 0.11 

 MEAN 48.37 43.80 4.57 588.46 787.54 8.36 569.39 515.56 0.11

 HUB 43.51 37.84 5.67 496.55 721.43 8.36 569.39 515.56 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 593.26 281.83 522.04 1185.30 0.50 2.16 1.89 8.34

 MEAN 16.57 607.81 298.02 529.74 1181.76 0.51 2.24 1.97 6.35

 HUB 13.89 659.49 381.31 538.08 1178.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.67 641.51 372.84 0.54 5324.41 0.92 0.91

 MEAN 574.70 597.64 276.68 0.51 4942.43 0.92 0.91 0.91 1.42

 HUB 481.64 547.35 100.33 0.46 5298.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.28 1.18 9.53 621.03 1.05 592.76 526.23 0.07

 MEAN 11.15 1.16 9.33 618.91 1.05 589.23 525.50 0.07

 HUB 11.27 1.17 9.14 620.89 1.05 585.96 526.21 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.36 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.36 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.32 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 662.0292 299.6975 590.3084 1177.5266 0.5622 -0.1357 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2171 9.0753 585.0828 525.9611 0.0779 26.9167 32.4000 5.4833

 

NASA/TM—2013-218094 H–172
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 585.1414 131.2301 570.2360 1185.2533 0.4937 0.0808 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1826 9.4867 592.7823 525.8575 432.2457 0.0282 0.2864

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 580.4775 0.0000 580.4775 1185.6589 0.4896 0.1899 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4820 593.2222 525.7841 0.0000 0.0600 0.0467 0.0783

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8636 11.1472 1.1618 620.2766 28.9032 265.2833 2.0565

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 179989.094 0.420 752.031 685951.250 0.105307E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.157 EfDer = 0.997 SH = 0.107318E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.936 3973.478 11.147 620.276 1.000 1.000 0.980

 W Kg/sec = 33.607 Wdry = 73.928 WH2O = 0.008 lbm/sec H2O = 0.078g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.621 3633.593 1.380 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98503.867 58011.551 1.633 509.668 312.178 384.739 1.232

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 463.85 -0.16 463.85 0.39 0.66 580.89

 MEAN 15.91 0.00 -0.02 463.85 -0.16 463.85 0.39 0.60

 HUB 13.07 0.00 -0.02 463.85 -0.16 463.85 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.87 47.36 6.51 635.25 786.70 10.06 603.00 525.75 0.06

 MEAN 49.96 44.80 5.16 551.79 720.97 10.06 603.00 525.75 0.06

 HUB 44.35 38.84 5.51 453.20 648.61 10.06 603.00 525.75 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 547.97 287.08 466.75 1216.81 0.45 2.05 1.78 7.43

 MEAN 15.50 555.66 288.74 474.75 1212.48 0.46 2.13 1.86 5.75

 HUB 12.59 594.90 347.03 483.20 1208.35 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.07 574.52 334.99 0.47 5153.16 0.92 0.91

 MEAN 537.38 535.92 248.64 0.44 4477.34 0.92 0.91 0.91 1.47

 HUB 436.56 491.42 89.53 0.41 4371.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.95 1.16 11.29 648.96 1.05 624.86 535.38 0.04

 MEAN 12.70 1.14 11.02 645.20 1.04 620.42 534.16 0.04

 HUB 12.66 1.14 10.75 644.61 1.04 616.20 533.97 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.59 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.31 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.69 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 623.9005 294.0360 550.2677 1207.1301 0.5168 -0.2161 2.0437

 

NASA/TM—2013-218094 H–173
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7383 10.6418 615.0202 534.4568 0.0437 28.1179 33.0000 4.8821

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 557.5737 127.3224 542.8420 1213.2919 0.4596 -0.0137 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6867 10.9973 621.3078 534.3389 410.5396 0.0495 0.3067

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 538.9139 0.0000 538.9139 1214.8628 0.4436 0.2236 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1105 622.9525 534.3510 0.0000 0.0600 0.0447 0.0509

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8706 12.6951 1.1389 646.2566 25.9819 269.4713 2.0889

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161901.438 0.418 676.457 691022.563 0.108866E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3400 Tt4 = 646.2566 T1 = 482.2730

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1020600.19 4264.2739 202.8189 2.4569 0.8274 2.9658 1.3400 37.3740

NASA/TM—2013-218094 H–174
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.308 EfDer = 0.998 SH = 0.966183E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.275 3704.939 5.167 482.272 1.000 1.000 0.980

 W Kg/sec = 29.670 Wdry = 65.269 WH2O = 0.006 lbm/sec H2O = 0.041g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 179.060 3842.304 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146640.750 51215.969 1.586 831.557 524.152 619.754 1.182

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 423.23 -0.15 423.23 0.40 0.75 691.71

 MEAN 17.06 0.00 -0.02 423.23 -0.15 423.23 0.40 0.66

 HUB 12.51 0.00 -0.02 423.23 -0.15 423.23 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.61 50.47 7.14 667.00 790.07 4.63 467.87 465.10 2.24

 MEAN 52.51 47.20 5.31 551.58 695.36 4.63 467.87 465.10 2.24

 HUB 43.71 38.62 5.09 404.47 585.52 4.63 467.87 465.10 2.24

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 659.83 369.04 546.98 1074.44 0.61 7.29 6.52 16.04

 MEAN 18.04 695.98 411.10 561.59 1068.93 0.65 7.43 6.80 12.53

 HUB 15.00 803.65 543.76 591.75 1058.76 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.00 622.87 297.96 0.58 7616.30 0.92 0.91

 MEAN 583.14 587.35 172.03 0.55 7417.17 0.92 0.91 0.91 1.31

 HUB 484.98 594.66 58.79 0.56 8158.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.22 521.88 1.08 486.87 487.18 1.14

 MEAN 6.67 1.29 5.03 520.84 1.08 481.89 486.76 1.35

 HUB 6.84 1.32 4.69 524.69 1.09 472.76 489.00 1.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.01 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.21 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.58 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 737.6886 410.3054 613.0530 1065.3956 0.6924 -0.0775 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7224 4.8968 478.7107 487.6383 1.5115 33.7937 35.4000 1.6063

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 581.4192 142.2329 563.7535 1083.6759 0.5365 0.3032 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6911 5.5136 495.2875 487.2287 554.9116 0.0278 0.4162

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 577.3548 0.0000 577.3548 1084.0660 0.5326 0.3351 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5087 495.6692 487.1718 0.0000 0.0600 0.0417 0.3003

NASA/TM—2013-218094 H–175
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8741 6.6665 1.2902 522.4689 40.1975 221.3266 1.7157

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 249979.188 0.562 922.109 701089.438 0.100180E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.283 EfDer = 1.000 SH = 0.103573E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.275 3704.939 6.667 522.469 1.000 1.000 0.980

 W Kg/sec = 29.670 Wdry = 65.268 WH2O = 0.007 lbm/sec H2O = 0.051g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.456 3691.552 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126899.133 51215.832 1.396 590.487 422.872 468.502 1.108

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 515.77 -0.18 515.77 0.47 0.77 662.00

 MEAN 18.08 0.00 -0.02 515.77 -0.18 515.77 0.47 0.72

 HUB 15.21 0.00 -0.02 515.77 -0.18 515.77 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.19 46.36 5.83 664.42 841.25 5.73 501.08 487.11 0.74

 MEAN 48.58 42.30 6.28 584.50 779.66 5.73 501.08 487.11 0.74

 HUB 43.65 37.84 5.81 491.77 712.76 5.73 501.08 487.11 0.74

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 591.35 297.53 511.05 1116.69 0.53 2.33 2.04 9.02

 MEAN 18.01 606.93 312.49 520.30 1112.61 0.55 2.40 2.13 7.35

 HUB 15.22 661.02 394.75 530.21 1108.84 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.21 626.67 362.69 0.56 6079.14 0.92 0.91

 MEAN 582.29 586.09 269.80 0.53 5631.17 0.92 0.91 0.91 1.44

 HUB 492.19 539.09 97.43 0.49 6012.05 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.71 554.07 1.06 525.96 501.62 0.35

 MEAN 7.99 1.20 6.54 551.74 1.06 522.13 500.64 0.39

 HUB 8.09 1.21 6.38 553.72 1.06 518.59 501.55 0.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.21 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 30.99 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.67 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 677.5884 313.3686 600.7713 1106.3223 0.6125 -0.1838 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0443 6.2637 516.2738 501.3093 0.4630 27.5470 30.6000 3.0530

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 566.8654 120.1795 553.9794 1118.1309 0.5070 0.1326 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0199 6.7439 527.3484 501.1343 491.5697 0.0261 0.2907

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 593.0331 0.0000 593.0331 1115.5181 0.5316 0.1964 0.5911

NASA/TM—2013-218094 H–176
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6134 524.9118 501.1094 0.0000 0.0600 0.0406 0.0465

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8766 7.9979 1.1997 553.1774 30.7095 251.8824 1.9526

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191053.172 0.438 704.746 630191.125 0.104638E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.476 EfDer = 1.000 SH = 0.106159E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.275 3704.939 7.998 553.177 1.000 1.000 0.980

 W Kg/sec = 29.670 Wdry = 65.268 WH2O = 0.007 lbm/sec H2O = 0.061g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.897 3587.624 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109888.992 51215.781 1.504 545.479 362.707 424.468 1.170

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 483.49 -0.17 483.49 0.43 0.72 628.33

 MEAN 17.74 0.00 -0.02 483.49 -0.17 483.49 0.43 0.67

 HUB 15.05 0.00 -0.02 483.49 -0.17 483.49 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.32 46.36 6.96 648.90 809.35 7.06 534.39 501.03 0.28

 MEAN 49.88 43.40 6.48 573.52 750.25 7.06 534.39 501.03 0.28

 HUB 45.19 38.84 6.35 486.59 686.07 7.06 534.39 501.03 0.28

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 567.07 296.74 483.24 1150.02 0.49 2.26 1.98 8.75

 MEAN 17.51 580.89 310.60 490.87 1146.33 0.51 2.34 2.07 6.78

 HUB 14.85 631.86 387.48 499.10 1142.89 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.49 593.03 343.75 0.52 5881.71 0.92 0.91 

 MEAN 566.02 553.35 255.42 0.48 5440.49 0.92 0.91 0.91 1.47

 HUB 480.13 507.63 92.65 0.44 5756.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.56 1.20 8.12 583.74 1.06 557.90 513.50 0.15

 MEAN 9.44 1.18 7.94 581.45 1.05 554.33 512.62 0.17

 HUB 9.53 1.19 7.76 583.09 1.05 551.01 513.29 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.55 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.32 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.82 10.52 6.50 4.02 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 642.9495 312.6380 561.8198 1141.3271 0.5633 -0.1678 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4939 7.6745 549.5468 513.1376 0.1896 29.0948 31.5000 2.4052

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 542.1099 118.2576 529.0541 1151.2585 0.4709 0.1373 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4731 8.1539 559.1474 513.0294 451.3937 0.0233 0.3144

 

NASA/TM—2013-218094 H–177
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 553.2624 0.0000 553.2624 1150.2186 0.4810 0.2237 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0816 558.1689 512.9846 0.0000 0.0600 0.0386 0.0913

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 9.4490 1.1814 582.7596 29.5835 240.9783 1.8680

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184124.313 0.449 679.187 603132.563 0.107319E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.800 EfDer = 1.000 SH = 0.109334E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.275 3704.939 9.449 582.759 1.000 1.000 0.980

 W Kg/sec = 29.670 Wdry = 65.268 WH2O = 0.007 lbm/sec H2O = 0.071g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.637 3495.380 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96426.422 51215.715 1.629 513.330 315.126 395.845 1.256

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 450.83 -0.16 450.83 0.39 0.66 587.47

 MEAN 16.97 0.00 -0.02 450.83 -0.16 450.83 0.39 0.61

 HUB 14.32 0.00 -0.02 450.83 -0.16 450.83 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.10 46.36 7.74 622.71 768.90 8.52 566.43 512.94 0.13

 MEAN 50.60 43.80 6.80 548.69 710.27 8.52 566.43 512.94 0.13

 HUB 45.77 37.84 7.93 462.99 646.33 8.52 566.43 512.94 0.13

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 536.81 288.10 452.95 1180.41 0.45 2.16 1.89 8.34

 MEAN 16.57 547.20 296.77 459.73 1176.78 0.47 2.24 1.97 6.35

 HUB 13.89 591.41 362.86 467.01 1173.33 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 610.42 555.92 322.32 0.47 5442.38 0.92 0.91

 MEAN 535.86 518.19 239.09 0.44 4921.33 0.92 0.91 0.91 1.49

 HUB 449.09 474.90 86.23 0.40 5042.38 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.06 1.17 9.61 611.03 1.05 587.88 523.47 0.08

 MEAN 10.90 1.15 9.41 608.32 1.04 584.27 522.51 0.09

 HUB 10.94 1.16 9.21 608.95 1.04 580.85 522.75 0.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.46 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 32.84 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.85 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 590.0690 298.4431 509.0316 1173.9005 0.5027 -0.1166 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9491 9.2341 581.4714 522.8937 0.0920 30.3829 32.4000 2.0171

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 503.9678 113.0252 491.1301 1181.5094 0.4265 0.1602 2.2705

 

NASA/TM—2013-218094 H–178
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9329 9.6630 589.0360 522.8282 432.2457 0.0205 0.3353

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 499.8349 0.0000 499.8349 1181.8126 0.4229 0.2476 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6588 589.3713 522.7728 0.0000 0.0600 0.0380 0.1575

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 10.9057 1.1542 609.4313 26.6734 243.8733 1.8905

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 166095.219 0.446 612.683 597163.188 0.110937E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.045 EfDer = 1.000 SH = 0.113783E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.275 3704.939 10.906 609.431 1.000 1.000 0.980

 W Kg/sec = 29.670 Wdry = 65.267 WH2O = 0.007 lbm/sec H2O = 0.083g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.370 3418.037 1.380 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 85863.016 51215.629 1.825 509.668 279.233 384.739 1.378

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 404.32 -0.14 404.32 0.34 0.60 546.43

 MEAN 15.91 0.00 -0.02 404.32 -0.14 404.32 0.34 0.55

 HUB 13.07 0.00 -0.02 404.32 -0.14 404.32 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.69 47.36 8.33 592.32 717.27 10.08 596.31 522.75 0.07

 MEAN 51.84 44.80 7.04 514.49 654.47 10.08 596.31 522.75 0.07

 HUB 46.27 38.84 7.43 422.58 584.95 10.08 596.31 522.75 0.07

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.14 286.95 409.64 1208.27 0.41 2.05 1.78 7.43

 MEAN 15.50 503.82 283.80 416.29 1204.15 0.42 2.13 1.86 5.75

 HUB 12.59 536.27 329.23 423.31 1200.18 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 580.03 503.69 293.08 0.42 5150.40 0.92 0.91

 MEAN 501.06 469.57 217.26 0.39 4400.43 0.92 0.91 0.91 1.53

 HUB 407.06 430.40 77.83 0.36 4146.78 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.58 1.15 11.20 636.17 1.04 616.09 532.05 0.05

 MEAN 12.32 1.13 10.94 632.27 1.04 611.90 530.73 0.05

 HUB 12.24 1.12 10.69 630.96 1.04 607.87 530.30 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.01 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.28 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.87 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 559.6825 289.0034 479.2928 1200.2465 0.4663 -0.1950 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3524 10.6632 607.9912 530.9885 0.0553 31.0891 33.0000 1.9109

 

NASA/TM—2013-218094 H–179
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.5247 110.6416 471.7231 1206.4475 0.4016 0.0714 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3268 11.0466 614.2899 530.9190 410.5396 0.0378 0.3478

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 469.5818 0.0000 469.5818 1207.5394 0.3889 0.2713 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1215 615.4358 530.9164 0.0000 0.0600 0.0379 0.1235

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8825 12.3267 1.1303 633.1313 23.7019 251.3382 1.9484

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 147674.281 0.439 544.733 607683.250 0.116062E-03

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.18508E-02

 trTOT = 1.3128 Tt4 = 633.1313 T1 = 482.2723

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 938926.13 3463.4583 179.0596 2.3856 0.8662 5.3085 1.3128 37.3740

NASA/TM—2013-218094 H–180
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.650 EfDer = 0.999 SH = 0.968042E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.161 3675.098 5.167 482.272 1.000 1.000 0.980

 W Kg/sec = 29.164 Wdry = 64.155 WH2O = 0.006 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 176.004 3811.357 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143673.188 50341.980 1.614 831.557 515.208 619.754 1.203

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 414.66 -0.14 414.66 0.39 0.74 686.14

 MEAN 17.06 0.00 -0.02 414.66 -0.14 414.66 0.39 0.65

 HUB 12.51 0.00 -0.02 414.66 -0.14 414.66 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.93 50.47 7.46 661.63 780.95 4.65 468.45 465.09 2.20

 MEAN 52.85 47.20 5.65 547.14 686.63 4.65 468.45 465.09 2.20

 HUB 44.07 38.62 5.45 401.21 577.09 4.65 468.45 465.09 2.20

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 650.80 370.11 535.32 1075.26 0.61 7.29 6.52 16.04

 MEAN 18.04 685.74 410.15 549.56 1069.75 0.64 7.43 6.80 12.53

 HUB 15.00 790.03 538.48 578.09 1059.87 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.63 609.55 291.52 0.57 7638.22 0.92 0.91 

 MEAN 578.44 574.75 168.29 0.54 7399.91 0.92 0.91 0.91 1.33

 HUB 481.07 580.93 57.41 0.55 8078.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 521.67 1.08 487.61 487.06 1.11

 MEAN 6.65 1.29 5.06 520.44 1.08 482.63 486.54 1.32

 HUB 6.80 1.32 4.72 523.94 1.09 473.75 488.59 1.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.66 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.73 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.97 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 725.5797 409.3532 599.0791 1066.4757 0.6804 -0.0748 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7049 4.9356 479.6833 487.3859 1.4651 34.3450 35.4000 1.0550

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 568.8643 139.1616 551.5801 1084.4495 0.5246 0.3124 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6759 5.5471 495.9965 487.0002 554.9116 0.0270 0.4235

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 564.6562 0.0000 564.6562 1084.8446 0.5205 0.3441 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5444 496.3828 486.9492 0.0000 0.0600 0.0398 0.3108

NASA/TM—2013-218094 H–181
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8773 6.6540 1.2877 522.0164 39.7451 219.1623 1.6989

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 247168.000 0.565 896.181 686901.625 0.100458E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.639 EfDer = 1.000 SH = 0.103965E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.161 3675.098 6.654 522.016 1.000 1.000 0.980

 W Kg/sec = 29.164 Wdry = 64.154 WH2O = 0.007 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.197 3663.406 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124309.094 50341.840 1.419 590.487 416.259 468.502 1.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 505.25 -0.17 505.25 0.46 0.76 656.95

 MEAN 18.08 0.00 -0.02 505.25 -0.17 505.25 0.46 0.71

 HUB 15.21 0.00 -0.02 505.25 -0.17 505.25 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.53 46.36 6.17 659.06 830.58 5.75 501.49 486.90 0.74

 MEAN 48.94 42.30 6.64 579.79 769.18 5.75 501.49 486.90 0.74

 HUB 44.00 37.84 6.16 487.80 702.42 5.75 501.49 486.90 0.74

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 583.79 299.42 501.16 1116.90 0.52 2.33 2.04 9.02

 MEAN 18.01 598.72 313.17 510.29 1112.79 0.54 2.40 2.13 7.35

 HUB 15.22 651.74 392.81 520.06 1108.97 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.90 614.43 355.48 0.55 6117.68 0.92 0.91

 MEAN 577.60 574.73 264.43 0.52 5643.29 0.92 0.91 0.91 1.45

 HUB 488.22 528.74 95.41 0.48 5982.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.09 1.22 6.73 553.56 1.06 526.16 501.42 0.35

 MEAN 7.97 1.20 6.56 551.12 1.06 522.30 500.38 0.39

 HUB 8.05 1.21 6.39 552.86 1.06 518.72 501.19 0.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.86 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.54 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.06 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 666.7491 314.0470 588.1572 1106.8654 0.6024 -0.1788 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0209 6.2950 516.7814 501.0312 0.4587 28.1000 30.6000 2.5000

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 555.1581 117.6975 542.5383 1118.5450 0.4963 0.1451 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9987 6.7737 527.7406 500.8651 491.5697 0.0250 0.2987

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 580.2136 0.0000 580.2136 1116.0957 0.5199 0.2063 0.5911

NASA/TM—2013-218094 H–182
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6510 525.4570 500.8421 0.0000 0.0600 0.0387 0.0620

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 7.9785 1.1990 552.5135 30.4982 248.5739 1.9269

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189739.313 0.442 687.956 617099.250 0.105080E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.795 EfDer = 1.000 SH = 0.106706E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.161 3675.098 7.978 552.513 1.000 1.000 0.980

 W Kg/sec = 29.164 Wdry = 64.154 WH2O = 0.007 lbm/sec H2O = 0.061g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.007 3560.866 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 107780.055 50341.789 1.527 545.479 357.171 424.468 1.188

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 474.21 -0.16 474.21 0.42 0.71 623.65

 MEAN 17.74 0.00 -0.02 474.21 -0.16 474.21 0.42 0.66

 HUB 15.05 0.00 -0.02 474.21 -0.16 474.21 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.63 46.36 7.27 643.67 799.62 7.07 534.44 500.77 0.28

 MEAN 50.19 43.40 6.79 568.90 740.75 7.07 534.44 500.77 0.28

 HUB 45.52 38.84 6.68 482.67 676.76 7.07 534.44 500.77 0.28

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 560.26 298.02 474.42 1149.85 0.49 2.26 1.98 8.75

 MEAN 17.51 573.49 310.84 481.95 1146.14 0.50 2.34 2.07 6.78

 HUB 14.85 623.47 385.43 490.05 1142.67 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.33 582.11 337.31 0.51 5907.03 0.92 0.91

 MEAN 561.46 543.22 250.62 0.47 5444.57 0.92 0.91 0.91 1.48

 HUB 476.26 498.40 90.83 0.44 5726.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.54 1.20 8.12 582.96 1.06 557.74 513.23 0.16

 MEAN 9.41 1.18 7.94 580.58 1.05 554.15 512.31 0.17

 HUB 9.48 1.19 7.77 582.03 1.05 550.79 512.91 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.14 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.82 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.19 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 633.5837 312.8758 550.9420 1141.3861 0.5551 -0.1641 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4602 7.6933 549.6033 512.8146 0.1908 29.5919 31.5000 1.9081

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.6735 115.9810 518.8690 1151.2543 0.4618 0.1486 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4411 8.1720 559.1439 512.7111 451.3937 0.0225 0.3215

 

NASA/TM—2013-218094 H–183
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 542.4531 0.0000 542.4531 1150.2671 0.4716 0.2317 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1027 558.2164 512.6671 0.0000 0.0600 0.0379 0.1033

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 9.4176 1.1804 581.8556 29.3433 238.1843 1.8464

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182629.516 0.452 662.177 591355.000 0.107927E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.078 EfDer = 1.000 SH = 0.110030E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.161 3675.098 9.418 581.855 1.000 1.000 0.980

 W Kg/sec = 29.164 Wdry = 64.154 WH2O = 0.007 lbm/sec H2O = 0.072g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.072 3469.920 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94707.070 50341.719 1.653 513.330 310.541 395.845 1.275 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 442.79 -0.15 442.79 0.38 0.66 583.19

 MEAN 16.97 0.00 -0.02 442.79 -0.15 442.79 0.38 0.61

 HUB 14.32 0.00 -0.02 442.79 -0.15 442.79 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.37 46.36 8.01 617.69 760.13 8.53 566.11 512.63 0.13

 MEAN 50.88 43.80 7.08 544.27 701.76 8.53 566.11 512.63 0.13

 HUB 46.06 37.84 8.22 459.26 638.06 8.53 566.11 512.63 0.13

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 530.71 288.78 445.26 1179.86 0.45 2.16 1.89 8.34

 MEAN 16.57 540.57 296.63 451.92 1176.23 0.46 2.24 1.97 6.35

 HUB 13.89 583.90 360.83 459.07 1172.78 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 605.51 546.42 316.73 0.46 5455.11 0.92 0.91

 MEAN 531.55 509.33 234.92 0.43 4918.81 0.92 0.91 0.91 1.50

 HUB 445.47 466.80 84.64 0.40 5014.11 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.02 1.17 9.61 609.96 1.05 587.34 523.13 0.08

 MEAN 10.85 1.15 9.41 607.20 1.04 583.73 522.14 0.09

 HUB 10.88 1.16 9.20 607.69 1.04 580.30 522.34 0.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.97 35.43 31.50 3.93 0.93 0.42 1.40

 MEAN 33.28 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.17 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 582.2895 298.2932 500.0822 1173.4807 0.4962 -0.1146 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9006 9.2323 581.0538 522.5198 0.0937 30.8156 32.4000 1.5844

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 495.0864 111.0334 482.4750 1181.0718 0.4192 0.1696 2.2705

 

NASA/TM—2013-218094 H–184
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8856 9.6613 588.5986 522.4568 432.2457 0.0199 0.3414

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 491.0261 0.0000 491.0261 1181.3636 0.4156 0.2545 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6569 588.9221 522.4028 0.0000 0.0600 0.0375 0.1667

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8817 10.8591 1.1531 608.2814 26.4276 241.4142 1.8714

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 164563.656 0.449 596.674 586145.063 0.111713E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.282 EfDer = 1.000 SH = 0.114729E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.161 3675.098 10.859 608.281 1.000 1.000 0.980

 W Kg/sec = 29.164 Wdry = 64.154 WH2O = 0.007 lbm/sec H2O = 0.084g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.056 3393.711 1.380 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84449.094 50341.625 1.851 509.668 275.385 384.739 1.397

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 397.67 -0.14 397.67 0.33 0.60 542.54

 MEAN 15.91 0.00 -0.02 397.67 -0.14 397.67 0.33 0.54

 HUB 13.07 0.00 -0.02 397.67 -0.14 397.67 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.92 47.36 8.56 587.55 709.58 10.06 595.59 522.38 0.07

 MEAN 52.08 44.80 7.28 510.35 647.10 10.06 595.59 522.38 0.07

 HUB 46.52 38.84 7.68 419.17 577.89 10.06 595.59 522.38 0.07

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.91 286.97 403.22 1207.34 0.41 2.05 1.78 7.43

 MEAN 15.50 498.11 283.29 409.72 1203.25 0.41 2.13 1.86 5.75

 HUB 12.59 529.74 327.24 416.58 1199.30 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 575.36 495.73 288.39 0.41 5150.76 0.92 0.91

 MEAN 497.03 462.12 213.74 0.38 4392.42 0.92 0.91 0.91 1.54

 HUB 403.78 423.55 76.54 0.35 4121.72 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.51 1.15 11.16 634.80 1.04 615.14 531.64 0.05

 MEAN 12.26 1.13 10.91 630.90 1.04 610.98 530.31 0.05

 HUB 12.17 1.12 10.66 629.51 1.03 606.98 529.85 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.44 35.57 31.50 4.07 0.93 0.44 1.40

 MEAN 34.66 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.15 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 552.6802 288.4798 471.4179 1199.4882 0.4608 -0.1927 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2868 10.6428 607.2194 530.5626 0.0568 31.4642 33.0000 1.5358

 

NASA/TM—2013-218094 H–185
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 476.4913 108.8072 463.9019 1205.6873 0.3952 0.0813 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2631 11.0272 613.5126 530.4965 410.5396 0.0369 0.3531

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 461.9071 0.0000 461.9071 1206.7350 0.3828 0.2772 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0984 614.6126 530.4929 0.0000 0.0600 0.0374 0.1321

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8831 12.2624 1.1292 631.7347 23.4551 249.2038 1.9318

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 146134.656 0.441 529.854 597085.125 0.117115E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.39902E-02

 trTOT = 1.3099 Tt4 = 631.7347 T1 = 482.2722

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 930235.13 3372.8433 176.0040 2.3731 0.8684 5.6497 1.3099 37.3740

NASA/TM—2013-218094 H–186
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.987 EfDer = 0.999 SH = 0.969892E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.049 3644.594 5.167 482.272 1.000 1.000 0.980

 W Kg/sec = 28.659 Wdry = 63.043 WH2O = 0.006 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.954 3779.722 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 140743.656 49469.711 1.642 831.557 506.282 619.754 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 406.21 -0.14 406.21 0.39 0.73 680.45

 MEAN 17.06 0.00 -0.02 406.21 -0.14 406.21 0.39 0.64

 HUB 12.51 0.00 -0.02 406.21 -0.14 406.21 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.24 50.47 7.77 656.14 771.82 4.67 469.00 465.08 2.16

 MEAN 53.19 47.20 5.99 542.60 677.92 4.67 469.00 465.08 2.16

 HUB 44.42 38.62 5.80 397.88 568.71 4.67 469.00 465.08 2.16

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 641.96 370.86 524.00 1076.00 0.60 7.29 6.52 16.04

 MEAN 18.04 675.71 409.01 537.86 1070.50 0.63 7.43 6.80 12.53

 HUB 15.00 776.76 533.18 564.88 1060.89 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.14 596.63 285.28 0.55 7653.70 0.92 0.91

 MEAN 573.64 562.49 164.63 0.53 7379.34 0.92 0.91 0.91 1.34

 HUB 477.08 567.65 56.10 0.54 7999.42 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 521.42 1.08 488.28 486.93 1.09

 MEAN 6.64 1.28 5.09 520.02 1.08 483.30 486.31 1.29

 HUB 6.77 1.31 4.76 523.19 1.08 474.67 488.18 1.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.29 28.57 24.20 4.37 0.93 0.36 1.80

 MEAN 37.25 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.35 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 713.8255 408.2175 585.5812 1067.4591 0.6687 -0.0723 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6860 4.9710 480.5697 487.1245 1.4247 34.8809 35.4000 0.5191

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 556.7557 136.1994 539.8394 1085.1273 0.5131 0.3211 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6589 5.5765 496.6182 486.7597 554.9116 0.0263 0.4305

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 552.4587 0.0000 552.4587 1085.5220 0.5089 0.3525 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5756 497.0041 486.7140 0.0000 0.0600 0.0382 0.3206

NASA/TM—2013-218094 H–187
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8798 6.6393 1.2849 521.5419 39.2708 217.0605 1.6826

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244220.109 0.567 870.150 672895.688 0.100751E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.980 EfDer = 1.000 SH = 0.104387E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.049 3644.594 6.639 521.542 1.000 1.000 0.980

 W Kg/sec = 28.659 Wdry = 63.043 WH2O = 0.007 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.979 3634.651 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121803.789 49469.570 1.441 590.487 409.767 468.502 1.143 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 495.06 -0.17 495.06 0.45 0.75 651.79

 MEAN 18.08 0.00 -0.02 495.06 -0.17 495.06 0.45 0.70

 HUB 15.21 0.00 -0.02 495.06 -0.17 495.06 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.87 46.36 6.51 653.59 820.06 5.77 501.84 486.67 0.73

 MEAN 49.28 42.30 6.98 574.98 758.87 5.77 501.84 486.67 0.73

 HUB 44.35 37.84 6.51 483.76 692.30 5.77 501.84 486.67 0.73

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 576.44 300.90 491.68 1117.01 0.52 2.33 2.04 9.02

 MEAN 18.01 590.73 313.53 500.65 1112.88 0.53 2.40 2.13 7.35

 HUB 15.22 642.68 390.71 510.27 1109.02 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 649.46 602.69 348.56 0.54 6147.88 0.92 0.91

 MEAN 572.81 563.81 259.27 0.51 5649.83 0.92 0.91 0.91 1.46

 HUB 484.17 518.76 93.46 0.47 5950.34 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.21 6.74 552.98 1.06 526.27 501.18 0.35

 MEAN 7.94 1.20 6.57 550.43 1.06 522.38 500.09 0.39

 HUB 8.02 1.21 6.40 551.97 1.06 518.77 500.81 0.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.47 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.06 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.44 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 656.3315 314.4147 576.1202 1107.2805 0.5927 -0.1744 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9929 6.3199 517.1695 500.7250 0.4561 28.6233 30.6000 1.9767

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 544.0317 115.3386 531.6648 1118.8230 0.4863 0.1566 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9727 6.7958 528.0040 500.5666 491.5697 0.0241 0.3061

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 568.2016 0.0000 568.2016 1116.5078 0.5089 0.2146 0.5911

NASA/TM—2013-218094 H–188
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6789 525.8459 500.5430 0.0000 0.0600 0.0379 0.0752

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 7.9528 1.1978 551.7937 30.2527 245.4966 1.9031

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188213.000 0.446 670.598 604283.125 0.105558E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.086 EfDer = 1.000 SH = 0.107267E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.049 3644.594 7.953 551.794 1.000 1.000 0.980

 W Kg/sec = 28.659 Wdry = 63.043 WH2O = 0.007 lbm/sec H2O = 0.062g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.201 3533.613 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105783.023 49469.516 1.550 545.479 351.887 424.468 1.206

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 465.42 -0.16 465.42 0.41 0.70 618.87

 MEAN 17.74 0.00 -0.02 465.42 -0.16 465.42 0.41 0.65

 HUB 15.05 0.00 -0.02 465.42 -0.16 465.42 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.91 46.36 7.55 638.33 790.12 7.08 534.39 500.48 0.29

 MEAN 50.49 43.40 7.09 564.17 731.50 7.08 534.39 500.48 0.29

 HUB 45.81 38.84 6.97 478.67 667.75 7.08 534.39 500.48 0.29

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 553.68 298.77 466.15 1149.53 0.48 2.26 1.98 8.75

 MEAN 17.51 566.36 310.66 473.55 1145.82 0.49 2.34 2.07 6.78

 HUB 14.85 615.36 383.15 481.51 1142.32 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.06 571.89 331.29 0.50 5921.82 0.92 0.91

 MEAN 556.80 533.70 246.13 0.47 5441.51 0.92 0.91 0.91 1.49

 HUB 472.31 489.70 89.15 0.43 5692.24 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.50 1.19 8.12 582.07 1.05 557.43 512.90 0.16

 MEAN 9.36 1.18 7.94 579.61 1.05 553.83 511.95 0.17

 HUB 9.43 1.19 7.76 580.89 1.05 550.46 512.48 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.66 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.27 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.51 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 624.6688 312.7029 540.7662 1141.2830 0.5473 -0.1610 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4168 7.7009 549.5033 512.4434 0.1926 30.0390 31.5000 1.4610

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 521.9710 113.8644 509.4003 1151.0691 0.4535 0.1585 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.3990 8.1771 558.9641 512.3439 451.3937 0.0219 0.3277

 

NASA/TM—2013-218094 H–189
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 532.4214 0.0000 532.4214 1150.1282 0.4629 0.2386 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1103 558.0814 512.3006 0.0000 0.0600 0.0373 0.1138

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8820 9.3760 1.1790 580.8544 29.0620 235.7062 1.8272

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180877.984 0.456 644.463 579843.938 0.108575E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.324 EfDer = 0.999 SH = 0.110796E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.049 3644.594 9.376 580.854 1.000 1.000 0.980

 W Kg/sec = 28.659 Wdry = 63.042 WH2O = 0.007 lbm/sec H2O = 0.072g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.605 3444.084 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 93099.953 49469.445 1.676 513.330 306.249 395.845 1.293

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 435.27 -0.15 435.27 0.38 0.65 578.85

 MEAN 16.97 0.00 -0.02 435.27 -0.15 435.27 0.38 0.60

 HUB 14.32 0.00 -0.02 435.27 -0.15 435.27 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.61 46.36 8.25 612.57 751.59 8.52 565.64 512.26 0.13

 MEAN 51.12 43.80 7.32 539.75 693.51 8.52 565.64 512.26 0.13

 HUB 46.31 37.84 8.47 455.45 630.11 8.52 565.64 512.26 0.13

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 524.84 288.95 438.14 1179.14 0.45 2.16 1.89 8.34

 MEAN 16.57 534.23 296.10 444.67 1175.52 0.45 2.24 1.97 6.35

 HUB 13.89 576.69 358.56 451.67 1172.07 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 600.48 537.60 311.53 0.46 5458.27 0.92 0.91

 MEAN 527.13 501.10 231.04 0.43 4910.03 0.92 0.91 0.91 1.51

 HUB 441.77 459.27 83.22 0.39 4982.49 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.96 1.17 9.58 608.74 1.05 586.62 522.72 0.08

 MEAN 10.79 1.15 9.38 605.94 1.04 583.02 521.71 0.09

 HUB 10.81 1.15 9.18 606.31 1.04 579.60 521.87 0.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.40 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.66 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.44 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 574.9127 297.7629 491.7945 1172.8785 0.4902 -0.1129 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8384 9.2157 580.4553 522.0845 0.0957 31.1933 32.4000 1.2067

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 486.9113 109.2000 474.5082 1180.4323 0.4125 0.1776 2.2705

 

NASA/TM—2013-218094 H–190
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8245 9.6428 587.9593 522.0236 432.2457 0.0195 0.3468

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 482.9211 0.0000 482.9211 1180.7136 0.4090 0.2603 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6382 588.2720 521.9706 0.0000 0.0600 0.0371 0.1744

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8822 10.7985 1.1517 606.9976 26.1450 239.2941 1.8550

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 162802.094 0.452 580.060 575378.250 0.112558E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.483 EfDer = 0.999 SH = 0.115705E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.049 3644.594 10.799 606.997 1.000 1.000 0.980

 W Kg/sec = 28.659 Wdry = 63.042 WH2O = 0.007 lbm/sec H2O = 0.085g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.847 3369.100 1.380 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 83141.977 49469.348 1.875 509.668 271.845 384.739 1.415

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 391.51 -0.13 391.51 0.33 0.59 538.61

 MEAN 15.91 0.00 -0.02 391.51 -0.13 391.51 0.33 0.54

 HUB 13.07 0.00 -0.02 391.51 -0.13 391.51 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.11 47.36 8.75 582.67 702.10 10.03 594.69 521.95 0.07

 MEAN 52.28 44.80 7.48 506.11 639.98 10.03 594.69 521.95 0.07

 HUB 46.73 38.84 7.89 415.69 571.13 10.03 594.69 521.95 0.07

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.85 286.49 397.33 1206.22 0.41 2.05 1.78 7.43

 MEAN 15.50 492.65 282.39 403.68 1202.16 0.41 2.13 1.86 5.75

 HUB 12.59 523.56 325.11 410.38 1198.24 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 570.58 488.45 284.09 0.40 5142.11 0.92 0.91

 MEAN 492.90 455.27 210.51 0.38 4378.54 0.92 0.91 0.91 1.55

 HUB 400.43 417.23 75.31 0.35 4094.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.43 1.15 11.11 633.26 1.04 613.99 531.15 0.05

 MEAN 12.18 1.13 10.86 629.36 1.04 609.87 529.82 0.05

 HUB 12.08 1.12 10.62 627.91 1.03 605.90 529.34 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.79 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 34.97 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.39 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 546.0554 287.5699 464.1982 1198.5264 0.4556 -0.1907 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2036 10.6039 606.2410 530.0652 0.0585 31.7781 33.0000 1.2219

 

NASA/TM—2013-218094 H–191
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 469.1784 107.1373 456.7822 1204.7014 0.3895 0.0894 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1815 10.9870 612.5052 530.0018 410.5396 0.0362 0.3574

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 454.9135 0.0000 454.9135 1205.7107 0.3773 0.2819 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0549 613.5648 529.9972 0.0000 0.0600 0.0371 0.1392

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8834 12.1803 1.1280 630.1726 23.1768 247.4240 1.9180

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 144397.859 0.444 514.486 586716.875 0.118199E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.56964E-02

 trTOT = 1.3067 Tt4 = 630.1726 T1 = 482.2721

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 920511.13 3279.7563 172.9544 2.3572 0.8699 5.9874 1.3067 37.3740

NASA/TM—2013-218094 H–192
 100μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.945 EfDer = 0.985 SH = 0.365015E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.576 3889.194 5.167 462.095 1.000 1.000 0.980

 W Kg/sec = 34.353 Wdry = 75.574 WH2O = 0.003 lbm/sec H2O = 0.016g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.931 4120.518 1.381 0.248 53.349 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 167523.047 59300.199 1.400 831.557 594.007 619.754 1.043

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 483.50 -0.17 483.50 0.47 0.83 741.80

 MEAN 17.06 0.00 -0.02 483.50 -0.17 483.50 0.47 0.74

 HUB 12.51 0.00 -0.02 483.50 -0.17 483.50 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.38 50.47 4.91 700.17 851.03 4.45 443.29 452.53 2.65

 MEAN 50.15 47.20 2.95 579.01 754.47 4.45 443.29 452.53 2.65

 HUB 41.30 38.62 2.68 424.58 643.57 4.45 443.29 452.53 2.65

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 726.14 354.57 633.69 1043.98 0.70 7.29 6.52 16.04

 MEAN 18.04 770.91 412.30 651.40 1038.59 0.74 7.43 6.80 12.53

 HUB 15.00 909.96 579.49 701.57 1024.86 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.17 721.81 345.60 0.69 7318.24 0.92 0.90

 MEAN 612.14 681.36 199.84 0.66 7439.07 0.92 0.90 0.90 1.21

 HUB 509.09 705.10 70.40 0.69 8694.50 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 502.05 1.09 459.64 478.30 1.32

 MEAN 6.81 1.32 4.74 502.71 1.09 454.91 478.76 1.59

 HUB 7.12 1.38 4.29 509.56 1.10 442.96 483.02 2.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.23 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.33 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.56 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 832.6525 411.4980 723.8644 1031.8378 0.8070 -0.1061 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8816 4.5036 449.0087 480.0487 2.0178 29.6171 35.4000 5.7829

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 677.8928 165.8333 657.2959 1053.2152 0.6436 0.2306 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8110 5.1714 467.8127 479.5774 554.9116 0.0414 0.3607

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 679.4662 0.0000 679.4662 1053.0049 0.6453 0.2562 1.3089

NASA/TM—2013-218094 H–193
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1129 467.6447 479.4538 0.0000 0.0600 0.0716 0.2046

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8256 6.7430 1.3049 504.7730 42.6786 237.4634 1.8408

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 265341.219 0.541 1133.245 863454.188 0.366094E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.575 EfDer = 0.990 SH = 0.366094E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.576 3889.194 6.743 504.773 1.000 1.000 0.980

 W Kg/sec = 34.353 Wdry = 75.574 WH2O = 0.003 lbm/sec H2O = 0.018g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.533 3942.482 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 146465.031 59300.199 1.241 590.487 475.764 468.502 0.985

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 595.30 -0.21 595.30 0.56 0.86 706.99

 MEAN 18.08 0.00 -0.02 595.30 -0.21 595.30 0.56 0.80

 HUB 15.21 0.00 -0.02 595.30 -0.21 595.30 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.53 46.36 3.17 697.46 917.12 5.46 476.27 479.37 0.69

 MEAN 45.88 42.30 3.58 613.57 855.04 5.46 476.27 479.37 0.69

 HUB 40.94 37.84 3.10 516.22 788.08 5.46 476.27 479.37 0.69

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 646.76 276.05 584.88 1090.91 0.59 2.33 2.04 9.02

 MEAN 18.01 666.44 301.22 594.48 1087.39 0.61 2.40 2.13 7.35

 HUB 15.22 727.51 403.94 605.07 1084.22 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 693.05 718.31 416.99 0.66 5641.21 0.92 0.91

 MEAN 611.25 670.46 310.03 0.62 5428.73 0.92 0.91 0.91 1.37

 HUB 516.66 615.48 112.73 0.57 6152.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.19 1.22 6.48 535.57 1.06 501.93 495.16 0.29

 MEAN 8.13 1.21 6.33 534.41 1.06 498.69 494.62 0.32

 HUB 8.33 1.24 6.18 538.36 1.07 495.79 496.53 0.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.27 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.87 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.73 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 763.4572 302.0692 701.1570 1077.0083 0.7089 -0.2347 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2020 5.8883 489.2435 495.4768 0.4321 23.3071 30.6000 7.2929

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 659.5112 139.8211 644.5192 1090.0298 0.6050 0.0244 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1431 6.3775 501.1344 495.2722 491.5697 0.0412 0.2229

 

NASA/TM—2013-218094 H–194
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 701.6173 0.0000 701.6173 1084.9901 0.6467 0.1009 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1218 496.5298 495.1830 0.0000 0.0600 0.0731 -0.1109

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8263 8.0827 1.1987 536.1091 31.3365 279.8581 2.1694

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 194889.906 0.406 832.355 781326.000 0.366094E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.935 EfDer = 0.992 SH = 0.366094E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.576 3889.194 8.083 536.109 1.000 1.000 0.980

 W Kg/sec = 34.353 Wdry = 75.574 WH2O = 0.003 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.739 3825.526 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126151.102 59300.199 1.334 545.479 409.055 424.468 1.038 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 555.04 -0.19 555.04 0.50 0.80 670.00

 MEAN 17.74 0.00 -0.02 555.04 -0.19 555.04 0.50 0.74

 HUB 15.05 0.00 -0.02 555.04 -0.19 555.04 0.50 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.83 46.36 4.47 681.17 878.82 6.81 511.34 495.10 0.21

 MEAN 47.33 43.40 3.93 602.04 818.99 6.81 511.34 495.10 0.21

 HUB 42.63 38.84 3.79 510.79 754.44 6.81 511.34 495.10 0.21

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 617.39 278.89 550.81 1126.89 0.55 2.26 1.98 8.75

 MEAN 17.51 635.18 301.89 558.86 1123.62 0.57 2.34 2.07 6.78

 HUB 14.85 692.97 397.33 567.75 1120.64 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.34 676.90 393.45 0.60 5528.73 0.92 0.91

 MEAN 594.17 630.67 292.28 0.56 5288.40 0.92 0.91 0.91 1.40

 HUB 504.00 577.69 106.68 0.52 5903.18 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.68 1.20 7.91 566.28 1.06 535.64 508.52 0.11

 MEAN 9.61 1.19 7.76 564.97 1.05 532.53 507.97 0.11

 HUB 9.80 1.21 7.59 568.32 1.06 529.72 509.40 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.85 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.38 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 34.99 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 716.0833 303.8685 648.4128 1115.9264 0.6417 -0.2039 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6764 7.3592 525.3076 508.6239 0.1387 25.1094 31.5000 6.3906

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 625.6119 136.4730 610.5452 1126.2521 0.5555 0.0380 2.3726

 

NASA/TM—2013-218094 H–195
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6287 7.8280 535.0626 508.4940 451.3937 0.0346 0.2554

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 642.4938 0.0000 642.4938 1124.4177 0.5714 0.1466 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6988 533.3455 508.4065 0.0000 0.0600 0.0591 -0.0285

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8469 9.5811 1.1854 566.5236 30.4148 265.5406 2.0585

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189221.266 0.419 808.144 738978.188 0.366094E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.504 EfDer = 0.995 SH = 0.366094E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.576 3889.194 9.581 566.523 1.000 1.000 0.980

 W Kg/sec = 34.353 Wdry = 75.574 WH2O = 0.003 lbm/sec H2O = 0.024g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.183 3721.421 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109780.039 59300.199 1.447 513.330 354.755 395.845 1.116

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 513.26 -0.18 513.26 0.45 0.73 625.46

 MEAN 16.97 0.00 -0.02 513.26 -0.18 513.26 0.45 0.68

 HUB 14.32 0.00 -0.02 513.26 -0.18 513.26 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.87 46.36 5.51 653.68 831.24 8.35 545.35 508.37 0.08

 MEAN 48.30 43.80 4.50 575.98 771.62 8.35 545.35 508.37 0.08

 HUB 43.45 37.84 5.61 486.02 706.98 8.35 545.35 508.37 0.08

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 581.39 274.91 512.29 1160.03 0.50 2.16 1.89 8.34

 MEAN 16.57 595.70 291.00 519.79 1156.59 0.52 2.24 1.97 6.35

 HUB 13.89 646.37 372.95 527.92 1153.40 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.78 629.53 365.87 0.54 5193.64 0.92 0.91

 MEAN 562.51 586.43 271.51 0.51 4826.02 0.92 0.91 0.91 1.42

 HUB 471.42 537.03 98.47 0.47 5182.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.26 1.18 9.50 594.85 1.05 567.69 519.68 0.05

 MEAN 11.13 1.16 9.31 592.85 1.05 564.33 518.91 0.05

 HUB 11.26 1.17 9.12 594.80 1.05 561.22 519.67 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.22 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.24 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.24 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 649.0269 292.6378 579.3091 1152.4224 0.5632 -0.1363 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.1971 9.0523 560.3224 519.3954 0.0551 26.8006 32.4000 5.5994

 

NASA/TM—2013-218094 H–196
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 574.3846 128.8177 559.7532 1159.9457 0.4952 0.0779 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1619 9.4597 567.6588 519.3138 432.2457 0.0285 0.2846

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 569.8206 0.0000 569.8206 1160.3505 0.4911 0.1877 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4548 568.0812 519.2459 0.0000 0.0600 0.0472 0.0753

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8628 11.1263 1.1613 594.1656 27.6428 266.0313 2.0623

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 172050.406 0.419 734.809 724091.625 0.366094E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.083 EfDer = 0.997 SH = 0.366094E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 75.576 3889.194 11.126 594.165 1.000 1.000 0.980

 W Kg/sec = 34.353 Wdry = 75.574 WH2O = 0.003 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.869 3633.825 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96665.563 59300.199 1.629 509.668 312.872 384.739 1.230

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 455.19 -0.16 455.19 0.39 0.66 580.93

 MEAN 15.91 0.00 -0.02 455.19 -0.16 455.19 0.39 0.60

 HUB 13.07 0.00 -0.02 455.19 -0.16 455.19 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.80 47.36 6.44 621.77 770.71 10.04 577.52 519.23 0.04

 MEAN 49.88 44.80 5.08 540.08 706.44 10.04 577.52 519.23 0.04

 HUB 44.27 38.84 5.43 443.59 635.70 10.04 577.52 519.23 0.04

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 536.96 280.03 458.15 1190.89 0.45 2.05 1.78 7.43

 MEAN 15.50 544.61 281.92 465.96 1186.66 0.46 2.13 1.86 5.75

 HUB 12.59 583.16 339.40 474.22 1182.64 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.88 563.95 328.85 0.47 5026.62 0.92 0.91

 MEAN 525.98 526.01 244.06 0.44 4371.60 0.92 0.91 0.91 1.47

 HUB 427.30 482.29 87.90 0.41 4275.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.92 1.16 11.26 621.57 1.05 598.41 529.32 0.02

 MEAN 12.68 1.14 10.99 618.00 1.04 594.18 528.04 0.03

 HUB 12.64 1.14 10.73 617.47 1.04 590.16 527.86 0.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.43 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.18 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.59 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 611.7329 287.0908 540.1815 1181.3938 0.5178 -0.2170 2.0437

 

NASA/TM—2013-218094 H–197
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7103 10.6111 588.9643 528.3547 0.0286 27.9893 33.0000 5.0107

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 547.5218 125.0271 533.0557 1187.3792 0.4611 -0.0177 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6577 10.9613 594.9410 528.2519 410.5396 0.0500 0.3048

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 529.1544 0.0000 529.1544 1188.9384 0.4451 0.2212 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0754 596.5314 528.2653 0.0000 0.0600 0.0451 0.0474

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8699 12.6663 1.1384 619.0144 24.8495 270.2948 2.0953

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154744.297 0.417 660.897 729473.063 0.366094E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3396 Tt4 = 619.0144 T1 = 462.0947

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 976247.06 4169.4502 202.9310 2.4512 0.8264 2.9451 1.3396 37.3740

NASA/TM—2013-218094 H–198
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.292 EfDer = 0.998 SH = 0.366605E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl 

 66.718 3626.345 5.167 462.094 1.000 1.000 0.980

 W Kg/sec = 30.326 Wdry = 66.716 WH2O = 0.002 lbm/sec H2O = 0.016g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 179.145 3842.035 1.381 0.248 53.349 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 143616.188 52349.641 1.586 831.557 524.385 619.754 1.182

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 414.50 -0.14 414.50 0.40 0.75 691.66

 MEAN 17.06 0.00 -0.02 414.50 -0.14 414.50 0.40 0.66

 HUB 12.51 0.00 -0.02 414.50 -0.14 414.50 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.59 50.47 7.12 652.85 773.44 4.63 448.28 452.48 2.15

 MEAN 52.49 47.20 5.29 539.88 680.76 4.63 448.28 452.48 2.15

 HUB 43.69 38.62 5.07 395.89 573.28 4.63 448.28 452.48 2.15

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 646.05 360.99 535.79 1051.68 0.61 7.29 6.52 16.04

 MEAN 18.04 681.47 402.26 550.08 1046.29 0.65 7.43 6.80 12.53

 HUB 15.00 786.95 532.28 579.64 1036.33 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.85 610.13 291.86 0.58 7450.24 0.92 0.91

 MEAN 570.77 575.32 168.51 0.55 7257.54 0.92 0.91 0.91 1.31

 HUB 474.69 582.49 57.59 0.56 7985.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.22 500.02 1.08 466.45 477.07 1.03

 MEAN 6.67 1.29 5.03 499.04 1.08 461.69 476.56 1.23

 HUB 6.84 1.32 4.68 502.75 1.09 452.94 478.87 1.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.97 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.18 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.56 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 722.3629 401.4752 600.5214 1042.8252 0.6927 -0.0776 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7218 4.8951 458.6333 477.4852 1.3844 33.7645 35.4000 1.6355

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 569.5626 139.3324 552.2572 1060.7159 0.5370 0.3026 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6904 5.5113 474.5110 477.2459 554.9116 0.0278 0.4157

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 565.5915 0.0000 565.5915 1061.1033 0.5330 0.3346 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5062 474.8758 477.1989 0.0000 0.0600 0.0418 0.2997

NASA/TM—2013-218094 H–199
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 6.6657 1.2900 500.6005 38.5066 221.4397 1.7166

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 239418.703 0.562 902.682 740232.188 0.368046E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.260 EfDer = 1.000 SH = 0.368046E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.718 3626.345 6.666 500.600 1.000 1.000 0.980

 W Kg/sec = 30.326 Wdry = 66.716 WH2O = 0.002 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.544 3691.320 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124305.727 52349.641 1.396 590.487 423.109 468.502 1.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 505.23 -0.17 505.23 0.47 0.77 661.95

 MEAN 18.08 0.00 -0.02 505.23 -0.17 505.23 0.47 0.72

 HUB 15.21 0.00 -0.02 505.23 -0.17 505.23 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.16 46.36 5.80 650.32 823.65 5.73 480.07 477.16 0.62

 MEAN 48.56 42.30 6.26 572.10 763.39 5.73 480.07 477.16 0.62

 HUB 43.62 37.84 5.78 481.33 697.93 5.73 480.07 477.16 0.62

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 579.03 290.89 500.66 1093.03 0.53 2.33 2.04 9.02

 MEAN 18.01 594.31 305.63 509.70 1089.05 0.55 2.40 2.13 7.35

 HUB 15.22 647.29 386.30 519.39 1085.37 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 646.21 613.93 355.32 0.56 5943.52 0.92 0.91

 MEAN 569.94 574.15 264.31 0.53 5507.60 0.92 0.91 0.91 1.44

 HUB 481.74 528.08 95.45 0.49 5883.25 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.71 530.85 1.06 503.89 493.13 0.28

 MEAN 7.99 1.20 6.54 528.63 1.06 500.23 492.05 0.31

 HUB 8.08 1.21 6.37 530.54 1.06 496.85 493.02 0.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.16 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 30.95 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.64 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 663.6008 306.4916 588.5822 1082.8834 0.6128 -0.1841 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0422 6.2602 494.6011 492.7416 0.3721 27.5073 30.6000 3.0927

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 555.3991 117.7486 542.7739 1094.4351 0.5075 0.1316 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0176 6.7397 505.2055 492.6349 491.5697 0.0262 0.2900

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 581.0704 0.0000 581.0704 1091.8738 0.5322 0.1956 0.5911

NASA/TM—2013-218094 H–200
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6087 502.8623 492.6038 0.0000 0.0600 0.0408 0.0453

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8764 7.9955 1.1995 530.0078 29.4077 252.1209 1.9544

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182899.313 0.438 689.586 665106.000 0.368046E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.450 EfDer = 1.000 SH = 0.368046E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.718 3626.345 7.995 530.008 1.000 1.000 0.980

 W Kg/sec = 30.326 Wdry = 66.716 WH2O = 0.002 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.994 3587.453 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107659.281 52349.641 1.503 545.479 362.967 424.468 1.169

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 473.68 -0.16 473.68 0.43 0.72 628.30

 MEAN 17.74 0.00 -0.02 473.68 -0.16 473.68 0.43 0.67

 HUB 15.05 0.00 -0.02 473.68 -0.16 473.68 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.29 46.36 6.93 635.13 792.45 7.05 511.97 492.56 0.22

 MEAN 49.85 43.40 6.45 561.35 734.62 7.05 511.97 492.56 0.22

 HUB 45.17 38.84 6.33 476.27 671.83 7.05 511.97 492.56 0.22

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 555.28 290.09 473.48 1125.66 0.49 2.26 1.98 8.75

 MEAN 17.51 568.84 303.76 480.94 1122.06 0.51 2.34 2.07 6.78

 HUB 14.85 618.77 379.17 488.99 1118.70 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 626.90 581.06 336.82 0.52 5749.88 0.92 0.91

 MEAN 554.01 542.16 250.25 0.48 5320.69 0.92 0.91 0.91 1.47

 HUB 469.94 497.34 90.77 0.44 5633.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.56 1.20 8.11 559.26 1.06 534.48 506.04 0.11

 MEAN 9.43 1.18 7.93 557.08 1.05 531.07 505.09 0.12

 HUB 9.52 1.19 7.76 558.67 1.05 527.89 505.80 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.49 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.28 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.79 10.52 6.50 4.02 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 629.7044 305.7536 550.4929 1117.1543 0.5637 -0.1681 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4897 7.6691 526.4656 505.6308 0.1396 29.0486 31.5000 2.4514

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.2191 115.8819 518.4257 1126.8661 0.4714 0.1362 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4688 8.1474 535.6550 505.5608 451.3937 0.0234 0.3137

 

NASA/TM—2013-218094 H–201
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 542.1594 0.0000 542.1594 1125.8505 0.4816 0.2229 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0749 534.7136 505.5175 0.0000 0.0600 0.0387 0.0901

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8799 9.4447 1.1813 558.3374 28.3301 241.2382 1.8701

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176252.734 0.448 664.527 636422.063 0.368046E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.770 EfDer = 1.000 SH = 0.368046E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.718 3626.345 9.445 558.337 1.000 1.000 0.980

 W Kg/sec = 30.326 Wdry = 66.716 WH2O = 0.002 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.737 3495.256 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94481.352 52349.641 1.628 513.330 315.393 395.845 1.255

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 441.73 -0.15 441.73 0.39 0.66 587.45

 MEAN 16.97 0.00 -0.02 441.73 -0.15 441.73 0.39 0.61

 HUB 14.32 0.00 -0.02 441.73 -0.15 441.73 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.07 46.36 7.71 609.50 752.86 8.52 542.66 505.50 0.09

 MEAN 50.57 43.80 6.77 537.05 695.50 8.52 542.66 505.50 0.09

 HUB 45.74 37.84 7.90 453.17 632.95 8.52 542.66 505.50 0.09

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 525.66 281.62 443.85 1155.42 0.45 2.16 1.89 8.34

 MEAN 16.57 535.88 290.22 450.49 1151.87 0.47 2.24 1.97 6.35

 HUB 13.89 579.20 355.08 457.60 1148.51 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 597.47 544.76 315.85 0.47 5319.97 0.92 0.91

 MEAN 524.49 507.76 234.27 0.44 4812.69 0.92 0.91 0.91 1.49

 HUB 439.56 465.33 84.48 0.41 4934.20 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.05 1.17 9.61 585.40 1.05 563.19 516.71 0.05

 MEAN 10.89 1.15 9.41 582.82 1.04 559.74 515.69 0.06

 HUB 10.93 1.16 9.21 583.43 1.04 556.47 515.94 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.39 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 32.79 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.81 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 577.9216 291.8546 498.8128 1149.0573 0.5030 -0.1169 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9427 9.2266 557.0464 516.0940 0.0623 30.3318 32.4000 2.0682

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 493.8882 110.7647 481.3074 1156.4954 0.4271 0.1591 2.2705

 

NASA/TM—2013-218094 H–202
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9264 9.6542 564.2831 516.0491 432.2457 0.0205 0.3345

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 489.8401 0.0000 489.8401 1156.7992 0.4234 0.2467 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6500 564.6050 515.9982 0.0000 0.0600 0.0381 0.1563

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8807 10.8992 1.1540 583.8813 25.5446 244.1620 1.8927

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 158985.078 0.445 599.422 630070.375 0.368046E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.013 EfDer = 1.000 SH = 0.368046E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 66.718 3626.345 10.899 583.881 1.000 1.000 0.980

 W Kg/sec = 30.326 Wdry = 66.716 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.471 3417.945 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84138.906 52349.641 1.823 509.668 279.502 384.739 1.377

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 396.21 -0.14 396.21 0.34 0.60 546.42

 MEAN 15.91 0.00 -0.02 396.21 -0.14 396.21 0.34 0.55

 HUB 13.07 0.00 -0.02 396.21 -0.14 396.21 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.66 47.36 8.30 579.75 702.32 10.07 571.27 515.99 0.04

 MEAN 51.81 44.80 7.01 503.58 640.87 10.07 571.27 515.99 0.04

 HUB 46.24 38.84 7.40 413.61 572.86 10.07 571.27 515.99 0.04

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.73 280.50 401.44 1182.71 0.41 2.05 1.78 7.43

 MEAN 15.50 493.39 277.51 407.95 1178.69 0.42 2.13 1.86 5.75

 HUB 12.59 525.23 322.17 414.82 1174.81 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 567.73 493.62 287.23 0.42 5034.62 0.92 0.91

 MEAN 490.43 460.17 212.92 0.39 4302.99 0.92 0.91 0.91 1.53

 HUB 398.42 421.77 76.25 0.36 4057.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.57 1.15 11.19 609.48 1.04 590.21 525.79 0.03

 MEAN 12.32 1.13 10.93 605.76 1.04 586.20 524.41 0.03

 HUB 12.23 1.12 10.68 604.51 1.04 582.35 523.95 0.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.94 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.23 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.83 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 548.1756 282.6036 469.7145 1174.8660 0.4666 -0.1953 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3436 10.6535 582.4485 524.6701 0.0345 31.0332 33.0000 1.9668

 

NASA/TM—2013-218094 H–203
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 474.8842 108.4402 462.3372 1180.9240 0.4021 0.0700 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3179 11.0353 588.4702 524.6157 410.5396 0.0379 0.3469

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 460.2311 0.0000 460.2311 1182.0028 0.3894 0.2703 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1104 589.5723 524.6141 0.0000 0.0600 0.0379 0.1222

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8824 12.3179 1.1302 606.5813 22.7009 251.6533 1.9508

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 141348.359 0.439 532.927 641170.813 0.368112E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3127 Tt4 = 606.5813 T1 = 462.0943

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 898904.19 3389.1438 179.1455 2.3838 0.8661 5.2919 1.3127 37.3740

NASA/TM—2013-218094 H–204
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.634 EfDer = 0.999 SH = 0.366757E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.576 3597.008 5.167 462.094 1.000 1.000 0.980

 W Kg/sec = 29.807 Wdry = 65.573 WH2O = 0.002 lbm/sec H2O = 0.016g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 176.078 3810.952 1.381 0.248 53.349 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140699.422 51453.270 1.613 831.557 515.406 619.754 1.202

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 406.08 -0.14 406.08 0.39 0.74 686.07

 MEAN 17.06 0.00 -0.02 406.08 -0.14 406.08 0.39 0.65

 HUB 12.51 0.00 -0.02 406.08 -0.14 406.08 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.91 50.47 7.44 647.57 764.48 4.65 448.83 452.48 2.11

 MEAN 52.83 47.20 5.63 535.51 672.18 4.65 448.83 452.48 2.11

 HUB 44.05 38.62 5.43 392.69 564.99 4.65 448.83 452.48 2.11

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 637.17 362.04 524.32 1052.48 0.61 7.29 6.52 16.04

 MEAN 18.04 671.40 401.32 538.26 1047.10 0.64 7.43 6.80 12.53

 HUB 15.00 773.56 527.08 566.20 1037.43 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.57 597.03 285.54 0.57 7471.69 0.92 0.91

 MEAN 566.15 562.93 164.83 0.54 7240.65 0.92 0.91 0.91 1.33

 HUB 470.85 568.99 56.23 0.55 7907.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 499.82 1.08 467.17 476.95 1.00

 MEAN 6.65 1.29 5.06 498.65 1.08 462.40 476.32 1.20

 HUB 6.80 1.32 4.72 502.02 1.09 453.90 478.43 1.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.62 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.71 17.03 12.70 4.33 0.92 0.30 2.22

 HUB 42.95 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 710.4520 400.5430 586.7772 1043.8894 0.6806 -0.0749 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7042 4.9340 459.5708 477.2201 1.3361 34.3180 35.4000 1.0820

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 557.2112 136.3109 540.2811 1061.4791 0.5249 0.3118 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6752 5.5450 475.1951 476.9959 554.9116 0.0270 0.4231

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 553.0968 0.0000 553.0968 1061.8715 0.5209 0.3436 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5423 475.5647 476.9539 0.0000 0.0600 0.0398 0.3102

NASA/TM—2013-218094 H–205
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8772 6.6532 1.2876 500.1653 38.0714 219.2666 1.6997

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 236714.188 0.564 877.203 725198.563 0.368295E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.618 EfDer = 1.000 SH = 0.368295E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.576 3597.008 6.653 500.165 1.000 1.000 0.980

 W Kg/sec = 29.807 Wdry = 65.573 WH2O = 0.002 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.275 3663.049 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121757.883 51453.262 1.418 590.487 416.467 468.502 1.125

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 494.88 -0.17 494.88 0.46 0.76 656.88

 MEAN 18.08 0.00 -0.02 494.88 -0.17 494.88 0.46 0.71

 HUB 15.21 0.00 -0.02 494.88 -0.17 494.88 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.51 46.36 6.15 645.06 813.16 5.75 480.47 476.92 0.61

 MEAN 48.92 42.30 6.62 567.47 753.08 5.75 480.47 476.92 0.61

 HUB 43.98 37.84 6.14 477.44 687.76 5.75 480.47 476.92 0.61

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 571.59 292.75 490.93 1093.25 0.52 2.33 2.04 9.02

 MEAN 18.01 586.24 306.31 499.85 1089.23 0.54 2.40 2.13 7.35

 HUB 15.22 638.16 384.39 509.41 1085.50 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.98 601.89 348.23 0.55 5981.53 0.92 0.91

 MEAN 565.33 562.97 259.01 0.52 5519.78 0.92 0.91 0.91 1.45

 HUB 477.85 517.91 93.45 0.48 5854.22 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.08 1.21 6.72 530.36 1.06 504.09 492.91 0.28

 MEAN 7.97 1.20 6.56 528.03 1.06 500.39 491.77 0.31

 HUB 8.05 1.21 6.39 529.72 1.06 496.97 492.63 0.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.81 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.50 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.04 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 652.9341 307.1738 576.1660 1083.4208 0.6027 -0.1791 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0188 6.2918 495.0926 492.4384 0.3670 28.0636 30.6000 2.5364

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 543.8706 115.3044 531.5074 1094.8468 0.4968 0.1442 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9965 6.7698 505.5869 492.3383 491.5697 0.0251 0.2981

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 568.4354 0.0000 568.4354 1092.4479 0.5203 0.2056 0.5911

NASA/TM—2013-218094 H–206
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6469 503.3923 492.3099 0.0000 0.0600 0.0388 0.0610

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 7.9762 1.1989 529.3701 29.2052 248.7901 1.9286

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 181640.797 0.442 673.115 651238.000 0.368295E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.770 EfDer = 1.000 SH = 0.368295E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.576 3597.008 7.976 529.370 1.000 1.000 0.980

 W Kg/sec = 29.807 Wdry = 65.573 WH2O = 0.002 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.091 3560.572 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105581.633 51453.262 1.526 545.479 357.398 424.468 1.188

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 464.54 -0.16 464.54 0.42 0.71 623.59

 MEAN 17.74 0.00 -0.02 464.54 -0.16 464.54 0.42 0.66

 HUB 15.05 0.00 -0.02 464.54 -0.16 464.54 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.60 46.36 7.24 629.99 782.87 7.07 512.02 492.27 0.22

 MEAN 50.17 43.40 6.77 556.81 725.26 7.07 512.02 492.27 0.22

 HUB 45.49 38.84 6.65 472.42 662.67 7.07 512.02 492.27 0.22

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 548.56 291.36 464.79 1125.50 0.49 2.26 1.98 8.75

 MEAN 17.51 561.55 304.00 472.15 1121.88 0.50 2.34 2.07 6.78

 HUB 14.85 610.49 377.13 480.07 1118.48 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 621.83 570.30 330.48 0.51 5774.99 0.92 0.91

 MEAN 549.53 532.17 245.53 0.47 5324.75 0.92 0.91 0.91 1.48

 HUB 466.14 488.25 89.01 0.44 5602.78 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.53 1.19 8.12 558.52 1.06 534.32 505.74 0.11

 MEAN 9.40 1.18 7.94 556.24 1.05 530.89 504.75 0.12

 HUB 9.48 1.19 7.76 557.65 1.05 527.69 505.38 0.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.08 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.78 27.48 23.50 3.98 0.93 0.39 1.62

 HUB 38.15 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 620.4698 305.9901 539.7712 1117.2168 0.5554 -0.1644 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4562 7.6883 526.5245 505.2789 0.1398 29.5484 31.5000 1.9516

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 520.9301 113.6374 508.3844 1126.8668 0.4623 0.1476 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4370 8.1661 535.6563 505.2130 451.3937 0.0226 0.3208

 

NASA/TM—2013-218094 H–207
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 531.5012 0.0000 531.5012 1125.9034 0.4721 0.2309 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0965 534.7643 505.1706 0.0000 0.0600 0.0379 0.1022

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 9.4135 1.1802 557.4684 28.0988 238.4278 1.8483

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 174813.859 0.452 647.816 623945.688 0.368295E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.050 EfDer = 1.000 SH = 0.368295E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.576 3597.008 9.413 557.468 1.000 1.000 0.980

 W Kg/sec = 29.807 Wdry = 65.573 WH2O = 0.002 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.161 3469.680 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 92786.719 51453.262 1.652 513.330 310.779 395.845 1.274

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 433.81 -0.15 433.81 0.38 0.66 583.15

 MEAN 16.97 0.00 -0.02 433.81 -0.15 433.81 0.38 0.61

 HUB 14.32 0.00 -0.02 433.81 -0.15 433.81 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.35 46.36 7.99 604.57 744.23 8.52 542.34 505.15 0.09

 MEAN 50.85 43.80 7.05 532.71 687.12 8.52 542.34 505.15 0.09

 HUB 46.03 37.84 8.19 449.50 624.80 8.52 542.34 505.15 0.09

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 519.65 282.32 436.27 1154.89 0.45 2.16 1.89 8.34

 MEAN 16.57 529.34 290.07 442.78 1151.34 0.46 2.24 1.97 6.35

 HUB 13.89 571.78 353.05 449.77 1147.97 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 592.64 535.38 310.32 0.46 5333.03 0.92 0.91

 MEAN 520.25 499.04 230.18 0.43 4810.20 0.92 0.91 0.91 1.50

 HUB 436.00 457.36 82.96 0.40 4905.94 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.01 1.17 9.60 584.37 1.05 562.67 516.34 0.05

 MEAN 10.84 1.15 9.40 581.74 1.04 559.22 515.29 0.06

 HUB 10.87 1.16 9.20 582.22 1.04 555.95 515.50 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.91 35.42 31.50 3.92 0.93 0.41 1.40

 MEAN 33.23 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.13 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 570.2456 291.7061 489.9874 1148.6488 0.4964 -0.1148 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8945 9.2254 556.6491 515.6903 0.0631 30.7668 32.4000 1.6332

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 485.1283 108.8001 472.7706 1156.0696 0.4196 0.1685 2.2705

 

NASA/TM—2013-218094 H–208
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8794 9.6532 563.8668 515.6480 432.2457 0.0200 0.3407

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 481.1514 0.0000 481.1514 1156.3621 0.4161 0.2536 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6488 564.1774 515.5983 0.0000 0.0600 0.0375 0.1656

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8816 10.8529 1.1529 582.7759 25.3083 241.6850 1.8735

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 157513.266 0.448 583.704 618398.563 0.368295E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.251 EfDer = 1.000 SH = 0.368295E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.576 3597.008 10.853 582.776 1.000 1.000 0.980

 W Kg/sec = 29.807 Wdry = 65.573 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.147 3393.506 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 82744.711 51453.262 1.849 509.668 275.626 384.739 1.396

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 389.64 -0.13 389.64 0.34 0.60 542.51

 MEAN 15.91 0.00 -0.02 389.64 -0.13 389.64 0.34 0.54

 HUB 13.07 0.00 -0.02 389.64 -0.13 389.64 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.89 47.36 8.53 575.06 694.74 10.05 570.58 515.59 0.05

 MEAN 52.05 44.80 7.25 499.51 633.61 10.05 570.58 515.59 0.05

 HUB 46.49 38.84 7.65 410.26 565.90 10.05 570.58 515.59 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 484.58 280.55 395.11 1181.81 0.41 2.05 1.78 7.43

 MEAN 15.50 487.77 277.03 401.47 1177.81 0.41 2.13 1.86 5.75

 HUB 12.59 518.80 320.22 408.18 1173.95 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 563.13 485.76 282.59 0.41 5035.44 0.92 0.91

 MEAN 486.47 452.81 209.44 0.38 4295.44 0.92 0.91 0.91 1.54

 HUB 395.20 415.01 74.98 0.35 4033.32 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.51 1.15 11.16 608.17 1.04 589.31 525.35 0.03

 MEAN 12.25 1.13 10.90 604.44 1.04 585.33 523.96 0.03

 HUB 12.16 1.12 10.65 603.12 1.03 581.49 523.47 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.38 35.57 31.50 4.07 0.93 0.44 1.40

 MEAN 34.61 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.11 10.41 6.50 3.91 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 541.2754 282.1099 461.9449 1174.1245 0.4610 -0.1930 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2785 10.6337 581.7105 524.2151 0.0352 31.4124 33.0000 1.5876

 

NASA/TM—2013-218094 H–209
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 466.9533 106.6292 454.6159 1180.1820 0.3957 0.0799 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2546 11.0167 587.7285 524.1640 410.5396 0.0370 0.3523

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 452.6551 0.0000 452.6551 1181.2173 0.3832 0.2763 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0881 588.7861 524.1613 0.0000 0.0600 0.0375 0.1309

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8830 12.2540 1.1291 605.2399 22.4648 249.4913 1.9340

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 139876.828 0.441 518.348 629942.688 0.368448E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3098 Tt4 = 605.2399 T1 = 462.0943

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 890558.94 3300.1870 176.0780 2.3714 0.8684 5.6342 1.3098 37.3740

NASA/TM—2013-218094 H–210
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.971 EfDer = 0.999 SH = 0.367065E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.442 3567.117 5.167 462.094 1.000 1.000 0.980

 W Kg/sec = 29.292 Wdry = 64.439 WH2O = 0.002 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 173.033 3779.283 1.381 0.248 53.349 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 137835.656 50563.492 1.642 831.557 506.494 619.754 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 397.81 -0.14 397.81 0.39 0.73 680.37

 MEAN 17.06 0.00 -0.02 397.81 -0.14 397.81 0.39 0.64

 HUB 12.51 0.00 -0.02 397.81 -0.14 397.81 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.23 50.47 7.76 642.19 755.54 4.67 449.37 452.47 2.06

 MEAN 53.17 47.20 5.97 531.06 663.65 4.67 449.37 452.47 2.06

 HUB 44.40 38.62 5.78 389.42 556.79 4.67 449.37 452.47 2.06

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 628.52 362.77 513.26 1053.21 0.60 7.29 6.52 16.04

 MEAN 18.04 661.58 400.20 526.81 1047.83 0.63 7.43 6.80 12.53

 HUB 15.00 760.58 521.89 553.28 1038.43 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 642.19 584.39 279.42 0.55 7486.69 0.92 0.91

 MEAN 561.44 550.93 161.24 0.53 7220.37 0.92 0.91 0.91 1.34

 HUB 466.93 556.00 54.95 0.54 7830.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 499.58 1.08 467.81 476.81 0.98

 MEAN 6.64 1.28 5.09 498.25 1.08 463.05 476.08 1.17

 HUB 6.77 1.31 4.76 501.30 1.08 454.78 478.00 1.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.25 28.56 24.20 4.36 0.93 0.36 1.80

 MEAN 37.22 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.33 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 698.9488 399.4237 573.5766 1044.8517 0.6689 -0.0724 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6853 4.9695 460.4196 476.9440 1.2943 34.8523 35.4000 0.5477

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 545.3701 133.4142 528.7997 1062.1421 0.5135 0.3206 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6582 5.5744 475.7899 476.7330 554.9116 0.0263 0.4301

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 541.1669 0.0000 541.1669 1062.5339 0.5093 0.3520 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5734 476.1592 476.6951 0.0000 0.0600 0.0382 0.3200

NASA/TM—2013-218094 H–211
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8797 6.6385 1.2847 499.7098 37.6161 217.1702 1.6835

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 233884.547 0.567 851.729 710437.875 0.368670E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.957 EfDer = 1.000 SH = 0.368670E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.442 3567.117 6.638 499.710 1.000 1.000 0.980

 W Kg/sec = 29.292 Wdry = 64.439 WH2O = 0.002 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.061 3634.264 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 119308.070 50563.492 1.440 590.487 409.986 468.502 1.143

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 484.92 -0.17 484.92 0.45 0.75 651.72

 MEAN 18.08 0.00 -0.02 484.92 -0.17 484.92 0.45 0.70

 HUB 15.21 0.00 -0.02 484.92 -0.17 484.92 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.84 46.36 6.48 639.70 802.86 5.77 480.80 476.66 0.61

 MEAN 49.26 42.30 6.96 562.76 742.99 5.77 480.80 476.66 0.61

 HUB 44.33 37.84 6.49 473.47 677.85 5.77 480.80 476.66 0.61

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 564.39 294.19 481.66 1093.35 0.52 2.33 2.04 9.02

 MEAN 18.01 578.41 306.65 490.43 1089.31 0.53 2.40 2.13 7.35

 HUB 15.22 629.29 382.33 499.83 1085.55 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.65 590.41 341.46 0.54 6010.81 0.92 0.91 

 MEAN 560.63 552.29 253.98 0.51 5525.83 0.92 0.91 0.91 1.46

 HUB 473.88 508.15 91.55 0.47 5822.71 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.21 6.74 529.80 1.06 504.19 492.64 0.28

 MEAN 7.94 1.20 6.57 527.37 1.06 500.47 491.45 0.31

 HUB 8.01 1.21 6.40 528.86 1.06 497.02 492.21 0.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.42 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.02 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.41 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 642.7302 307.5139 564.3911 1083.8267 0.5930 -0.1746 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9908 6.3168 495.4638 492.1044 0.3634 28.5842 30.6000 2.0158

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 532.9885 112.9973 520.8726 1095.1172 0.4867 0.1557 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9704 6.7919 505.8374 492.0102 491.5697 0.0241 0.3055

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 556.6851 0.0000 556.6851 1092.8499 0.5094 0.2139 0.5911

NASA/TM—2013-218094 H–212
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6748 503.7635 491.9817 0.0000 0.0600 0.0380 0.0742

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8804 7.9505 1.1976 528.6782 28.9688 245.7210 1.9048

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180170.688 0.446 656.121 637739.500 0.368670E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.061 EfDer = 1.000 SH = 0.368670E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.442 3567.117 7.951 528.678 1.000 1.000 0.980

 W Kg/sec = 29.292 Wdry = 64.439 WH2O = 0.002 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.289 3533.294 1.381 0.248 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 103628.922 50563.492 1.549 545.479 352.122 424.468 1.205

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 455.95 -0.16 455.95 0.41 0.70 618.82

 MEAN 17.74 0.00 -0.02 455.95 -0.16 455.95 0.41 0.65

 HUB 15.05 0.00 -0.02 455.95 -0.16 455.95 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.88 46.36 7.52 624.76 773.57 7.08 511.97 491.95 0.22

 MEAN 50.46 43.40 7.06 552.18 716.22 7.08 511.97 491.95 0.22

 HUB 45.79 38.84 6.95 468.49 653.85 7.08 511.97 491.95 0.22

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 542.12 292.09 456.71 1125.18 0.48 2.26 1.98 8.75

 MEAN 17.51 554.57 303.82 463.94 1121.56 0.49 2.34 2.07 6.78

 HUB 14.85 602.57 374.93 471.72 1118.15 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 616.66 560.29 324.57 0.50 5789.48 0.92 0.91

 MEAN 544.96 522.86 241.14 0.47 5321.69 0.92 0.91 0.91 1.48

 HUB 462.27 479.74 87.34 0.43 5570.07 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.49 1.19 8.11 557.65 1.05 534.03 505.38 0.11

 MEAN 9.36 1.18 7.94 555.31 1.05 530.59 504.36 0.13

 HUB 9.43 1.19 7.76 556.56 1.05 527.37 504.92 0.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.60 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.22 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.48 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 611.7420 305.8172 529.8152 1117.1151 0.5476 -0.1612 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4128 7.6960 526.4280 504.8767 0.1405 29.9942 31.5000 1.5058

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 511.4362 111.5664 499.1192 1126.6848 0.4539 0.1575 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.3950 8.1712 535.4832 504.8141 451.3937 0.0219 0.3270

 

NASA/TM—2013-218094 H–213
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 521.6844 0.0000 521.6844 1125.7668 0.4634 0.2378 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1043 534.6345 504.7725 0.0000 0.0600 0.0374 0.1127

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8820 9.3720 1.1788 556.5076 27.8298 235.9462 1.8290

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 173140.000 0.455 630.518 611826.250 0.368670E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.295 EfDer = 1.000 SH = 0.368670E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.442 3567.117 9.372 556.507 1.000 1.000 0.980

 W Kg/sec = 29.292 Wdry = 64.439 WH2O = 0.002 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.696 3443.816 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 91214.523 50563.492 1.675 513.330 306.491 395.845 1.292

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 426.46 -0.15 426.46 0.38 0.65 578.80

 MEAN 16.97 0.00 -0.02 426.46 -0.15 426.46 0.38 0.60

 HUB 14.32 0.00 -0.02 426.46 -0.15 426.46 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.58 46.36 8.22 599.54 735.86 8.51 541.89 504.75 0.09

 MEAN 51.10 43.80 7.30 528.28 679.05 8.51 541.89 504.75 0.09

 HUB 46.28 37.84 8.44 445.77 617.01 8.51 541.89 504.75 0.09

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 513.89 282.45 429.30 1154.18 0.45 2.16 1.89 8.34

 MEAN 16.57 523.13 289.56 435.69 1150.64 0.45 2.24 1.97 6.35

 HUB 13.89 564.75 350.86 442.53 1147.27 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 587.71 526.77 305.27 0.46 5335.48 0.92 0.91

 MEAN 515.93 490.98 226.37 0.43 4801.58 0.92 0.91 0.91 1.50

 HUB 432.38 449.98 81.52 0.39 4875.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.95 1.17 9.57 583.20 1.05 561.98 515.90 0.06

 MEAN 10.78 1.15 9.38 580.53 1.04 558.54 514.84 0.06

 HUB 10.81 1.15 9.18 580.90 1.04 555.27 514.99 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.34 35.42 31.50 3.92 0.93 0.42 1.40

 MEAN 33.61 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.41 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 563.0238 291.1856 481.8784 1148.0577 0.4904 -0.1131 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8324 9.2089 556.0745 515.2230 0.0641 31.1434 32.4000 1.2566

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 477.1283 107.0059 464.9743 1155.4420 0.4129 0.1765 2.2705

 

NASA/TM—2013-218094 H–214
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8184 9.6348 563.2532 515.1827 432.2457 0.0195 0.3460

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 473.2194 0.0000 473.2194 1155.7242 0.4095 0.2595 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6302 563.5534 515.1340 0.0000 0.0600 0.0371 0.1733

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8822 10.7924 1.1516 581.5439 25.0371 239.5667 1.8571

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 155824.125 0.451 567.459 607061.688 0.368670E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.452 EfDer = 0.999 SH = 0.368670E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.442 3567.117 10.792 581.544 1.000 1.000 0.980

 W Kg/sec = 29.292 Wdry = 64.439 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.939 3368.870 1.381 0.249 53.349 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 81465.781 50563.492 1.873 509.668 272.089 384.739 1.414 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 383.62 -0.13 383.62 0.33 0.59 538.57

 MEAN 15.91 0.00 -0.02 383.62 -0.13 383.62 0.33 0.54

 HUB 13.07 0.00 -0.02 383.62 -0.13 383.62 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.08 47.36 8.72 570.28 687.41 10.02 569.72 515.12 0.05

 MEAN 52.25 44.80 7.45 495.36 626.63 10.02 569.72 515.12 0.05

 HUB 46.69 38.84 7.85 406.86 559.29 10.02 569.72 515.12 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 479.62 280.08 389.35 1180.71 0.41 2.05 1.78 7.43

 MEAN 15.50 482.40 276.13 395.56 1176.74 0.41 2.13 1.86 5.75

 HUB 12.59 512.72 318.09 402.12 1172.91 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 558.45 478.63 278.38 0.41 5026.98 0.92 0.91

 MEAN 482.42 446.12 206.30 0.38 4281.45 0.92 0.91 0.91 1.55

 HUB 391.91 408.84 73.82 0.35 4006.48 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.42 1.15 11.10 606.68 1.04 588.21 524.83 0.03

 MEAN 12.17 1.13 10.86 602.96 1.04 584.26 523.43 0.03

 HUB 12.08 1.12 10.61 601.58 1.03 580.46 522.92 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.73 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 34.92 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.35 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 534.7756 281.1927 454.8798 1173.1803 0.4558 -0.1910 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.1954 10.5950 580.7713 523.6850 0.0360 31.7231 33.0000 1.2769

 

NASA/TM—2013-218094 H–215
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 459.7983 104.9953 447.6499 1179.2130 0.3899 0.0880 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1731 10.9765 586.7603 523.6367 410.5396 0.0363 0.3566

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 445.8129 0.0000 445.8129 1180.2103 0.3777 0.2810 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0447 587.7789 523.6331 0.0000 0.0600 0.0372 0.1379

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8834 12.1719 1.1278 603.7394 22.1963 247.7261 1.9204

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 138202.250 0.443 503.286 619024.500 0.368823E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3065 Tt4 = 603.7394 T1 = 462.0942

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 881221.63 3209.1138 173.0331 2.3556 0.8699 5.9706 1.3065 37.3740

NASA/TM—2013-218094 H–216
 100μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.965 EfDer = 0.985 SH = 0.897218E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.939 3973.479 5.167 482.274 1.000 1.000 0.980

 W Kg/sec = 33.608 Wdry = 73.932 WH2O = 0.007 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.826 4120.801 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171035.109 58013.906 1.401 831.557 593.718 619.754 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 493.63 -0.17 493.63 0.47 0.83 741.85

 MEAN 17.06 0.00 -0.02 493.63 -0.17 493.63 0.47 0.74

 HUB 12.51 0.00 -0.02 493.63 -0.17 493.63 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.40 50.47 4.93 715.35 869.28 4.45 462.68 465.16 2.54

 MEAN 50.16 47.20 2.96 591.56 770.60 4.45 462.68 465.16 2.54

 HUB 41.32 38.62 2.70 433.79 657.26 4.45 462.68 465.16 2.54

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 741.45 362.62 646.73 1066.62 0.70 7.29 6.52 16.04

 MEAN 18.04 787.16 421.44 664.84 1061.11 0.74 7.43 6.80 12.53

 HUB 15.00 929.01 591.97 715.98 1047.10 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.35 736.66 352.73 0.69 7484.40 0.92 0.90

 MEAN 625.40 695.42 203.96 0.66 7604.03 0.92 0.90 0.90 1.21

 HUB 520.13 719.57 71.85 0.69 8881.72 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.31 4.93 524.02 1.09 479.80 488.31 1.32

 MEAN 6.81 1.32 4.75 524.68 1.09 474.85 488.79 1.57

 HUB 7.12 1.38 4.29 531.81 1.10 462.40 492.93 2.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.28 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.37 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.58 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 850.0397 420.6230 738.6771 1054.2437 0.8063 -0.1058 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8829 4.5074 468.7258 490.0532 1.9615 29.6584 35.4000 5.7416

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 691.6898 169.2084 670.6737 1076.0887 0.6428 0.2316 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.8126 5.1763 488.3607 489.3307 554.9116 0.0412 0.3614

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 693.1922 0.0000 693.1922 1075.8815 0.6443 0.2573 1.3089

NASA/TM—2013-218094 H–217
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1187 488.1987 489.1814 0.0000 0.0600 0.0712 0.2060

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8262 6.7452 1.3054 526.8347 44.5608 237.3056 1.8396

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 277084.219 0.541 1157.753 817719.188 0.902295E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.611 EfDer = 0.990 SH = 0.903139E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.939 3973.479 6.745 526.835 1.000 1.000 0.980

 W Kg/sec = 33.608 Wdry = 73.932 WH2O = 0.007 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.396 3942.683 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149454.781 58013.898 1.242 590.487 475.379 468.502 0.986

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 607.45 -0.21 607.45 0.56 0.86 707.03

 MEAN 18.08 0.00 -0.02 607.45 -0.21 607.45 0.56 0.80

 HUB 15.21 0.00 -0.02 607.45 -0.21 607.45 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.56 46.36 3.20 712.57 936.51 5.47 497.17 489.04 0.72

 MEAN 45.91 42.30 3.61 626.87 873.05 5.47 497.17 489.04 0.72

 HUB 40.98 37.84 3.14 527.41 804.60 5.47 497.17 489.04 0.72

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 660.23 282.69 596.65 1114.62 0.59 2.33 2.04 9.02

 MEAN 18.01 680.32 308.21 606.50 1110.99 0.61 2.40 2.13 7.35

 HUB 15.22 742.70 412.87 617.36 1107.74 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.07 732.75 425.37 0.66 5776.93 0.92 0.91

 MEAN 624.50 684.02 316.29 0.62 5554.64 0.92 0.91 0.91 1.37

 HUB 527.86 627.98 114.99 0.57 6288.34 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.20 1.22 6.49 559.05 1.06 524.00 503.42 0.32

 MEAN 8.14 1.21 6.34 557.81 1.06 520.59 502.93 0.35

 HUB 8.34 1.24 6.19 561.90 1.07 517.55 504.71 0.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.35 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 26.94 27.54 23.50 4.04 0.92 0.32 1.63

 HUB 33.77 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 779.0581 309.0756 715.1251 1100.4442 0.7079 -0.2339 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2074 5.8972 510.7946 503.7718 0.4620 23.3739 30.6000 7.2261

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 672.5429 142.5839 657.2548 1113.7645 0.6038 0.0264 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1491 6.3883 523.2208 503.4864 491.5697 0.0409 0.2242

 

NASA/TM—2013-218094 H–218
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 715.2482 0.0000 715.2482 1108.6603 0.6451 0.1028 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1347 518.4616 503.4027 0.0000 0.0600 0.0725 -0.1078

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8274 8.0894 1.1993 559.5825 32.7480 279.3839 2.1658

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 203721.531 0.406 851.218 740140.375 0.903604E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.984 EfDer = 0.992 SH = 0.903604E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.939 3973.479 8.089 559.582 1.000 1.000 0.980

 W Kg/sec = 33.608 Wdry = 73.932 WH2O = 0.007 lbm/sec H2O = 0.050g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.555 3825.578 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 128663.164 58013.895 1.335 545.479 408.538 424.468 1.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 566.09 -0.19 566.09 0.50 0.80 670.01

 MEAN 17.74 0.00 -0.02 566.09 -0.19 566.09 0.50 0.74

 HUB 15.05 0.00 -0.02 566.09 -0.19 566.09 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.88 46.36 4.52 695.93 897.25 6.82 533.83 503.26 0.24

 MEAN 47.38 43.40 3.98 615.08 836.08 6.82 533.83 503.26 0.24

 HUB 42.68 38.84 3.84 521.86 770.07 6.82 533.83 503.26 0.24

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 630.13 285.76 561.61 1151.41 0.55 2.26 1.98 8.75

 MEAN 17.51 648.27 309.02 569.87 1148.04 0.56 2.34 2.07 6.78

 HUB 14.85 707.24 406.13 579.00 1144.98 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.91 690.16 401.15 0.60 5664.90 0.92 0.91

 MEAN 607.04 643.10 298.02 0.56 5413.30 0.92 0.91 0.91 1.40

 HUB 514.93 589.13 108.79 0.51 6034.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.70 1.20 7.93 591.16 1.06 559.24 515.74 0.12

 MEAN 9.62 1.19 7.77 589.75 1.05 555.98 515.22 0.13

 HUB 9.81 1.21 7.61 593.21 1.06 553.01 516.55 0.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.97 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.47 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 35.05 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 730.5581 311.0457 661.0339 1140.2324 0.6407 -0.2031 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.6880 7.3742 548.4911 515.8463 0.1594 25.1991 31.5000 6.3009

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 637.6495 139.0989 622.2928 1150.8127 0.5541 0.0405 2.3726

 

NASA/TM—2013-218094 H–219
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.6409 7.8460 558.7028 515.6786 451.3937 0.0342 0.2569

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 654.7361 0.0000 654.7361 1148.9556 0.5699 0.1487 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7183 556.9334 515.5870 0.0000 0.0600 0.0584 -0.0253

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8480 9.5940 1.1860 591.3747 31.7926 264.9568 2.0539

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 197864.688 0.419 826.747 700090.000 0.904037E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.566 EfDer = 0.995 SH = 0.904037E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.939 3973.479 9.594 591.375 1.000 1.000 0.980

 W Kg/sec = 33.608 Wdry = 73.932 WH2O = 0.007 lbm/sec H2O = 0.058g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.966 3721.326 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111915.844 58013.898 1.450 513.330 354.143 395.845 1.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 523.25 -0.18 523.25 0.45 0.73 625.44

 MEAN 16.97 0.00 -0.02 523.25 -0.18 523.25 0.45 0.68

 HUB 14.32 0.00 -0.02 523.25 -0.18 523.25 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.93 46.36 5.57 667.84 848.55 8.36 569.38 515.53 0.10

 MEAN 48.37 43.80 4.57 588.46 787.58 8.36 569.38 515.53 0.10

 HUB 43.51 37.84 5.67 496.55 721.47 8.36 569.38 515.53 0.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 593.30 281.80 522.11 1185.29 0.50 2.16 1.89 8.34

 MEAN 16.57 607.85 297.99 529.80 1181.76 0.51 2.24 1.97 6.35

 HUB 13.89 659.53 381.29 538.15 1178.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.67 641.58 372.87 0.54 5323.81 0.92 0.91 

 MEAN 574.70 597.71 276.72 0.51 4941.83 0.92 0.91 0.91 1.42

 HUB 481.64 547.42 100.34 0.46 5298.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.28 1.18 9.53 621.03 1.05 592.76 526.20 0.06

 MEAN 11.15 1.16 9.33 618.90 1.05 589.22 525.47 0.06

 HUB 11.27 1.17 9.14 620.89 1.05 585.95 526.18 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.36 35.53 31.50 4.03 0.93 0.36 1.40

 MEAN 29.36 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.32 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 662.0808 299.6611 590.3848 1177.5209 0.5623 -0.1357 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 11.2162 9.0742 585.0746 525.9277 0.0672 26.9109 32.4000 5.4891

 

NASA/TM—2013-218094 H–220
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 585.2230 131.2484 570.3155 1185.2461 0.4938 0.0807 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 11.1816 9.4855 592.7725 525.8286 432.2457 0.0282 0.2863

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 580.5613 0.0000 580.5613 1185.6521 0.4897 0.1898 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4807 593.2126 525.7549 0.0000 0.0600 0.0468 0.0782

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8636 11.1462 1.1618 620.2761 28.9020 265.3154 2.0567

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 179974.078 0.420 751.993 685985.188 0.904473E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.153 EfDer = 0.997 SH = 0.904473E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 73.939 3973.479 11.146 620.276 1.000 1.000 0.980

 W Kg/sec = 33.608 Wdry = 73.932 WH2O = 0.007 lbm/sec H2O = 0.065g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.634 3633.595 1.380 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98516.492 58013.895 1.632 509.668 312.212 384.739 1.232

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 463.91 -0.16 463.91 0.39 0.66 580.89

 MEAN 15.91 0.00 -0.02 463.91 -0.16 463.91 0.39 0.60

 HUB 13.07 0.00 -0.02 463.91 -0.16 463.91 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.87 47.36 6.51 635.25 786.74 10.06 603.00 525.73 0.05

 MEAN 49.95 44.80 5.15 551.79 721.01 10.06 603.00 525.73 0.05

 HUB 44.34 38.84 5.50 453.20 648.65 10.06 603.00 525.73 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 548.00 287.03 466.82 1216.81 0.45 2.05 1.78 7.43

 MEAN 15.50 555.70 288.71 474.81 1212.48 0.46 2.13 1.86 5.75

 HUB 12.59 594.95 347.02 483.26 1208.35 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.07 574.60 335.04 0.47 5152.30 0.92 0.91

 MEAN 537.38 535.99 248.67 0.44 4476.82 0.92 0.91 0.91 1.47

 HUB 436.56 491.49 89.54 0.41 4371.01 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.95 1.16 11.29 648.96 1.05 624.85 535.35 0.03

 MEAN 12.70 1.14 11.02 645.20 1.04 620.41 534.13 0.03

 HUB 12.66 1.14 10.75 644.61 1.04 616.20 533.95 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.59 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.30 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.68 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 623.9541 294.0019 550.3468 1207.1251 0.5169 -0.2161 2.0437

 

NASA/TM—2013-218094 H–221
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.7371 10.6404 615.0118 534.4249 0.0365 28.1117 33.0000 4.8883

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 557.6608 127.3423 542.9268 1213.2852 0.4596 -0.0139 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.6853 10.9956 621.2975 534.3098 410.5396 0.0495 0.3066

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 538.9975 0.0000 538.9975 1214.8573 0.4437 0.2235 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1089 622.9433 534.3220 0.0000 0.0600 0.0447 0.0508

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8706 12.6938 1.1388 646.2559 25.9807 269.5089 2.0892

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161885.266 0.418 676.412 691053.000 0.904980E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3400 Tt4 = 646.2559 T1 = 482.2743

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1020529.75 4264.1230 202.8258 2.4566 0.8273 2.9646 1.3400 37.3740

NASA/TM—2013-218094 H–222
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 75.6% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.307 EfDer = 0.998 SH = 0.900838E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.277 3704.934 5.167 482.274 1.000 1.000 0.980

 W Kg/sec = 29.672 Wdry = 65.272 WH2O = 0.006 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 179.066 3842.299 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146647.234 51218.059 1.586 831.557 524.171 619.754 1.182

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 423.25 -0.15 423.25 0.40 0.75 691.71

 MEAN 17.06 0.00 -0.02 423.25 -0.15 423.25 0.40 0.66

 HUB 12.51 0.00 -0.02 423.25 -0.15 423.25 0.40 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.61 50.47 7.14 667.00 790.08 4.63 467.87 465.06 2.09

 MEAN 52.51 47.20 5.31 551.58 695.37 4.63 467.87 465.06 2.09

 HUB 43.71 38.62 5.09 404.47 585.53 4.63 467.87 465.06 2.09

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 659.85 369.02 547.01 1074.43 0.61 7.29 6.52 16.04

 MEAN 18.04 696.00 411.09 561.62 1068.93 0.65 7.43 6.80 12.53

 HUB 15.00 803.67 543.77 591.78 1058.75 0.76 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.00 622.91 297.98 0.58 7615.95 0.92 0.91

 MEAN 583.13 587.38 172.04 0.55 7417.00 0.92 0.91 0.91 1.31

 HUB 484.97 594.70 58.79 0.56 8158.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.22 521.88 1.08 486.86 487.13 1.04

 MEAN 6.67 1.29 5.03 520.84 1.08 481.89 486.70 1.24

 HUB 6.84 1.32 4.69 524.70 1.09 472.76 488.92 1.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.00 28.58 24.20 4.38 0.93 0.34 1.80

 MEAN 36.20 17.03 12.70 4.33 0.92 0.29 2.22

 HUB 42.58 -5.67 -9.30 3.63 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 737.7123 410.2960 613.0878 1065.3943 0.6924 -0.0775 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7224 4.8967 478.7084 487.5707 1.3817 33.7916 35.4000 1.6084

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 581.4529 142.2411 563.7863 1083.6749 0.5366 0.3031 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6910 5.5135 495.2854 487.1888 554.9116 0.0278 0.4162

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 577.3900 0.0000 577.3900 1084.0654 0.5326 0.3351 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5085 495.6672 487.1297 0.0000 0.0600 0.0418 0.3003

NASA/TM—2013-218094 H–223
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8741 6.6665 1.2902 522.4709 40.1975 221.3351 1.7158

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 249973.344 0.562 922.123 701120.500 0.907373E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.281 EfDer = 1.000 SH = 0.910017E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.277 3704.934 6.666 522.471 1.000 1.000 0.980

 W Kg/sec = 29.672 Wdry = 65.271 WH2O = 0.006 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 144.463 3691.540 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 126905.984 51218.039 1.396 590.487 422.889 468.502 1.108

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 515.80 -0.18 515.80 0.47 0.77 661.99

 MEAN 18.08 0.00 -0.02 515.80 -0.18 515.80 0.47 0.72

 HUB 15.21 0.00 -0.02 515.80 -0.18 515.80 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.18 46.36 5.82 664.42 841.27 5.73 501.08 487.07 0.65

 MEAN 48.58 42.30 6.28 584.50 779.68 5.73 501.08 487.07 0.65

 HUB 43.64 37.84 5.80 491.76 712.78 5.73 501.08 487.07 0.65

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 591.36 297.50 511.08 1116.69 0.53 2.33 2.04 9.02

 MEAN 18.01 606.94 312.47 520.33 1112.61 0.55 2.40 2.13 7.35

 HUB 15.22 661.04 394.75 530.24 1108.84 0.60 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.21 626.71 362.71 0.56 6078.68 0.92 0.91

 MEAN 582.29 586.12 269.82 0.53 5630.86 0.92 0.91 0.91 1.44

 HUB 492.18 539.12 97.44 0.49 6011.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.10 1.22 6.71 554.07 1.06 525.96 501.58 0.31

 MEAN 7.99 1.20 6.54 551.74 1.06 522.13 500.59 0.34

 HUB 8.09 1.21 6.38 553.72 1.06 518.59 501.50 0.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.20 35.36 31.50 3.86 0.93 0.38 1.40

 MEAN 30.99 27.41 23.50 3.91 0.93 0.37 1.63

 HUB 36.67 10.41 6.50 3.91 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 677.6141 313.3513 600.8093 1106.3220 0.6125 -0.1838 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0442 6.2634 516.2715 501.2531 0.4047 27.5442 30.6000 3.0558

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 566.9032 120.1875 554.0164 1118.1306 0.5070 0.1325 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0198 6.7437 527.3459 501.0929 491.5697 0.0261 0.2906

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 593.0759 0.0000 593.0759 1115.5172 0.5317 0.1963 0.5911

NASA/TM—2013-218094 H–224
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6130 524.9089 501.0640 0.0000 0.0600 0.0406 0.0464

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8766 7.9977 1.1997 553.1797 30.7092 251.8978 1.9527

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191044.125 0.438 704.740 630216.000 0.910659E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.474 EfDer = 1.000 SH = 0.910659E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.277 3704.934 7.998 553.180 1.000 1.000 0.980

 W Kg/sec = 29.672 Wdry = 65.271 WH2O = 0.006 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 123.905 3587.612 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109895.930 51218.039 1.504 545.479 362.725 424.468 1.170 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 483.52 -0.17 483.52 0.43 0.72 628.33

 MEAN 17.74 0.00 -0.02 483.52 -0.17 483.52 0.43 0.67

 HUB 15.05 0.00 -0.02 483.52 -0.17 483.52 0.43 0.61

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.32 46.36 6.96 648.90 809.37 7.06 534.39 500.99 0.24

 MEAN 49.87 43.40 6.47 573.51 750.27 7.06 534.39 500.99 0.24

 HUB 45.19 38.84 6.35 486.59 686.09 7.06 534.39 500.99 0.24

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 567.09 296.71 483.27 1150.02 0.49 2.26 1.98 8.75

 MEAN 17.51 580.90 310.58 490.91 1146.34 0.51 2.34 2.07 6.78

 HUB 14.85 631.88 387.47 499.13 1142.89 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.49 593.07 343.78 0.52 5881.21 0.92 0.91

 MEAN 566.02 553.39 255.43 0.48 5440.17 0.92 0.91 0.91 1.47

 HUB 480.13 507.66 92.65 0.44 5756.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.56 1.20 8.12 583.74 1.06 557.90 513.46 0.13

 MEAN 9.44 1.18 7.94 581.45 1.05 554.33 512.58 0.14

 HUB 9.53 1.19 7.76 583.09 1.05 551.01 513.25 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.55 35.43 31.50 3.93 0.93 0.40 1.40

 MEAN 32.32 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.82 10.52 6.50 4.02 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 642.9754 312.6195 561.8598 1141.3281 0.5634 -0.1678 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4937 7.6742 549.5450 513.0925 0.1617 29.0916 31.5000 2.4084

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 542.1503 118.2664 529.0935 1151.2593 0.4709 0.1373 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4728 8.1535 559.1454 512.9935 451.3937 0.0233 0.3143

 

NASA/TM—2013-218094 H–225
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 553.3060 0.0000 553.3060 1150.2192 0.4810 0.2237 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0812 558.1668 512.9470 0.0000 0.0600 0.0386 0.0912

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 9.4488 1.1814 582.7626 29.5834 240.9948 1.8682

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184114.906 0.449 679.179 603155.063 0.911247E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.798 EfDer = 1.000 SH = 0.911247E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.277 3704.934 9.449 582.763 1.000 1.000 0.980

 W Kg/sec = 29.672 Wdry = 65.271 WH2O = 0.006 lbm/sec H2O = 0.059g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.645 3495.367 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96433.203 51218.035 1.629 513.330 315.144 395.845 1.256

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 450.86 -0.16 450.86 0.39 0.66 587.47

 MEAN 16.97 0.00 -0.02 450.86 -0.16 450.86 0.39 0.61

 HUB 14.32 0.00 -0.02 450.86 -0.16 450.86 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.10 46.36 7.74 622.71 768.92 8.52 566.43 512.91 0.11

 MEAN 50.60 43.80 6.80 548.69 710.29 8.52 566.43 512.91 0.11

 HUB 45.77 37.84 7.93 462.99 646.36 8.52 566.43 512.91 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 536.83 288.08 452.98 1180.41 0.45 2.16 1.89 8.34

 MEAN 16.57 547.22 296.76 459.77 1176.78 0.47 2.24 1.97 6.35

 HUB 13.89 591.43 362.85 467.04 1173.34 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 610.42 555.97 322.34 0.47 5441.90 0.92 0.91

 MEAN 535.86 518.22 239.10 0.44 4921.02 0.92 0.91 0.91 1.49

 HUB 449.09 474.93 86.23 0.40 5042.27 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.06 1.17 9.61 611.03 1.05 587.88 523.44 0.07

 MEAN 10.90 1.15 9.41 608.32 1.04 584.27 522.47 0.07

 HUB 10.94 1.16 9.21 608.95 1.04 580.86 522.71 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.45 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 32.84 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 37.84 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 590.0931 298.4244 509.0705 1173.9036 0.5027 -0.1166 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9487 9.2336 581.4711 522.8550 0.0761 30.3794 32.4000 2.0206

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 504.0080 113.0343 491.1693 1181.5120 0.4266 0.1602 2.2705

 

NASA/TM—2013-218094 H–226
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.9325 9.6624 589.0352 522.7950 432.2457 0.0205 0.3352

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 499.8763 0.0000 499.8763 1181.8158 0.4230 0.2476 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6582 589.3709 522.7390 0.0000 0.0600 0.0380 0.1574

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 10.9053 1.1542 609.4354 26.6735 243.8912 1.8906

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 166086.563 0.446 612.674 597183.750 0.912122E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.043 EfDer = 1.000 SH = 0.912167E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 65.277 3704.934 10.905 609.435 1.000 1.000 0.980

 W Kg/sec = 29.672 Wdry = 65.271 WH2O = 0.006 lbm/sec H2O = 0.067g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.378 3418.021 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85869.484 51218.043 1.825 509.668 279.251 384.739 1.378

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 404.35 -0.14 404.35 0.34 0.60 546.43

 MEAN 15.91 0.00 -0.02 404.35 -0.14 404.35 0.34 0.55

 HUB 13.07 0.00 -0.02 404.35 -0.14 404.35 0.34 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.69 47.36 8.33 592.32 717.29 10.08 596.31 522.72 0.06

 MEAN 51.84 44.80 7.04 514.49 654.48 10.08 596.31 522.72 0.06

 HUB 46.27 38.84 7.43 422.57 584.97 10.08 596.31 522.72 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.15 286.92 409.67 1208.27 0.41 2.05 1.78 7.43

 MEAN 15.50 503.84 283.78 416.32 1204.16 0.42 2.13 1.86 5.75

 HUB 12.59 536.29 329.22 423.34 1200.19 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 580.03 503.73 293.11 0.42 5149.95 0.92 0.91

 MEAN 501.06 469.61 217.28 0.39 4400.14 0.92 0.91 0.91 1.53

 HUB 407.06 430.44 77.84 0.36 4146.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.58 1.15 11.20 636.17 1.04 616.09 532.01 0.04

 MEAN 12.32 1.13 10.94 632.28 1.04 611.90 530.70 0.04

 HUB 12.24 1.12 10.69 630.96 1.04 607.87 530.26 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.01 35.58 31.50 4.08 0.93 0.44 1.40

 MEAN 34.28 27.56 23.50 4.06 0.93 0.41 1.64

 HUB 37.87 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 559.7060 288.9846 479.3315 1200.2517 0.4663 -0.1950 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.3519 10.6626 607.9922 530.9499 0.0439 31.0854 33.0000 1.9146

 

NASA/TM—2013-218094 H–227
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.5659 110.6510 471.7632 1206.4524 0.4016 0.0714 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.3262 11.0459 614.2903 530.8844 410.5396 0.0378 0.3477

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 469.6224 0.0000 469.6224 1207.5450 0.3889 0.2712 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.1208 615.4370 530.8816 0.0000 0.0600 0.0379 0.1234

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8824 12.3262 1.1303 633.1369 23.7023 251.3574 1.9485

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 147666.469 0.439 544.725 607700.438 0.913236E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3128 Tt4 = 633.1369 T1 = 482.2739

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 938885.38 3463.4404 179.0664 2.3855 0.8662 5.3072 1.3128 37.3740

NASA/TM—2013-218094 H–228
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 72.7% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.648 EfDer = 0.999 SH = 0.901338E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.164 3675.064 5.167 482.274 1.000 1.000 0.980

 W Kg/sec = 29.165 Wdry = 64.158 WH2O = 0.006 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 176.012 3811.322 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 143680.688 50344.387 1.614 831.557 515.230 619.754 1.203

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 414.68 -0.14 414.68 0.39 0.74 686.13

 MEAN 17.06 0.00 -0.02 414.68 -0.14 414.68 0.39 0.65

 HUB 12.51 0.00 -0.02 414.68 -0.14 414.68 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.93 50.47 7.46 661.62 780.96 4.65 468.45 465.06 2.05

 MEAN 52.85 47.20 5.65 547.14 686.64 4.65 468.45 465.06 2.05

 HUB 44.06 38.62 5.44 401.21 577.10 4.65 468.45 465.06 2.05

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 650.82 370.08 535.36 1075.25 0.61 7.29 6.52 16.04

 MEAN 18.04 685.77 410.15 549.60 1069.75 0.64 7.43 6.80 12.53

 HUB 15.00 790.06 538.48 578.13 1059.87 0.75 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.62 609.59 291.54 0.57 7637.69 0.92 0.91

 MEAN 578.43 574.78 168.28 0.54 7399.91 0.92 0.91 0.91 1.33

 HUB 481.06 580.97 57.41 0.55 8078.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.30 5.25 521.67 1.08 487.61 487.01 1.02

 MEAN 6.65 1.29 5.06 520.44 1.08 482.62 486.48 1.21

 HUB 6.80 1.32 4.72 523.94 1.09 473.75 488.51 1.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.66 28.57 24.20 4.37 0.93 0.35 1.80

 MEAN 36.73 17.02 12.70 4.32 0.92 0.30 2.22

 HUB 42.97 -5.67 -9.30 3.63 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 725.6160 409.3535 599.1230 1066.4725 0.6804 -0.0748 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7048 4.9354 479.6794 487.3197 1.3369 34.3430 35.4000 1.0570

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 568.9033 139.1711 551.6179 1084.4479 0.5246 0.3123 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6758 5.5469 495.9937 486.9605 554.9116 0.0270 0.4235

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 564.6969 0.0000 564.6969 1084.8433 0.5205 0.3441 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5442 496.3801 486.9075 0.0000 0.0600 0.0398 0.3108

NASA/TM—2013-218094 H–229
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8772 6.6539 1.2877 522.0181 39.7448 219.1714 1.6990

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 247159.781 0.565 896.192 686937.563 0.908100E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.637 EfDer = 1.000 SH = 0.911773E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.164 3675.064 6.654 522.018 1.000 1.000 0.980

 W Kg/sec = 29.165 Wdry = 64.158 WH2O = 0.006 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 142.205 3663.366 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 124317.094 50344.363 1.418 590.487 416.279 468.502 1.125

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 505.28 -0.17 505.28 0.46 0.76 656.94

 MEAN 18.08 0.00 -0.02 505.28 -0.17 505.28 0.46 0.71

 HUB 15.21 0.00 -0.02 505.28 -0.17 505.28 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.53 46.36 6.17 659.06 830.60 5.75 501.49 486.85 0.65

 MEAN 48.94 42.30 6.64 579.79 769.20 5.75 501.49 486.85 0.65

 HUB 44.00 37.84 6.16 487.80 702.44 5.75 501.49 486.85 0.65

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 583.81 299.38 501.20 1116.90 0.52 2.33 2.04 9.02

 MEAN 18.01 598.74 313.14 510.32 1112.79 0.54 2.40 2.13 7.35

 HUB 15.22 651.76 392.80 520.10 1108.97 0.59 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.89 614.48 355.51 0.55 6116.99 0.92 0.91

 MEAN 577.60 574.77 264.45 0.52 5642.84 0.92 0.91 0.91 1.45

 HUB 488.22 528.78 95.41 0.48 5982.28 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.09 1.22 6.73 553.56 1.06 526.16 501.38 0.31

 MEAN 7.97 1.20 6.56 551.12 1.06 522.30 500.33 0.34

 HUB 8.05 1.21 6.39 552.87 1.06 518.72 501.14 0.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.85 35.35 31.50 3.85 0.93 0.39 1.40

 MEAN 31.53 27.39 23.50 3.89 0.93 0.38 1.63

 HUB 37.06 10.40 6.50 3.90 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 666.7773 314.0220 588.2024 1106.8636 0.6024 -0.1789 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0207 6.2947 516.7776 500.9747 0.4001 28.0963 30.6000 2.5037

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 555.2038 117.7072 542.5829 1118.5430 0.4964 0.1450 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9985 6.7733 527.7363 500.8232 491.5697 0.0250 0.2987

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 580.2643 0.0000 580.2643 1116.0930 0.5199 0.2062 0.5911

NASA/TM—2013-218094 H–230
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6506 525.4521 500.7966 0.0000 0.0600 0.0388 0.0619

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 7.9782 1.1990 552.5146 30.4969 248.5946 1.9271

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189724.063 0.442 687.932 617129.375 0.912479E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.792 EfDer = 1.000 SH = 0.912479E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.164 3675.064 7.978 552.515 1.000 1.000 0.980

 W Kg/sec = 29.165 Wdry = 64.158 WH2O = 0.006 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.015 3560.830 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 107788.289 50344.367 1.527 545.479 357.194 424.468 1.188

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 474.25 -0.16 474.25 0.42 0.71 623.64

 MEAN 17.74 0.00 -0.02 474.25 -0.16 474.25 0.42 0.66

 HUB 15.05 0.00 -0.02 474.25 -0.16 474.25 0.42 0.60

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.62 46.36 7.26 643.66 799.64 7.07 534.44 500.73 0.24

 MEAN 50.19 43.40 6.79 568.89 740.77 7.07 534.44 500.73 0.24

 HUB 45.51 38.84 6.67 482.67 676.78 7.07 534.44 500.73 0.24

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 560.27 297.98 474.46 1149.85 0.49 2.26 1.98 8.75

 MEAN 17.51 573.51 310.81 481.99 1146.14 0.50 2.34 2.07 6.78

 HUB 14.85 623.49 385.42 490.09 1142.67 0.55 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 635.33 582.16 337.34 0.51 5906.31 0.92 0.91

 MEAN 561.45 543.26 250.64 0.47 5444.09 0.92 0.91 0.91 1.48

 HUB 476.25 498.44 90.83 0.44 5725.94 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.54 1.20 8.12 582.96 1.06 557.73 513.19 0.13

 MEAN 9.41 1.18 7.94 580.58 1.05 554.14 512.27 0.15

 HUB 9.48 1.19 7.77 582.03 1.05 550.79 512.86 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.13 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.82 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.18 10.50 6.50 4.00 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 633.6123 312.8485 550.9904 1141.3845 0.5551 -0.1642 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4599 7.6929 549.5990 512.7682 0.1622 29.5876 31.5000 1.9124

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 531.7227 115.9917 518.9171 1151.2521 0.4619 0.1485 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.4407 8.1715 559.1389 512.6740 451.3937 0.0225 0.3214

 

NASA/TM—2013-218094 H–231
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 542.5060 0.0000 542.5060 1150.2648 0.4716 0.2316 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1021 558.2114 512.6284 0.0000 0.0600 0.0379 0.1032

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 9.4172 1.1804 581.8563 29.3422 238.2065 1.8466

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182613.891 0.452 662.151 591383.188 0.913114E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.075 EfDer = 1.000 SH = 0.913114E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.164 3675.064 9.417 581.856 1.000 1.000 0.980

 W Kg/sec = 29.165 Wdry = 64.158 WH2O = 0.006 lbm/sec H2O = 0.060g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.081 3469.886 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 94715.336 50344.363 1.653 513.330 310.565 395.845 1.275

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 442.83 -0.15 442.83 0.38 0.66 583.18

 MEAN 16.97 0.00 -0.02 442.83 -0.15 442.83 0.38 0.61

 HUB 14.32 0.00 -0.02 442.83 -0.15 442.83 0.38 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.37 46.36 8.01 617.69 760.15 8.53 566.10 512.59 0.11

 MEAN 50.88 43.80 7.08 544.27 701.78 8.53 566.10 512.59 0.11

 HUB 46.05 37.84 8.21 459.26 638.09 8.53 566.10 512.59 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 530.72 288.74 445.30 1179.86 0.45 2.16 1.89 8.34

 MEAN 16.57 540.59 296.60 451.96 1176.23 0.46 2.24 1.97 6.35

 HUB 13.89 583.92 360.82 459.11 1172.78 0.50 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 605.50 546.47 316.76 0.46 5454.43 0.92 0.91

 MEAN 531.54 509.38 234.94 0.43 4918.37 0.92 0.91 0.91 1.50

 HUB 445.47 466.85 84.65 0.40 5013.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 11.02 1.17 9.60 609.96 1.05 587.33 523.09 0.07

 MEAN 10.85 1.15 9.40 607.20 1.04 583.72 522.10 0.07

 HUB 10.88 1.16 9.20 607.69 1.04 580.30 522.30 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.96 35.43 31.50 3.93 0.93 0.42 1.40

 MEAN 33.27 27.47 23.50 3.97 0.93 0.40 1.62

 HUB 38.16 10.45 6.50 3.95 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 582.3169 298.2663 500.1302 1173.4803 0.4962 -0.1146 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.9001 9.2317 581.0500 522.4791 0.0771 30.8109 32.4000 1.5891

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 495.1362 111.0446 482.5235 1181.0708 0.4192 0.1695 2.2705

 

NASA/TM—2013-218094 H–232
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8851 9.6606 588.5941 522.4217 432.2457 0.0199 0.3414

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 491.0772 0.0000 491.0772 1181.3632 0.4157 0.2544 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6561 588.9180 522.3671 0.0000 0.0600 0.0375 0.1666

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8816 10.8586 1.1531 608.2825 26.4269 241.4381 1.8716

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 164549.484 0.449 596.650 586171.875 0.914196E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.279 EfDer = 1.000 SH = 0.914290E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 64.164 3675.064 10.859 608.282 1.000 1.000 0.980

 W Kg/sec = 29.165 Wdry = 64.158 WH2O = 0.006 lbm/sec H2O = 0.067g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 94.065 3393.676 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84457.164 50344.359 1.851 509.668 275.408 384.739 1.397

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 397.70 -0.14 397.70 0.33 0.60 542.54

 MEAN 15.91 0.00 -0.02 397.70 -0.14 397.70 0.33 0.54

 HUB 13.07 0.00 -0.02 397.70 -0.14 397.70 0.33 0.49

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.91 47.36 8.55 587.54 709.60 10.06 595.58 522.35 0.06

 MEAN 52.08 44.80 7.28 510.35 647.12 10.06 595.58 522.35 0.06

 HUB 46.51 38.84 7.67 419.17 577.91 10.06 595.58 522.35 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.92 286.94 403.26 1207.34 0.41 2.05 1.78 7.43

 MEAN 15.50 498.13 283.26 409.76 1203.25 0.41 2.13 1.86 5.75

 HUB 12.59 529.76 327.23 416.62 1199.31 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 575.35 495.78 288.42 0.41 5150.13 0.92 0.91

 MEAN 497.02 462.17 213.77 0.38 4392.01 0.92 0.91 0.91 1.54

 HUB 403.77 423.60 76.55 0.35 4121.56 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.51 1.15 11.16 634.80 1.04 615.14 531.60 0.04

 MEAN 12.26 1.13 10.91 630.90 1.04 610.98 530.28 0.04

 HUB 12.17 1.12 10.66 629.51 1.03 606.97 529.81 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.43 35.57 31.50 4.07 0.93 0.44 1.40

 MEAN 34.66 27.55 23.50 4.05 0.93 0.42 1.64

 HUB 38.15 10.41 6.50 3.91 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 552.7074 288.4526 471.4664 1199.4896 0.4608 -0.1927 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2861 10.6419 607.2162 530.5217 0.0448 31.4591 33.0000 1.5409

 

NASA/TM—2013-218094 H–233
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 476.5431 108.8190 463.9523 1205.6879 0.3952 0.0812 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.2623 11.0262 613.5085 530.4596 410.5396 0.0369 0.3530

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 461.9581 0.0000 461.9581 1206.7365 0.3828 0.2771 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0975 614.6093 530.4556 0.0000 0.0600 0.0374 0.1320

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8830 12.2617 1.1292 631.7364 23.4548 249.2300 1.9320

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 146121.672 0.441 529.831 597109.250 0.915383E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3099 Tt4 = 631.7364 T1 = 482.2738

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 930168.94 3372.7554 176.0119 2.3730 0.8684 5.6480 1.3099 37.3740

NASA/TM—2013-218094 H–234
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 69.9% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.986 EfDer = 0.999 SH = 0.901851E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.052 3644.566 5.167 482.274 1.000 1.000 0.980

 W Kg/sec = 28.660 Wdry = 63.047 WH2O = 0.006 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 172.962 3779.693 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 140751.047 49472.121 1.642 831.557 506.303 619.754 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 406.23 -0.14 406.23 0.39 0.73 680.44

 MEAN 17.06 0.00 -0.02 406.23 -0.14 406.23 0.39 0.64

 HUB 12.51 0.00 -0.02 406.23 -0.14 406.23 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.24 50.47 7.77 656.13 771.83 4.67 469.00 465.05 2.01

 MEAN 53.19 47.20 5.99 542.60 677.93 4.67 469.00 465.05 2.01

 HUB 44.42 38.62 5.80 397.88 568.72 4.67 469.00 465.05 2.01

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 641.98 370.83 524.04 1075.99 0.60 7.29 6.52 16.04

 MEAN 18.04 675.73 409.00 537.89 1070.49 0.63 7.43 6.80 12.53

 HUB 15.00 776.79 533.18 564.91 1060.89 0.73 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.13 596.67 285.30 0.55 7653.19 0.92 0.91

 MEAN 573.63 562.52 164.64 0.53 7379.06 0.92 0.91 0.91 1.34

 HUB 477.07 567.69 56.11 0.54 7999.41 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.30 5.28 521.42 1.08 488.28 486.88 1.00

 MEAN 6.64 1.28 5.09 520.02 1.08 483.30 486.25 1.18

 HUB 6.77 1.31 4.76 523.19 1.08 474.67 488.10 1.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.29 28.57 24.20 4.37 0.93 0.36 1.80

 MEAN 37.25 17.02 12.70 4.32 0.92 0.31 2.22

 HUB 43.34 -5.67 -9.30 3.63 0.92 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 713.8489 408.2022 585.6204 1067.4574 0.6687 -0.0723 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6859 4.9709 480.5669 487.0591 1.2974 34.8781 35.4000 0.5219

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 556.7946 136.2090 539.8772 1085.1255 0.5131 0.3211 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6589 5.5763 496.6151 486.7202 554.9116 0.0263 0.4305

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 552.4993 0.0000 552.4993 1085.5204 0.5090 0.3525 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5754 497.0011 486.6722 0.0000 0.0600 0.0382 0.3205

NASA/TM—2013-218094 H–235
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8798 6.6392 1.2849 521.5433 39.2700 217.0716 1.6827

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244209.359 0.567 870.151 672931.000 0.908733E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.978 EfDer = 1.000 SH = 0.912397E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.052 3644.566 6.639 521.543 1.000 1.000 0.980

 W Kg/sec = 28.660 Wdry = 63.046 WH2O = 0.006 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.988 3634.618 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 121811.773 49472.098 1.441 590.487 409.788 468.502 1.143

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 495.10 -0.17 495.10 0.45 0.75 651.79

 MEAN 18.08 0.00 -0.02 495.10 -0.17 495.10 0.45 0.70

 HUB 15.21 0.00 -0.02 495.10 -0.17 495.10 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.86 46.36 6.50 653.59 820.08 5.77 501.84 486.62 0.64

 MEAN 49.28 42.30 6.98 574.98 758.89 5.77 501.84 486.62 0.64

 HUB 44.35 37.84 6.51 483.75 692.32 5.77 501.84 486.62 0.64

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 576.46 300.87 491.71 1117.01 0.52 2.33 2.04 9.02

 MEAN 18.01 590.75 313.51 500.69 1112.88 0.53 2.40 2.13 7.35

 HUB 15.22 642.70 390.70 510.31 1109.02 0.58 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 649.45 602.74 348.59 0.54 6147.22 0.92 0.91

 MEAN 572.80 563.85 259.29 0.51 5649.41 0.92 0.91 0.91 1.46

 HUB 484.17 518.80 93.47 0.47 5950.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.21 6.74 552.98 1.06 526.26 501.13 0.31

 MEAN 7.94 1.20 6.57 550.43 1.06 522.38 500.05 0.34

 HUB 8.02 1.21 6.40 551.97 1.06 518.76 500.76 0.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.46 35.33 31.50 3.83 0.93 0.40 1.40

 MEAN 32.05 27.38 23.50 3.88 0.93 0.38 1.63

 HUB 37.44 10.38 6.50 3.88 0.93 0.39 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 656.3596 314.3913 576.1649 1107.2787 0.5928 -0.1744 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9927 6.3196 517.1656 500.6682 0.3964 28.6196 30.6000 1.9804

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 544.0760 115.3480 531.7081 1118.8209 0.4863 0.1566 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9725 6.7955 527.9997 500.5244 491.5697 0.0241 0.3060

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 568.2507 0.0000 568.2507 1116.5052 0.5090 0.2145 0.5911

NASA/TM—2013-218094 H–236
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6785 525.8412 500.4972 0.0000 0.0600 0.0379 0.0751

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8804 7.9526 1.1978 551.7946 30.2517 245.5166 1.9032

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188198.766 0.446 670.578 604312.625 0.913128E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 7.084 EfDer = 1.000 SH = 0.913128E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.052 3644.566 7.953 551.794 1.000 1.000 0.980

 W Kg/sec = 28.660 Wdry = 63.046 WH2O = 0.006 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.210 3533.583 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 105791.086 49472.098 1.550 545.479 351.909 424.468 1.206

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 465.46 -0.16 465.46 0.41 0.70 618.87

 MEAN 17.74 0.00 -0.02 465.46 -0.16 465.46 0.41 0.65

 HUB 15.05 0.00 -0.02 465.46 -0.16 465.46 0.41 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.91 46.36 7.55 638.32 790.14 7.08 534.38 500.44 0.24

 MEAN 50.48 43.40 7.08 564.17 731.52 7.08 534.38 500.44 0.24

 HUB 45.81 38.84 6.97 478.66 667.78 7.08 534.38 500.44 0.24

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 553.70 298.73 466.19 1149.53 0.48 2.26 1.98 8.75

 MEAN 17.51 566.38 310.64 473.59 1145.82 0.49 2.34 2.07 6.78

 HUB 14.85 615.38 383.14 481.55 1142.32 0.54 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.05 571.93 331.32 0.50 5921.15 0.92 0.91

 MEAN 556.79 533.74 246.15 0.47 5441.06 0.92 0.91 0.91 1.49

 HUB 472.30 489.74 89.16 0.43 5692.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.50 1.19 8.12 582.06 1.05 557.43 512.86 0.13

 MEAN 9.36 1.18 7.94 579.61 1.05 553.83 511.91 0.15

 HUB 9.43 1.19 7.76 580.89 1.05 550.46 512.44 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.65 35.40 31.50 3.90 0.93 0.41 1.40

 MEAN 33.26 27.46 23.50 3.96 0.93 0.40 1.62

 HUB 38.51 10.49 6.50 3.99 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 624.6964 312.6773 540.8129 1141.2816 0.5474 -0.1610 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4164 7.7004 549.4992 512.3962 0.1629 30.0349 31.5000 1.4651

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 522.0183 113.8748 509.4464 1151.0674 0.4535 0.1585 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.3987 8.1766 558.9594 512.3059 451.3937 0.0219 0.3277

 

NASA/TM—2013-218094 H–237
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 532.4721 0.0000 532.4721 1150.1263 0.4630 0.2386 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1098 558.0767 512.2610 0.0000 0.0600 0.0373 0.1137

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8820 9.3757 1.1789 580.8552 29.0611 235.7274 1.8273

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180863.656 0.456 644.442 579871.750 0.913763E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 7.321 EfDer = 0.999 SH = 0.913763E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.052 3644.566 9.376 580.855 1.000 1.000 0.980

 W Kg/sec = 28.660 Wdry = 63.046 WH2O = 0.006 lbm/sec H2O = 0.060g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.614 3444.055 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 93107.930 49472.098 1.676 513.330 306.271 395.845 1.292

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 435.31 -0.15 435.31 0.38 0.65 578.84

 MEAN 16.97 0.00 -0.02 435.31 -0.15 435.31 0.38 0.60

 HUB 14.32 0.00 -0.02 435.31 -0.15 435.31 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.61 46.36 8.25 612.56 751.61 8.51 565.63 512.23 0.11

 MEAN 51.12 43.80 7.32 539.75 693.53 8.51 565.63 512.23 0.11

 HUB 46.30 37.84 8.46 455.45 630.13 8.51 565.63 512.23 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 524.85 288.92 438.18 1179.14 0.45 2.16 1.89 8.34

 MEAN 16.57 534.25 296.07 444.71 1175.52 0.45 2.24 1.97 6.35

 HUB 13.89 576.71 358.54 451.71 1172.07 0.49 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 600.48 537.65 311.56 0.46 5457.61 0.92 0.91

 MEAN 527.13 501.15 231.06 0.43 4909.62 0.92 0.91 0.91 1.51

 HUB 441.77 459.31 83.22 0.39 4982.34 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.96 1.17 9.58 608.74 1.05 586.61 522.68 0.07

 MEAN 10.79 1.15 9.38 605.94 1.04 583.01 521.68 0.07

 HUB 10.81 1.15 9.18 606.31 1.04 579.60 521.82 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.40 35.41 31.50 3.91 0.93 0.42 1.40

 MEAN 33.65 27.46 23.50 3.96 0.93 0.41 1.62

 HUB 38.44 10.44 6.50 3.94 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 574.9388 297.7378 491.8403 1172.8788 0.4902 -0.1129 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.8379 9.2151 580.4518 522.0426 0.0783 31.1888 32.4000 1.2112

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 486.9586 109.2106 474.5543 1180.4318 0.4125 0.1775 2.2705

 

NASA/TM—2013-218094 H–238
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.8239 9.6421 587.9552 521.9874 432.2457 0.0195 0.3467

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 482.9695 0.0000 482.9695 1180.7137 0.4090 0.2603 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6375 588.2683 521.9338 0.0000 0.0600 0.0371 0.1743

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 10.7980 1.1517 606.9988 26.1444 239.3172 1.8552

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 162788.813 0.451 580.039 575404.375 0.914949E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.480 EfDer = 0.999 SH = 0.914994E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.052 3644.566 10.798 606.999 1.000 1.000 0.980

 W Kg/sec = 28.660 Wdry = 63.046 WH2O = 0.006 lbm/sec H2O = 0.067g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 92.856 3369.070 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 83149.617 49472.098 1.875 509.668 271.867 384.739 1.415

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 391.55 -0.13 391.55 0.33 0.59 538.60

 MEAN 15.91 0.00 -0.02 391.55 -0.13 391.55 0.33 0.54

 HUB 13.07 0.00 -0.02 391.55 -0.13 391.55 0.33 0.48

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.11 47.36 8.75 582.66 702.11 10.02 594.69 521.91 0.06

 MEAN 52.28 44.80 7.48 506.11 639.99 10.02 594.69 521.91 0.06

 HUB 46.72 38.84 7.88 415.69 571.16 10.02 594.69 521.91 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 489.86 286.46 397.37 1206.22 0.41 2.05 1.78 7.43

 MEAN 15.50 492.66 282.37 403.72 1202.17 0.41 2.13 1.86 5.75

 HUB 12.59 523.58 325.10 410.42 1198.25 0.44 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 570.58 488.50 284.12 0.40 5141.50 0.92 0.91

 MEAN 492.90 455.31 210.53 0.38 4378.16 0.92 0.91 0.91 1.55

 HUB 400.42 417.27 75.32 0.35 4094.80 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 12.43 1.15 11.11 633.26 1.04 613.99 531.11 0.04

 MEAN 12.18 1.13 10.86 629.36 1.04 609.87 529.78 0.04

 HUB 12.08 1.12 10.62 627.91 1.03 605.90 529.29 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.79 35.56 31.50 4.06 0.93 0.45 1.40

 MEAN 34.97 27.54 23.50 4.04 0.93 0.42 1.64

 HUB 38.38 10.40 6.50 3.90 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 546.0810 287.5448 464.2439 1198.5284 0.4556 -0.1907 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 12.2029 10.6032 606.2384 530.0228 0.0457 31.7734 33.0000 1.2266

 

NASA/TM—2013-218094 H–239
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 469.2271 107.1484 456.8296 1204.7028 0.3895 0.0893 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 12.1808 10.9861 612.5018 529.9637 410.5396 0.0362 0.3573

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 454.9614 0.0000 454.9614 1205.7126 0.3773 0.2819 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 11.0541 613.5621 529.9587 0.0000 0.0600 0.0371 0.1391

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8834 12.1796 1.1279 630.1747 23.1767 247.4486 1.9182

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 144386.109 0.444 514.467 586740.375 0.916205E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3067 Tt4 = 630.1747 T1 = 482.2737

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 920446.69 3279.6777 172.9624 2.3571 0.8699 5.9857 1.3067 37.3740

NASA/TM—2013-218094 H–240
Appendix I: NPSS cycle analysis for the altitude cruise conditions at 39000 feet

 5μm, ISA +18R

************************************************************************************************************************************ 

Date:05/10/13 Time:11:00:06 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 26/ 54/ 2/23 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 444.75 Stator 1 exit: 463.49 Stator 2 inlet: 485.28 Stator 2 exit: 492.72 

 Stator 3 inlet: 521.55 Stator 3 exit: 529.73 Stator 4 inlet: 556.62 Stator 4 exit: 564.45 

 Stator 5 inlet: 585.25 Stator 5 exit: 592.90 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.21 

Fan Bypass Relative Humidity 0.15 

LPC Inlet Relative Humidity 2.28 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 483.11 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 438.28 

Additional Water at LPC Exit 0.0029812 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 396.12 6805.8 0.5961 4057.03 5.3007 772.64 32.312 1.705 100.000 2814.3 2641.6 1836.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 396.12 4.267 457.74 -20.96 0.0000 1281.69 2.854 407.97 3910.0 0.7800 1.40084 0.0000295 396.11 0.012 0.0000

FS1 Inlet.Fl_O 396.12 4.267 457.74 -20.96 0.0000 1281.69 3.152 419.74 4168.2 0.6720 1.40084 0.0000295 396.11 0.012 0.0000

FS12 Splitter.Fl_02 333.25 4.265 457.74 -20.96 0.0000 1078.81 3.174 420.64 3531.8 0.6633 1.40084 0.0000295 333.24 0.010 0.0000

FS2 Splitter.Fl_01 62.87 4.265 457.74 -20.96 0.0000 203.52 3.664 438.28 830.5 0.4706 1.40084 0.0000295 62.87 0.002 0.0000

FS14 Fan.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS23 LPC.Fl_O 62.87 10.583 621.71 18.40 0.0000 95.58 9.281 598.87 412.6 0.4374 1.39828 0.0000295 62.87 0.002 0.0000

FS24 VaporIN.Fl_O 63.06 10.583 625.30 2.18 0.0000 96.14 9.260 601.96 412.6 0.4413 1.39776 0.0030106 62.87 0.189 0.0030

FS25 Bleed2.Fl_O 63.06 10.583 625.30 2.18 0.0000 96.14 9.260 601.96 412.6 0.4413 1.39776 0.0030106 62.87 0.189 0.0030

FS3 HPC.Fl_O 60.00 137.870 1377.26 190.17 0.0000 10.42 124.294 1340.14 49.7 0.3933 1.35677 0.0030106 59.82 0.180 0.0030

FS36 Bleed3.Fl_O 46.50 137.870 1377.26 190.17 0.0000 8.08 129.984 1356.06 49.3 0.2957 1.35677 0.0030106 46.36 0.140 0.0030

FS4 Burner.Fl_O 47.62 134.694 2814.25 160.34 0.0243 12.10 127.230 2778.51 74.6 0.3007 1.28425 0.0030106 46.36 0.140 0.0321

FS45 HPT.Fl_O 63.45 31.488 1845.31 -17.97 0.0181 55.85 28.359 1798.88 265.4 0.4006 1.32062 0.0030106 62.13 0.187 0.0249

FS49 LPT.Fl_O 64.18 7.245 1322.51 -157.86 0.0179 207.90 6.249 1272.87 860.2 0.4723 1.34775 0.0030106 62.87 0.189 0.0246

FS5 TEGV.Fl_O 64.18 7.245 1322.57 -157.86 0.0179 207.91 6.249 1272.93 860.2 0.4723 1.34775 0.0030106 62.87 0.189 0.0246

FS8 Core_Nozz.Fl_O 64.18 7.245 1322.70 -157.86 0.0179 207.92 3.875 1123.01 613.4 1.0000 1.34774 0.0030106 62.87 0.189 0.0246

FS17 FanDuctLkg.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS171 Bleed15.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS172 FanDuct.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS173 Byp_Nozz.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 3.833 450.06 2006.9 1.0000 1.39992 0.0000295 333.24 0.010 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.81 1.702 0.9114 4139.469 1.1801 0.9178 -9322.3 36.69 23.09

LPC 203.52 2.482 0.8276 4139.469 1.3582 0.8480 -3501.0 2.97 2.24

HPC 96.14 13.027 0.8586 10339.379 2.2026 0.8979 -16365.1 26.38 25.58

HPT 12.10 4.278 0.9118 213.999 1.3463 0.8912 16364.9 

LPT 55.85 4.346 0.9155 90.526 1.3918 0.8989 12823.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.47 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2198 0.8477 0.9922 0.0003

HPC 87.44 12.460 0.8675 10063.738 13.4623 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.187 0.9118 1.286 4.1868 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.517 0.9223 1.018 3.5170 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–1
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3910.00 9512.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3205 1009.15 96.17 31.488

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7378 1009.15 96.17 7.245

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.41 86.77 38.586

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1202.68 145.05 89.501

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.41 86.77 38.586

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1377.26 190.17 137.870

Splitter 5.3007 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.41 86.77 38.586

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11352.5 7571.0 16364.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 625.30 2.18 10.583

LP_Shaft 3888.7 17319.1 12823.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.1997 1377.26 190.17 134.694

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.2999 1377.26 190.17 75.660

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1377.26 190.17 137.870

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1377.26 190.17 137.870

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1377.26 190.17 137.870

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2814.25 0.9995 0.0230 1.12695 0.02431 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.538 0.9809 1.0000 0.9800 613.40 1.000 1588.3 3794.4

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1019.5 12523.9

NASA/TM—2013-218094 I–2
************************************************************************************************************************************ 

Date:05/10/13 Time:11:00:41 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 450.83 Stator 1 exit: 468.07 Stator 2 inlet: 488.64 Stator 2 exit: 496.76 

 Stator 3 inlet: 522.20 Stator 3 exit: 530.54 Stator 4 inlet: 554.47 Stator 4 exit: 562.16 

 Stator 5 inlet: 581.05 Stator 5 exit: 588.40 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.13 

Fan Bypass Relative Humidity 0.18 

LPC Inlet Relative Humidity 1.99 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 443.02 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.76 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 441.38 

Additional Water at LPC Exit 0.0032403 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 378.64 5820.2 0.5893 3429.77 5.4535 772.64 29.224 1.498 84.000 2651.2 2490.8 1726.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 378.64 4.267 457.74 -20.96 0.0000 1225.14 2.854 407.97 3737.5 0.7800 1.40084 0.0000295 378.63 0.011 0.0000

FS1 Inlet.Fl_O 378.64 4.267 457.74 -20.96 0.0000 1225.14 3.297 425.18 4168.2 0.6181 1.40084 0.0000295 378.63 0.011 0.0000

FS12 Splitter.Fl_02 319.97 4.265 457.74 -20.96 0.0000 1035.82 3.302 425.40 3531.8 0.6157 1.40084 0.0000295 319.96 0.009 0.0000

FS2 Splitter.Fl_01 58.67 4.265 457.74 -20.96 0.0000 189.94 3.755 441.38 830.5 0.4300 1.40084 0.0000295 58.67 0.002 0.0000

FS14 Fan.Fl_O 319.97 6.916 532.19 -3.11 0.0000 688.70 5.741 504.60 2606.7 0.5226 1.40004 0.0000295 319.96 0.009 0.0000

FS23 LPC.Fl_O 58.67 10.432 613.70 16.48 0.0000 89.91 9.319 594.27 412.6 0.4050 1.39848 0.0000295 58.67 0.002 0.0000

FS24 VaporIN.Fl_O 58.86 10.432 617.64 -1.15 0.0000 90.49 9.299 597.75 412.6 0.4088 1.39792 0.0032697 58.67 0.192 0.0033

FS25 Bleed2.Fl_O 58.86 10.432 617.64 -1.15 0.0000 90.49 9.299 597.75 412.6 0.4088 1.39792 0.0032697 58.67 0.192 0.0033

FS3 HPC.Fl_O 56.01 124.692 1326.74 175.57 0.0000 10.56 112.046 1289.65 49.7 0.3991 1.35972 0.0032697 55.82 0.183 0.0033

FS36 Bleed3.Fl_O 43.41 124.692 1326.74 175.57 0.0000 8.18 117.358 1305.60 49.3 0.2997 1.35972 0.0032697 43.26 0.141 0.0033

FS4 Burner.Fl_O 44.36 121.820 2651.21 148.93 0.0220 12.10 115.055 2617.01 74.6 0.2999 1.29033 0.0032697 43.26 0.141 0.0297

FS45 HPT.Fl_O 59.13 28.385 1734.99 -19.33 0.0164 55.99 25.546 1690.44 265.4 0.4009 1.32659 0.0032697 57.98 0.190 0.0231

FS49 LPT.Fl_O 59.81 6.525 1239.14 -150.29 0.0162 208.21 5.626 1191.87 860.2 0.4721 1.35402 0.0032697 58.67 0.192 0.0229

FS5 TEGV.Fl_O 59.81 6.525 1239.20 -150.29 0.0162 208.22 5.626 1191.93 860.2 0.4721 1.35402 0.0032697 58.67 0.192 0.0229

FS8 Core_Nozz.Fl_O 59.81 6.525 1239.33 -150.29 0.0162 208.23 3.483 1049.52 613.4 1.0000 1.35401 0.0032697 58.67 0.192 0.0229

FS17 FanDuctLkg.Fl_O 319.97 6.916 532.19 -3.11 0.0000 688.70 5.741 504.60 2606.7 0.5226 1.40004 0.0000295 319.96 0.009 0.0000

FS171 Bleed15.Fl_O 319.97 6.916 532.19 -3.11 0.0000 688.70 5.579 500.49 2481.9 0.5625 1.40004 0.0000295 319.96 0.009 0.0000

FS172 FanDuct.Fl_O 319.97 6.916 532.19 -3.11 0.0000 688.70 5.579 500.49 2481.9 0.5625 1.40004 0.0000295 319.96 0.009 0.0000

FS173 Byp_Nozz.Fl_O 319.97 6.916 532.19 -3.11 0.0000 688.70 3.652 443.37 2006.9 1.0000 1.40004 0.0000295 319.96 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1035.82 1.622 0.9117 3971.018 1.1626 0.9175 -8080.2 52.83 26.41

LPC 189.94 2.446 0.8546 3971.018 1.3407 0.8716 -3107.3 2.94 2.13

HPC 90.49 11.953 0.8609 10162.222 2.1481 0.8986 -14361.1 30.35 29.29

HPT 12.10 4.292 0.9099 215.372 1.3525 0.8903 14361.2 

LPT 55.99 4.350 0.9132 89.561 1.3971 0.8963 11187.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1203.52 1.607 0.9136 3933.155 0.0612 0.8607 1.0235 0.9980 0.9905

LPC 151.42 2.562 0.8233 1.049 0.0000 1.2544 0.9255 1.0380 0.0003

HPC 82.30 11.437 0.8698 9891.304 13.1020 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.200 0.9098 1.294 4.2005 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9200 1.007 3.5195 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–3
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3737.52 9092.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1661 979.04 87.21 28.385

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6887 979.04 87.21 6.525

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 943.45 78.37 35.569

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1161.72 133.16 81.273

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 943.45 78.37 35.569

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1326.74 175.57 124.692

Splitter 5.4535 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 943.45 78.37 35.569

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11089.5 6801.6 14361.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 617.64 -1.15 10.432

LP_Shaft 3730.5 15750.6 11187.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.7209 1326.74 175.57 121.820

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.8809 1326.74 175.57 68.375

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1326.74 175.57 124.692

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1326.74 175.57 124.692

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1326.74 175.57 124.692

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 532.19 -3.11 6.916

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 532.19 -3.11 6.916

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 532.19 -3.11 6.916

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 532.19 -3.11 6.916

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2651.19 0.9995 0.0230 0.95271 0.02202 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.286 0.9816 1.0000 0.9800 613.40 1.000 1538.9 3247.1 

Byp_Nozz 2.423 0.9814 1.0000 0.9800 2006.86 1.000 1011.9 11666.0

NASA/TM—2013-218094 I–4
************************************************************************************************************************************ 

Date:05/10/13 Time:11:01:31 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 47/ 2/16 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 452.44 Stator 1 exit: 469.27 Stator 2 inlet: 489.52 Stator 2 exit: 497.76 

 Stator 3 inlet: 522.38 Stator 3 exit: 530.72 Stator 4 inlet: 553.90 Stator 4 exit: 561.54 

 Stator 5 inlet: 579.94 Stator 5 exit: 587.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.89 

Fan Bypass Relative Humidity 0.20 

LPC Inlet Relative Humidity 1.91 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 430.69 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.78 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.28 

Additional Water at LPC Exit 0.0033318 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 373.35 5530.6 0.5885 3254.66 5.5124 772.64 28.295 1.439 79.800 2605.0 2448.0 1696.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 373.35 4.267 457.74 -20.96 0.0000 1208.02 2.854 407.97 3685.3 0.7800 1.40084 0.0000295 373.34 0.011 0.0000

FS1 Inlet.Fl_O 373.35 4.267 457.74 -20.96 0.0000 1208.02 3.336 426.61 4168.2 0.6033 1.40084 0.0000295 373.34 0.011 0.0000

FS12 Splitter.Fl_02 316.02 4.265 457.74 -20.96 0.0000 1023.04 3.336 426.66 3531.8 0.6028 1.40084 0.0000295 316.01 0.009 0.0000

FS2 Splitter.Fl_01 57.33 4.265 457.74 -20.96 0.0000 185.59 3.782 442.28 830.5 0.4176 1.40084 0.0000295 57.33 0.002 0.0000

FS14 Fan.Fl_O 316.02 6.815 529.79 -3.68 0.0000 688.70 5.657 502.33 2606.7 0.5226 1.40007 0.0000295 316.01 0.009 0.0000

FS23 LPC.Fl_O 57.33 10.371 611.54 15.96 0.0000 88.21 9.311 593.03 412.6 0.3956 1.39853 0.0000295 57.33 0.002 0.0000

FS24 VaporIN.Fl_O 57.52 10.371 615.61 -2.17 0.0000 88.80 9.292 596.65 412.6 0.3994 1.39796 0.0033613 57.33 0.193 0.0034

FS25 Bleed2.Fl_O 57.52 10.371 615.61 -2.17 0.0000 88.80 9.292 596.65 412.6 0.3994 1.39796 0.0033613 57.33 0.193 0.0034

FS3 HPC.Fl_O 54.73 120.730 1312.35 171.33 0.0000 10.60 108.380 1275.28 49.7 0.4008 1.36058 0.0033613 54.55 0.183 0.0034

FS36 Bleed3.Fl_O 42.42 120.730 1312.35 171.33 0.0000 8.21 113.572 1291.25 49.3 0.3008 1.36058 0.0033613 42.27 0.142 0.0034

FS4 Burner.Fl_O 43.32 117.950 2604.98 145.56 0.0214 12.10 111.399 2571.22 74.6 0.2996 1.29207 0.0033613 42.27 0.142 0.0290

FS45 HPT.Fl_O 57.75 27.458 1704.05 -19.80 0.0160 56.02 24.708 1660.07 265.4 0.4009 1.32834 0.0033613 56.66 0.190 0.0226

FS49 LPT.Fl_O 58.42 6.311 1215.93 -148.25 0.0158 208.29 5.441 1169.35 860.2 0.4720 1.35578 0.0033613 57.33 0.193 0.0224

FS5 TEGV.Fl_O 58.42 6.311 1215.99 -148.25 0.0158 208.30 5.441 1169.41 860.2 0.4720 1.35577 0.0033613 57.33 0.193 0.0224

FS8 Core_Nozz.Fl_O 58.42 6.311 1216.12 -148.25 0.0158 208.31 3.367 1029.14 613.4 1.0000 1.35576 0.0033613 57.33 0.193 0.0224

FS17 FanDuctLkg.Fl_O 316.02 6.815 529.79 -3.68 0.0000 688.70 5.657 502.33 2606.7 0.5226 1.40007 0.0000295 316.01 0.009 0.0000

FS171 Bleed15.Fl_O 316.02 6.815 529.79 -3.68 0.0000 688.70 5.498 498.23 2481.9 0.5625 1.40007 0.0000295 316.01 0.009 0.0000

FS172 FanDuct.Fl_O 316.02 6.815 529.79 -3.68 0.0000 688.70 5.498 498.23 2481.9 0.5625 1.40007 0.0000295 316.01 0.009 0.0000

FS173 Byp_Nozz.Fl_O 316.02 6.815 529.79 -3.68 0.0000 688.70 3.599 441.37 2006.9 1.0000 1.40007 0.0000295 316.01 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1023.04 1.598 0.9114 3923.364 1.1574 0.9171 -7723.8 56.99 27.45

LPC 185.59 2.432 0.8601 3923.364 1.3360 0.8764 -2994.1 3.32 2.60

HPC 88.80 11.642 0.8614 10115.453 2.1318 0.8987 -13777.4 31.59 30.43

HPT 12.10 4.296 0.9090 215.918 1.3541 0.8897 13777.4 

LPT 56.02 4.351 0.9125 89.286 1.3985 0.8954 10717.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1188.67 1.584 0.9133 3885.955 0.0604 0.8607 1.0235 0.9980 0.9905

LPC 148.34 2.513 0.8224 1.036 0.0000 1.2511 0.9460 1.0459 0.0003

HPC 80.76 11.140 0.8703 9845.782 12.9962 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.204 0.9090 1.298 4.2043 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9192 1.004 3.5201 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–5
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3685.27 8965.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1167 970.55 84.58 27.458

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6730 970.55 84.58 6.311

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 935.58 75.91 34.650

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1150.11 129.69 78.793

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 935.58 75.91 34.650

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1312.35 171.33 120.730

Splitter 5.5124 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 935.58 75.91 34.650

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11020.3 6566.1 13777.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 615.61 -2.17 10.371

LP_Shaft 3685.7 15272.9 10717.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.5676 1312.35 171.33 117.950

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7468 1312.35 171.33 66.189

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1312.35 171.33 120.730

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1312.35 171.33 120.730

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1312.35 171.33 120.730

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.79 -3.68 6.815

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.79 -3.68 6.815

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.79 -3.68 6.815

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.79 -3.68 6.815

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2604.96 0.9995 0.0230 0.90407 0.02139 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.211 0.9816 1.0000 0.9800 613.40 1.000 1524.8 3083.8

Byp_Nozz 2.388 0.9815 1.0000 0.9800 2006.86 1.000 1009.6 11412.6

NASA/TM—2013-218094 I–6
************************************************************************************************************************************ 

Date:05/10/13 Time:11:02:07 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 453.52 Stator 1 exit: 470.08 Stator 2 inlet: 490.14 Stator 2 exit: 498.45 

 Stator 3 inlet: 522.55 Stator 3 exit: 530.89 Stator 4 inlet: 553.58 Stator 4 exit: 561.19 

 Stator 5 inlet: 579.25 Stator 5 exit: 586.48 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.73 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 1.86 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 421.98 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.80 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.90 

Additional Water at LPC Exit 0.0034016 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 369.47 5325.2 0.5888 3135.61 5.5548 772.64 27.645 1.398 76.800 2573.5 2418.9 1675.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 369.47 4.267 457.74 -20.96 0.0000 1195.45 2.854 407.97 3646.9 0.7800 1.40084 0.0000295 369.45 0.011 0.0000

FS1 Inlet.Fl_O 369.47 4.267 457.74 -20.96 0.0000 1195.45 3.363 427.60 4168.2 0.5929 1.40084 0.0000295 369.45 0.011 0.0000

FS12 Splitter.Fl_02 313.10 4.265 457.74 -20.96 0.0000 1013.58 3.360 427.54 3531.8 0.5935 1.40084 0.0000295 313.09 0.009 0.0000

FS2 Splitter.Fl_01 56.37 4.265 457.74 -20.96 0.0000 182.47 3.801 442.90 830.5 0.4089 1.40084 0.0000295 56.36 0.002 0.0000

FS14 Fan.Fl_O 313.10 6.742 528.16 -4.07 0.0000 688.70 5.596 500.78 2606.7 0.5226 1.40010 0.0000295 313.09 0.009 0.0000

FS23 LPC.Fl_O 56.37 10.328 610.15 15.62 0.0000 86.99 9.305 592.29 412.6 0.3889 1.39857 0.0000295 56.36 0.002 0.0000

FS24 VaporIN.Fl_O 56.56 10.328 614.31 -2.88 0.0000 87.58 9.287 596.01 412.6 0.3927 1.39798 0.0034311 56.36 0.193 0.0034

FS25 Bleed2.Fl_O 56.56 10.328 614.31 -2.88 0.0000 87.58 9.287 596.01 412.6 0.3927 1.39798 0.0034311 56.36 0.193 0.0034

FS3 HPC.Fl_O 53.81 117.957 1302.62 168.42 0.0000 10.63 105.818 1265.54 49.7 0.4020 1.36116 0.0034311 53.63 0.184 0.0034

FS36 Bleed3.Fl_O 41.71 117.957 1302.62 168.42 0.0000 8.23 110.924 1281.52 49.3 0.3017 1.36116 0.0034311 41.56 0.143 0.0034

FS4 Burner.Fl_O 42.58 115.240 2573.46 143.23 0.0210 12.09 108.838 2540.01 74.6 0.2994 1.29327 0.0034311 41.56 0.143 0.0286

FS45 HPT.Fl_O 56.77 26.812 1683.06 -20.14 0.0156 56.05 24.124 1639.45 265.4 0.4009 1.32954 0.0034311 55.70 0.191 0.0223

FS49 LPT.Fl_O 57.43 6.162 1200.21 -146.90 0.0155 208.35 5.312 1154.09 860.2 0.4719 1.35697 0.0034311 56.36 0.193 0.0221

FS5 TEGV.Fl_O 57.43 6.162 1200.27 -146.90 0.0155 208.36 5.312 1154.15 860.2 0.4719 1.35697 0.0034311 56.36 0.193 0.0221

FS8 Core_Nozz.Fl_O 57.43 6.162 1200.40 -146.90 0.0155 208.37 3.287 1015.35 613.4 1.0000 1.35696 0.0034311 56.36 0.193 0.0221

FS17 FanDuctLkg.Fl_O 313.10 6.742 528.16 -4.07 0.0000 688.70 5.596 500.78 2606.7 0.5226 1.40010 0.0000295 313.09 0.009 0.0000

FS171 Bleed15.Fl_O 313.10 6.742 528.16 -4.07 0.0000 688.70 5.438 496.69 2481.9 0.5625 1.40010 0.0000295 313.09 0.009 0.0000

FS172 FanDuct.Fl_O 313.10 6.742 528.16 -4.07 0.0000 688.70 5.438 496.69 2481.9 0.5625 1.40010 0.0000295 313.09 0.009 0.0000

FS173 Byp_Nozz.Fl_O 313.10 6.742 528.16 -4.07 0.0000 688.70 3.560 440.00 2006.9 1.0000 1.40010 0.0000295 313.09 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1013.58 1.581 0.9096 3891.073 1.1538 0.9153 -7478.6 59.09 28.22

LPC 182.47 2.422 0.8634 3891.073 1.3330 0.8792 -2917.1 3.59 2.85

HPC 87.58 11.421 0.8614 10082.571 2.1204 0.8985 -13375.1 32.47 31.24

HPT 12.09 4.298 0.9085 216.303 1.3552 0.8892 13375.1 

LPT 56.05 4.351 0.9119 89.101 1.3995 0.8948 10395.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1177.68 1.568 0.9115 3853.972 0.0598 0.8607 1.0235 0.9980 0.9905

LPC 146.25 2.480 0.8217 1.028 0.0000 1.2477 0.9605 1.0507 0.0003

HPC 79.66 10.930 0.8703 9813.777 12.9219 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.207 0.9085 1.300 4.2067 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9187 1.002 3.5206 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–7
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3646.93 8872.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0813 964.85 82.77 26.812

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6617 964.85 82.77 6.162

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 930.30 74.21 34.006

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1142.26 127.31 77.058

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 930.30 74.21 34.006

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1302.62 168.42 117.957

Splitter 5.5548 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 930.30 74.21 34.006

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10972.9 6401.9 13375.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 614.31 -2.88 10.328

LP_Shaft 3655.4 14936.8 10395.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4577 1302.62 168.42 115.240

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6506 1302.62 168.42 64.659

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1302.62 168.42 117.957

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1302.62 168.42 117.957

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1302.62 168.42 117.957

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 528.16 -4.07 6.742

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 528.16 -4.07 6.742

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 528.16 -4.07 6.742

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 528.16 -4.07 6.742

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2573.44 0.9995 0.0230 0.87100 0.02096 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.159 0.9815 1.0000 0.9800 613.40 1.000 1515.2 2969.8

Byp_Nozz 2.362 0.9815 1.0000 0.9800 2006.86 1.000 1008.1 11227.9

NASA/TM—2013-218094 I–8
 5μm, ISA +36R

************************************************************************************************************************************ 

Date:05/10/13 Time:11:38:06 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 38/ 1/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 465.07 Stator 1 exit: 484.73 Stator 2 inlet: 507.72 Stator 2 exit: 515.80 

 Stator 3 inlet: 545.76 Stator 3 exit: 554.54 Stator 4 inlet: 582.42 Stator 4 exit: 590.81 

 Stator 5 inlet: 612.50 Stator 5 exit: 620.61 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.44 

Fan Bypass Relative Humidity 0.19 

LPC Inlet Relative Humidity 2.49 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 491.33 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.67 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 457.80 

Additional Water at LPC Exit 0.0055918 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 387.42 6824.0 0.6109 4168.86 5.3204 789.49 32.228 1.708 100.000 2921.7 2743.6 1914.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.42 4.267 477.92 -16.44 0.0000 1280.92 2.854 425.97 3907.8 0.7800 1.40068 0.0000851 387.39 0.033 0.0001

FS1 Inlet.Fl_O 387.42 4.267 477.92 -16.44 0.0000 1280.92 3.154 438.33 4168.2 0.6713 1.40068 0.0000851 387.39 0.033 0.0001

FS12 Splitter.Fl_02 326.13 4.265 477.92 -16.44 0.0000 1078.79 3.174 439.19 3531.8 0.6634 1.40068 0.0000851 326.10 0.028 0.0001

FS2 Splitter.Fl_01 61.30 4.265 477.92 -16.44 0.0000 202.77 3.669 457.80 830.5 0.4683 1.40068 0.0000851 61.29 0.005 0.0001

FS14 Fan.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS23 LPC.Fl_O 61.30 10.700 650.42 25.00 0.0000 94.28 9.425 627.35 412.6 0.4299 1.39749 0.0000851 61.29 0.005 0.0001

FS24 VaporIN.Fl_O 61.64 10.700 656.78 -5.40 0.0000 95.27 9.388 632.82 412.6 0.4368 1.39650 0.0056769 61.29 0.348 0.0056

FS25 Bleed2.Fl_O 61.64 10.700 656.78 -5.40 0.0000 95.27 9.388 632.82 412.6 0.4368 1.39650 0.0056769 61.29 0.348 0.0056

FS3 HPC.Fl_O 58.65 137.506 1434.67 190.50 0.0000 10.43 123.924 1396.17 49.7 0.3944 1.35306 0.0056769 58.32 0.331 0.0056

FS36 Bleed3.Fl_O 45.45 137.506 1434.67 190.50 0.0000 8.08 129.620 1412.70 49.3 0.2965 1.35306 0.0056769 45.20 0.257 0.0056

FS4 Burner.Fl_O 46.61 134.340 2921.68 159.09 0.0256 12.10 126.902 2884.92 74.6 0.3014 1.27995 0.0056769 45.20 0.257 0.0361

FS45 HPT.Fl_O 62.08 31.473 1923.93 -26.47 0.0191 55.83 28.343 1875.95 265.4 0.4014 1.31633 0.0056769 60.58 0.344 0.0285

FS49 LPT.Fl_O 62.80 7.264 1383.50 -172.77 0.0189 207.51 6.268 1332.19 860.2 0.4726 1.34312 0.0056769 61.29 0.348 0.0283

FS5 TEGV.Fl_O 62.80 7.264 1383.57 -172.77 0.0189 207.51 6.268 1332.26 860.2 0.4726 1.34312 0.0056769 61.29 0.348 0.0283

FS8 Core_Nozz.Fl_O 62.80 7.264 1383.69 -172.77 0.0189 207.52 3.890 1177.08 613.4 1.0000 1.34311 0.0056769 61.29 0.348 0.0283

FS17 FanDuctLkg.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS171 Bleed15.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS172 FanDuct.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS173 Byp_Nozz.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 3.833 469.91 2006.9 1.0000 1.39952 0.0000851 326.10 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.79 1.702 0.9114 4139.469 1.1801 0.9178 -9525.9 36.68 23.09

LPC 202.77 2.509 0.8319 4139.469 1.3609 0.8520 -3594.1 2.97 2.24

HPC 95.27 12.851 0.8589 10303.595 2.1844 0.8977 -16671.2 27.03 26.21

HPT 12.10 4.268 0.9122 214.505 1.3415 0.8904 16671.1 

LPT 55.83 4.333 0.9168 90.590 1.3872 0.9007 13120.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.45 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2153 0.8633 0.9974 0.0003

HPC 86.64 12.293 0.8678 10028.908 13.3993 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.178 0.9121 1.289 4.1778 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.507 0.9236 1.019 3.5068 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–9
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3907.84 9506.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.2684 1054.43 92.55 31.473

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7212 1054.43 92.55 7.264

TEGV 0.0000 0.4726 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1015.39 82.75 38.597

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1254.40 143.48 89.320

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1015.39 82.75 38.597

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1434.67 190.50 137.506

Splitter 5.3204 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1015.39 82.75 38.597

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11594.5 7551.7 16671.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 656.78 -5.40 10.700

LP_Shaft 3973.5 17341.9 13120.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.0381 1434.67 190.50 134.340

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.1585 1434.67 190.50 75.500

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1434.67 190.50 137.506

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1434.67 190.50 137.506

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1434.67 190.50 137.506

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2921.68 0.9995 0.0230 1.15802 0.02562 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.545 0.9809 1.0000 0.9800 613.40 1.000 1624.7 3806.9

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1041.7 12523.7

NASA/TM—2013-218094 I–10
************************************************************************************************************************************ 

Date:05/10/13 Time:11:38:42 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 470.84 Stator 1 exit: 489.03 Stator 2 inlet: 510.79 Stator 2 exit: 519.44 

 Stator 3 inlet: 546.19 Stator 3 exit: 555.04 Stator 4 inlet: 580.14 Stator 4 exit: 588.35 

 Stator 5 inlet: 608.21 Stator 5 exit: 616.00 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.46 

Fan Bypass Relative Humidity 0.23 

LPC Inlet Relative Humidity 2.21 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 453.72 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.75 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 460.77 

Additional Water at LPC Exit 0.0060986 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 371.95 5928.8 0.6037 3578.97 5.4660 789.49 29.417 1.518 84.000 2770.0 2603.3 1812.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 371.95 4.267 477.92 -16.44 0.0000 1229.75 2.854 425.97 3751.7 0.7800 1.40068 0.0000851 371.92 0.032 0.0001

FS1 Inlet.Fl_O 371.95 4.267 477.92 -16.44 0.0000 1229.75 3.286 443.51 4168.2 0.6222 1.40068 0.0000851 371.92 0.032 0.0001

FS12 Splitter.Fl_02 314.42 4.265 477.92 -16.44 0.0000 1040.08 3.290 443.71 3531.8 0.6202 1.40068 0.0000851 314.40 0.027 0.0001

FS2 Splitter.Fl_01 57.52 4.265 477.92 -16.44 0.0000 190.28 3.753 460.77 830.5 0.4310 1.40068 0.0000851 57.52 0.005 0.0001

FS14 Fan.Fl_O 314.42 6.950 556.40 2.39 0.0000 688.65 5.769 527.58 2606.7 0.5226 1.39965 0.0000851 314.40 0.027 0.0001

FS23 LPC.Fl_O 57.52 10.537 642.64 23.13 0.0000 89.30 9.430 622.64 412.6 0.4017 1.39771 0.0000851 57.52 0.005 0.0001

FS24 VaporIN.Fl_O 57.87 10.537 649.67 -10.01 0.0000 90.34 9.395 628.83 412.6 0.4086 1.39665 0.0061837 57.52 0.356 0.0061

FS25 Bleed2.Fl_O 57.87 10.537 649.67 -10.01 0.0000 90.34 9.395 628.83 412.6 0.4086 1.39665 0.0061837 57.52 0.356 0.0061

FS3 HPC.Fl_O 55.07 125.513 1388.23 175.50 0.0000 10.55 112.778 1349.71 49.7 0.3998 1.35562 0.0061837 54.73 0.338 0.0061

FS36 Bleed3.Fl_O 42.68 125.513 1388.23 175.50 0.0000 8.18 118.129 1366.30 49.3 0.3002 1.35562 0.0061837 42.41 0.262 0.0061

FS4 Burner.Fl_O 43.67 122.622 2769.97 147.19 0.0234 12.10 115.818 2734.61 74.6 0.3006 1.28550 0.0061837 42.41 0.262 0.0341

FS45 HPT.Fl_O 58.19 28.636 1820.51 -29.16 0.0175 55.95 25.773 1774.29 265.4 0.4017 1.32165 0.0061837 56.85 0.352 0.0271

FS49 LPT.Fl_O 58.87 6.605 1305.16 -167.09 0.0173 207.77 5.697 1256.03 860.2 0.4723 1.34882 0.0061837 57.52 0.356 0.0269

FS5 TEGV.Fl_O 58.87 6.605 1305.22 -167.09 0.0173 207.77 5.697 1256.09 860.2 0.4723 1.34882 0.0061837 57.52 0.356 0.0269

FS8 Core_Nozz.Fl_O 58.87 6.605 1305.35 -167.09 0.0173 207.78 3.531 1107.79 613.4 1.0000 1.34881 0.0061837 57.52 0.356 0.0269

FS17 FanDuctLkg.Fl_O 314.42 6.950 556.40 2.39 0.0000 688.65 5.769 527.58 2606.7 0.5226 1.39965 0.0000851 314.40 0.027 0.0001

FS171 Bleed15.Fl_O 314.42 6.950 556.40 2.39 0.0000 688.65 5.606 523.28 2481.9 0.5626 1.39965 0.0000851 314.40 0.027 0.0001

FS172 FanDuct.Fl_O 314.42 6.950 556.40 2.39 0.0000 688.65 5.606 523.28 2481.9 0.5626 1.39965 0.0000851 314.40 0.027 0.0001

FS173 Byp_Nozz.Fl_O 314.42 6.950 556.40 2.39 0.0000 688.65 3.670 463.58 2006.9 1.0000 1.39965 0.0000851 314.40 0.027 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1040.08 1.630 0.9122 3986.202 1.1642 0.9180 -8375.0 51.41 26.07

LPC 190.28 2.471 0.8549 3986.202 1.3447 0.8720 -3220.3 2.91 2.10

HPC 90.34 11.911 0.8611 10157.437 2.1368 0.8985 -14821.5 30.61 29.54

HPT 12.10 4.282 0.9108 215.996 1.3473 0.8901 14821.5 

LPT 55.95 4.335 0.9149 89.680 1.3918 0.8981 11596.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1208.47 1.615 0.9140 3948.195 0.0614 0.8607 1.0235 0.9980 0.9905

LPC 152.70 2.579 0.8241 1.053 0.0000 1.2463 0.9316 1.0373 0.0003

HPC 82.16 11.397 0.8700 9886.647 13.0781 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.191 0.9108 1.298 4.1911 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.509 0.9217 1.009 3.5086 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–11
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3751.73 9126.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1298 1026.69 82.75 28.636

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6771 1026.69 82.75 6.605

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 989.63 73.47 35.832

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1216.73 130.98 81.822

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 989.63 73.47 35.832

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1388.23 175.50 125.513

Splitter 5.4660 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 989.63 73.47 35.832

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11368.0 6847.7 14821.5 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 649.67 -10.01 10.537

LP_Shaft 3826.4 15916.7 11596.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.6081 1388.23 175.50 122.622

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7822 1388.23 175.50 68.862

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1388.23 175.50 125.513

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1388.23 175.50 125.513

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1388.23 175.50 125.513

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 556.40 2.39 6.950

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 556.40 2.39 6.950

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 556.40 2.39 6.950

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 556.40 2.39 6.950

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2769.97 0.9995 0.0230 0.99416 0.02344 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.314 0.9816 1.0000 0.9800 613.40 1.000 1579.6 3305.7

Byp_Nozz 2.435 0.9814 1.0000 0.9800 2006.86 1.000 1034.7 11750.0

NASA/TM—2013-218094 I–12
************************************************************************************************************************************ 

Date:05/10/13 Time:11:39:17 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 472.55 Stator 1 exit: 490.30 Stator 2 inlet: 511.72 Stator 2 exit: 520.48 

 Stator 3 inlet: 546.36 Stator 3 exit: 555.19 Stator 4 inlet: 579.49 Stator 4 exit: 587.65 

 Stator 5 inlet: 606.98 Stator 5 exit: 614.67 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.21 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 2.13 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 440.91 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.78 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 461.72 

Additional Water at LPC Exit 0.0062973 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 366.73 5636.1 0.6026 3396.21 5.5267 789.49 28.478 1.457 79.800 2722.5 2559.4 1780.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 366.73 4.267 477.92 -16.44 0.0000 1212.50 2.854 425.97 3699.1 0.7800 1.40068 0.0000851 366.70 0.031 0.0001

FS1 Inlet.Fl_O 366.73 4.267 477.92 -16.44 0.0000 1212.50 3.326 445.04 4168.2 0.6072 1.40068 0.0000851 366.70 0.031 0.0001

FS12 Splitter.Fl_02 310.54 4.265 477.92 -16.44 0.0000 1027.24 3.324 445.05 3531.8 0.6071 1.40068 0.0000851 310.51 0.026 0.0001

FS2 Splitter.Fl_01 56.19 4.265 477.92 -16.44 0.0000 185.87 3.780 461.72 830.5 0.4184 1.40068 0.0000851 56.18 0.005 0.0001

FS14 Fan.Fl_O 310.54 6.848 553.91 1.79 0.0000 688.65 5.685 525.22 2606.7 0.5226 1.39969 0.0000851 310.51 0.026 0.0001

FS23 LPC.Fl_O 56.19 10.470 640.36 22.58 0.0000 87.63 9.416 621.30 412.6 0.3925 1.39778 0.0000851 56.18 0.005 0.0001

FS24 VaporIN.Fl_O 56.54 10.470 647.64 -11.63 0.0000 88.68 9.382 627.76 412.6 0.3994 1.39668 0.0063824 56.18 0.359 0.0063

FS25 Bleed2.Fl_O 56.54 10.470 647.64 -11.63 0.0000 88.68 9.382 627.76 412.6 0.3994 1.39668 0.0063824 56.18 0.359 0.0063

FS3 HPC.Fl_O 53.80 121.507 1373.71 170.60 0.0000 10.59 109.067 1335.19 49.7 0.4016 1.35643 0.0063824 53.46 0.341 0.0063

FS36 Bleed3.Fl_O 41.70 121.507 1373.71 170.60 0.0000 8.21 114.299 1351.77 49.3 0.3014 1.35643 0.0063824 41.43 0.264 0.0063

FS4 Burner.Fl_O 42.64 118.709 2722.47 143.23 0.0228 12.09 112.117 2687.59 74.6 0.3004 1.28726 0.0063824 41.43 0.264 0.0335

FS45 HPT.Fl_O 56.82 27.696 1788.41 -30.20 0.0170 55.99 24.922 1742.75 265.4 0.4018 1.32336 0.0063824 55.53 0.354 0.0267

FS49 LPT.Fl_O 57.49 6.387 1280.76 -165.54 0.0168 207.85 5.508 1232.31 860.2 0.4722 1.35064 0.0063824 56.18 0.359 0.0265

FS5 TEGV.Fl_O 57.49 6.387 1280.82 -165.54 0.0168 207.85 5.508 1232.37 860.2 0.4722 1.35063 0.0063824 56.18 0.359 0.0265

FS8 Core_Nozz.Fl_O 57.49 6.387 1280.95 -165.54 0.0168 207.87 3.413 1086.26 613.4 1.0000 1.35062 0.0063824 56.18 0.359 0.0265

FS17 FanDuctLkg.Fl_O 310.54 6.848 553.91 1.79 0.0000 688.65 5.685 525.22 2606.7 0.5226 1.39969 0.0000851 310.51 0.026 0.0001

FS171 Bleed15.Fl_O 310.54 6.848 553.91 1.79 0.0000 688.65 5.525 520.94 2481.9 0.5626 1.39969 0.0000851 310.51 0.026 0.0001

FS172 FanDuct.Fl_O 310.54 6.848 553.91 1.79 0.0000 688.65 5.525 520.94 2481.9 0.5626 1.39969 0.0000851 310.51 0.026 0.0001

FS173 Byp_Nozz.Fl_O 310.54 6.848 553.91 1.79 0.0000 688.65 3.617 461.51 2006.9 1.0000 1.39969 0.0000851 310.51 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1027.24 1.606 0.9118 3938.129 1.1590 0.9175 -8009.1 56.02 27.11

LPC 185.87 2.455 0.8600 3938.129 1.3399 0.8764 -3101.8 3.20 2.45

HPC 88.68 11.605 0.8614 10111.890 2.1211 0.8985 -14224.3 31.85 30.67

HPT 12.09 4.286 0.9102 216.556 1.3491 0.8899 14224.3 

LPT 55.99 4.336 0.9143 89.390 1.3934 0.8977 11110.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1193.55 1.592 0.9137 3900.579 0.0606 0.8607 1.0235 0.9980 0.9905

LPC 149.29 2.529 0.8227 1.040 0.0000 1.2450 0.9519 1.0454 0.0003

HPC 80.65 11.105 0.8703 9842.314 12.9732 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.195 0.9102 1.301 4.1951 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.509 0.9211 1.006 3.5093 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–13
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3699.11 8998.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0808 1018.12 79.49 27.696

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6616 1018.12 79.49 6.387

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 981.68 70.37 34.898

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1205.00 126.86 79.313

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 981.68 70.37 34.898

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1373.71 170.60 121.507

Splitter 5.5267 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 981.68 70.37 34.898

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11299.3 6611.7 14224.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 647.64 -11.63 10.470

LP_Shaft 3780.3 15436.9 11110.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4561 1373.71 170.60 118.709

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6492 1373.71 170.60 66.649

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.71 170.60 121.507

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.71 170.60 121.507

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.71 170.60 121.507

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.91 1.79 6.848

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.91 1.79 6.848

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.91 1.79 6.848

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.91 1.79 6.848

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2722.47 0.9995 0.0230 0.94339 0.02277 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.238 0.9816 1.0000 0.9800 613.40 1.000 1565.2 3139.5

Byp_Nozz 2.400 0.9814 1.0000 0.9800 2006.86 1.000 1032.4 11495.4

NASA/TM—2013-218094 I–14
************************************************************************************************************************************ 

Date:05/10/13 Time:11:39:52 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 473.71 Stator 1 exit: 491.17 Stator 2 inlet: 512.37 Stator 2 exit: 521.20 

 Stator 3 inlet: 546.52 Stator 3 exit: 555.35 Stator 4 inlet: 579.13 Stator 4 exit: 587.27 

 Stator 5 inlet: 606.24 Stator 5 exit: 613.87 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.05 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 2.08 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 431.80 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.80 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 462.38 

Additional Water at LPC Exit 0.0064518 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 362.93 5427.7 0.6025 3270.15 5.5717 789.49 27.815 1.415 76.800 2689.4 2528.9 1758.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 362.93 4.267 477.92 -16.44 0.0000 1199.93 2.854 425.97 3660.7 0.7800 1.40068 0.0000851 362.90 0.031 0.0001

FS1 Inlet.Fl_O 362.93 4.267 477.92 -16.44 0.0000 1199.93 3.353 446.10 4168.2 0.5966 1.40068 0.0000851 362.90 0.031 0.0001

FS12 Splitter.Fl_02 307.70 4.265 477.92 -16.44 0.0000 1017.85 3.349 445.98 3531.8 0.5978 1.40068 0.0000851 307.67 0.026 0.0001

FS2 Splitter.Fl_01 55.23 4.265 477.92 -16.44 0.0000 182.68 3.799 462.38 830.5 0.4095 1.40068 0.0000851 55.22 0.005 0.0001

FS14 Fan.Fl_O 307.70 6.775 552.16 1.37 0.0000 688.66 5.624 523.55 2606.7 0.5226 1.39972 0.0000851 307.67 0.026 0.0001

FS23 LPC.Fl_O 55.23 10.425 638.89 22.22 0.0000 86.40 9.408 620.50 412.6 0.3859 1.39782 0.0000851 55.22 0.005 0.0001

FS24 VaporIN.Fl_O 55.58 10.425 646.36 -12.81 0.0000 87.47 9.375 627.16 412.6 0.3927 1.39669 0.0065369 55.22 0.361 0.0065

FS25 Bleed2.Fl_O 55.58 10.425 646.36 -12.81 0.0000 87.47 9.375 627.16 412.6 0.3927 1.39669 0.0065369 55.22 0.361 0.0065

FS3 HPC.Fl_O 52.89 118.679 1363.70 167.12 0.0000 10.62 106.450 1325.14 49.7 0.4029 1.35699 0.0065369 52.54 0.343 0.0065

FS36 Bleed3.Fl_O 40.99 118.679 1363.70 167.12 0.0000 8.23 111.596 1341.76 49.3 0.3023 1.35699 0.0065369 40.72 0.266 0.0065

FS4 Burner.Fl_O 41.89 115.946 2689.43 140.40 0.0223 12.09 109.507 2654.85 74.6 0.3002 1.28848 0.0065369 40.72 0.266 0.0331

FS45 HPT.Fl_O 55.84 27.033 1766.10 -30.98 0.0166 56.01 24.323 1720.82 265.4 0.4019 1.32457 0.0065369 54.57 0.357 0.0265

FS49 LPT.Fl_O 56.49 6.233 1263.92 -164.52 0.0164 207.91 5.375 1215.96 860.2 0.4722 1.35191 0.0065369 55.22 0.361 0.0262

FS5 TEGV.Fl_O 56.49 6.233 1263.99 -164.52 0.0164 207.91 5.375 1216.02 860.2 0.4722 1.35190 0.0065369 55.22 0.361 0.0262

FS8 Core_Nozz.Fl_O 56.49 6.233 1264.12 -164.52 0.0164 207.92 3.330 1071.44 613.4 1.0000 1.35189 0.0065369 55.22 0.361 0.0262

FS17 FanDuctLkg.Fl_O 307.70 6.775 552.16 1.37 0.0000 688.66 5.624 523.55 2606.7 0.5226 1.39972 0.0000851 307.67 0.026 0.0001

FS171 Bleed15.Fl_O 307.70 6.775 552.16 1.37 0.0000 688.66 5.465 519.29 2481.9 0.5626 1.39972 0.0000851 307.67 0.026 0.0001

FS172 FanDuct.Fl_O 307.70 6.775 552.16 1.37 0.0000 688.66 5.465 519.29 2481.9 0.5626 1.39972 0.0000851 307.67 0.026 0.0001

FS173 Byp_Nozz.Fl_O 307.70 6.775 552.16 1.37 0.0000 688.66 3.578 460.04 2006.9 1.0000 1.39972 0.0000851 307.67 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1017.85 1.589 0.9108 3905.459 1.1553 0.9164 -7752.1 58.14 27.87

LPC 182.68 2.445 0.8631 3905.459 1.3368 0.8791 -3021.0 3.47 2.76

HPC 87.47 11.384 0.8614 10078.845 2.1098 0.8983 -13806.9 32.74 31.50

HPT 12.09 4.289 0.9097 216.957 1.3504 0.8898 13806.9 

LPT 56.01 4.337 0.9138 89.207 1.3944 0.8971 10773.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1182.64 1.575 0.9126 3868.221 0.0600 0.8607 1.0235 0.9980 0.9905

LPC 147.18 2.495 0.8220 1.032 0.0000 1.2412 0.9662 1.0500 0.0003

HPC 79.55 10.895 0.8703 9810.149 12.8977 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.198 0.9097 1.304 4.1978 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.510 0.9206 1.003 3.5098 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–15
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3660.74 8905.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0454 1012.27 77.16 27.033

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6503 1012.27 77.16 6.233

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 976.27 68.16 34.241

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1196.94 123.94 77.543

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 976.27 68.16 34.241

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1363.70 167.12 118.679

Splitter 5.5717 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 976.27 68.16 34.241

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11251.3 6445.0 13806.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 646.36 -12.81 10.425

LP_Shaft 3748.9 15092.9 10773.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.3463 1363.70 167.12 115.946

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.5532 1363.70 167.12 65.088

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1363.70 167.12 118.679

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1363.70 167.12 118.679

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1363.70 167.12 118.679

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 552.16 1.37 6.775

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 552.16 1.37 6.775

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 552.16 1.37 6.775

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 552.16 1.37 6.775

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2689.42 0.9995 0.0230 0.90837 0.02231 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.184 0.9816 1.0000 0.9800 613.40 1.000 1555.2 3022.4

Byp_Nozz 2.374 0.9815 1.0000 0.9800 2006.86 1.000 1030.7 11310.8

NASA/TM—2013-218094 I–16
 10μm, ISA +18R

************************************************************************************************************************************ 

Date:05/13/13 Time:07:04:22 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 23/ 51/ 2/20 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 444.20 Stator 1 exit: 462.85 Stator 2 inlet: 484.44 Stator 2 exit: 491.60 

 Stator 3 inlet: 520.52 Stator 3 exit: 528.49 Stator 4 inlet: 555.54 Stator 4 exit: 563.26 

 Stator 5 inlet: 584.14 Stator 5 exit: 591.68 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.21 

Fan Bypass Relative Humidity 0.15 

LPC Inlet Relative Humidity 2.29 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 484.89 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 438.14 

Additional Water at LPC Exit 0.0007415 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 396.30 6797.5 0.5971 4058.61 5.2856 772.64 32.328 1.706 100.000 2814.2 2641.1 1835.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 396.30 4.267 457.74 -20.96 0.0000 1282.27 2.854 407.97 3911.8 0.7800 1.40084 0.0000295 396.29 0.012 0.0000

FS1 Inlet.Fl_O 396.30 4.267 457.74 -20.96 0.0000 1282.27 3.150 419.67 4168.2 0.6726 1.40084 0.0000295 396.29 0.012 0.0000

FS12 Splitter.Fl_02 333.25 4.265 457.74 -20.96 0.0000 1078.81 3.174 420.64 3531.8 0.6633 1.40084 0.0000295 333.24 0.010 0.0000

FS2 Splitter.Fl_01 63.05 4.265 457.74 -20.96 0.0000 204.10 3.660 438.14 830.5 0.4724 1.40084 0.0000295 63.05 0.002 0.0000

FS14 Fan.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS23 LPC.Fl_O 63.05 10.488 620.60 18.14 0.0000 96.64 9.163 597.17 412.6 0.4436 1.39831 0.0000295 63.05 0.002 0.0000

FS24 VaporIN.Fl_O 63.10 10.488 621.54 14.10 0.0000 96.78 9.158 597.98 412.6 0.4447 1.39818 0.0007710 63.05 0.049 0.0008

FS25 Bleed2.Fl_O 63.10 10.488 621.54 14.10 0.0000 96.78 9.158 597.98 412.6 0.4447 1.39818 0.0007710 63.05 0.049 0.0008

FS3 HPC.Fl_O 60.03 137.939 1374.13 201.80 0.0000 10.41 124.410 1337.20 49.7 0.3924 1.35732 0.0007710 59.99 0.046 0.0008

FS36 Bleed3.Fl_O 46.53 137.939 1374.13 201.80 0.0000 8.07 130.079 1353.03 49.3 0.2951 1.35732 0.0007710 46.49 0.036 0.0008

FS4 Burner.Fl_O 47.65 134.763 2814.20 171.65 0.0242 12.10 127.304 2778.46 74.6 0.3004 1.28466 0.0007710 46.49 0.036 0.0299

FS45 HPT.Fl_O 63.48 31.493 1844.04 -6.29 0.0181 55.86 28.368 1797.65 265.4 0.4002 1.32102 0.0007710 62.31 0.048 0.0227

FS49 LPT.Fl_O 64.22 7.239 1320.92 -145.95 0.0179 208.07 6.244 1271.28 860.2 0.4724 1.34817 0.0007710 63.05 0.049 0.0224

FS5 TEGV.Fl_O 64.22 7.239 1320.99 -145.95 0.0179 208.08 6.244 1271.34 860.2 0.4724 1.34817 0.0007710 63.05 0.049 0.0224

FS8 Core_Nozz.Fl_O 64.22 7.239 1321.11 -145.95 0.0179 208.09 3.871 1121.47 613.4 1.0000 1.34816 0.0007710 63.05 0.049 0.0224

FS17 FanDuctLkg.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS171 Bleed15.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS172 FanDuct.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS173 Byp_Nozz.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 3.833 450.06 2006.9 1.0000 1.39992 0.0000295 333.24 0.010 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.81 1.702 0.9114 4139.469 1.1801 0.9178 -9322.3 36.69 23.09

LPC 204.10 2.459 0.8238 4139.469 1.3558 0.8444 -3487.4 2.97 2.24

HPC 96.78 13.153 0.8584 10365.299 2.2109 0.8979 -16349.9 25.94 25.16

HPT 12.10 4.279 0.9118 213.891 1.3468 0.8911 16349.9 

LPT 55.86 4.351 0.9155 90.557 1.3925 0.8988 12809.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.47 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2233 0.8348 0.9876 0.0003

HPC 88.02 12.580 0.8673 10088.967 13.5045 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.188 0.9118 1.285 4.1882 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9223 1.019 3.5201 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–17
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3911.78 9516.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3219 1005.68 107.95 31.493

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7382 1005.68 107.95 7.239

TEGV 0.0000 0.4724 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 967.90 98.57 38.527

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1199.38 156.76 89.508

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 967.90 98.57 38.527

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1374.13 201.80 137.939

Splitter 5.2856 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 967.90 98.57 38.527

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11346.7 7568.0 16349.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 621.54 14.10 10.488

LP_Shaft 3888.7 17300.7 12809.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.2042 1374.13 201.80 134.763

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.3038 1374.13 201.80 75.693

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1374.13 201.80 137.939

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1374.13 201.80 137.939

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1374.13 201.80 137.939

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2814.20 0.9995 0.0230 1.12739 0.02425 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.536 0.9809 1.0000 0.9800 613.40 1.000 1586.4 3790.4

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1019.5 12523.9

NASA/TM—2013-218094 I–18
************************************************************************************************************************************ 

Date:05/13/13 Time:07:05:00 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 21/ 35/ 1/19 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 450.34 Stator 1 exit: 467.50 Stator 2 inlet: 487.90 Stator 2 exit: 495.85 

 Stator 3 inlet: 521.31 Stator 3 exit: 529.50 Stator 4 inlet: 553.54 Stator 4 exit: 561.15 

 Stator 5 inlet: 580.11 Stator 5 exit: 587.37 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.13 

Fan Bypass Relative Humidity 0.18 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 444.99 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.75 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 441.23 

Additional Water at LPC Exit 0.0008168 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 378.72 5804.3 0.5902 3425.49 5.4316 772.64 29.234 1.498 84.000 2647.6 2487.0 1723.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 378.72 4.267 457.74 -20.96 0.0000 1225.39 2.854 407.97 3738.3 0.7800 1.40084 0.0000295 378.71 0.011 0.0000

FS1 Inlet.Fl_O 378.72 4.267 457.74 -20.96 0.0000 1225.39 3.296 425.16 4168.2 0.6183 1.40084 0.0000295 378.71 0.011 0.0000

FS12 Splitter.Fl_02 319.83 4.265 457.74 -20.96 0.0000 1035.38 3.303 425.45 3531.8 0.6153 1.40084 0.0000295 319.82 0.009 0.0000

FS2 Splitter.Fl_01 58.88 4.265 457.74 -20.96 0.0000 190.62 3.751 441.23 830.5 0.4320 1.40084 0.0000295 58.88 0.002 0.0000

FS14 Fan.Fl_O 319.83 6.913 532.10 -3.13 0.0000 688.70 5.738 504.53 2606.7 0.5226 1.40004 0.0000295 319.82 0.009 0.0000

FS23 LPC.Fl_O 58.88 10.356 612.59 16.21 0.0000 90.81 9.225 592.72 412.6 0.4100 1.39851 0.0000295 58.88 0.002 0.0000

FS24 VaporIN.Fl_O 58.93 10.356 613.62 11.76 0.0000 90.96 9.220 593.63 412.6 0.4110 1.39837 0.0008462 58.88 0.050 0.0008

FS25 Bleed2.Fl_O 58.93 10.356 613.62 11.76 0.0000 90.96 9.220 593.63 412.6 0.4110 1.39837 0.0008462 58.88 0.050 0.0008

FS3 HPC.Fl_O 56.07 124.735 1322.38 187.94 0.0000 10.55 112.130 1285.51 49.7 0.3983 1.36038 0.0008462 56.03 0.047 0.0008

FS36 Bleed3.Fl_O 43.46 124.735 1322.38 187.94 0.0000 8.18 117.423 1301.37 49.3 0.2991 1.36038 0.0008462 43.42 0.037 0.0008

FS4 Burner.Fl_O 44.41 121.862 2647.58 161.07 0.0219 12.10 115.103 2613.42 74.6 0.2996 1.29090 0.0008462 43.42 0.037 0.0272

FS45 HPT.Fl_O 59.19 28.387 1731.31 -6.59 0.0164 55.99 25.553 1686.86 265.4 0.4004 1.32716 0.0008462 58.19 0.049 0.0207

FS49 LPT.Fl_O 59.88 6.518 1235.69 -137.13 0.0162 208.40 5.620 1188.48 860.2 0.4721 1.35461 0.0008462 58.88 0.050 0.0204

FS5 TEGV.Fl_O 59.88 6.518 1235.75 -137.13 0.0162 208.40 5.620 1188.55 860.2 0.4721 1.35461 0.0008462 58.88 0.050 0.0204

FS8 Core_Nozz.Fl_O 59.88 6.518 1235.88 -137.13 0.0162 208.41 3.479 1046.35 613.4 1.0000 1.35460 0.0008462 58.88 0.050 0.0204

FS17 FanDuctLkg.Fl_O 319.83 6.913 532.10 -3.13 0.0000 688.70 5.738 504.53 2606.7 0.5226 1.40004 0.0000295 319.82 0.009 0.0000

FS171 Bleed15.Fl_O 319.83 6.913 532.10 -3.13 0.0000 688.70 5.576 500.41 2481.9 0.5625 1.40004 0.0000295 319.82 0.009 0.0000

FS172 FanDuct.Fl_O 319.83 6.913 532.10 -3.13 0.0000 688.70 5.576 500.41 2481.9 0.5625 1.40004 0.0000295 319.82 0.009 0.0000

FS173 Byp_Nozz.Fl_O 319.83 6.913 532.10 -3.13 0.0000 688.70 3.651 443.30 2006.9 1.0000 1.40004 0.0000295 319.82 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1035.38 1.621 0.9117 3969.398 1.1625 0.9175 -8068.0 52.98 26.45

LPC 190.62 2.428 0.8528 3969.398 1.3383 0.8699 -3096.3 2.95 2.15

HPC 90.96 12.045 0.8607 10175.576 2.1551 0.8986 -14333.9 29.96 28.94

HPT 12.10 4.293 0.9099 215.099 1.3532 0.8903 14333.9 

LPT 55.99 4.355 0.9131 89.619 1.3980 0.8962 11164.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1203.01 1.607 0.9135 3931.550 0.0611 0.8607 1.0235 0.9980 0.9905

LPC 151.31 2.561 0.8233 1.048 0.0000 1.2598 0.9151 1.0358 0.0003

HPC 82.73 11.524 0.8696 9904.302 13.1355 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.202 0.9099 1.293 4.2016 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.523 0.9199 1.008 3.5235 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–19
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3738.26 9094.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1687 974.80 99.85 28.387

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6895 974.80 99.85 6.518

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 939.22 91.04 35.519

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1157.42 145.66 81.271

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 939.22 91.04 35.519

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1322.38 187.94 124.735

Splitter 5.4316 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 939.22 91.04 35.519

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11067.8 6802.0 14333.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 613.62 11.76 10.356

LP_Shaft 3729.0 15724.4 11164.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.7289 1322.38 187.94 121.862

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.8879 1322.38 187.94 68.395

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1322.38 187.94 124.735

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1322.38 187.94 124.735

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1322.38 187.94 124.735

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 532.10 -3.13 6.913

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 532.10 -3.13 6.913

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 532.10 -3.13 6.913

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 532.10 -3.13 6.913

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2647.56 0.9995 0.0230 0.95152 0.02191 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.284 0.9816 1.0000 0.9800 613.40 1.000 1535.8 3241.8

Byp_Nozz 2.422 0.9814 1.0000 0.9800 2006.86 1.000 1011.8 11657.2

NASA/TM—2013-218094 I–20
************************************************************************************************************************************ 

Date:05/13/13 Time:07:05:36 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 451.95 Stator 1 exit: 468.71 Stator 2 inlet: 488.79 Stator 2 exit: 496.87 

 Stator 3 inlet: 521.51 Stator 3 exit: 529.72 Stator 4 inlet: 553.00 Stator 4 exit: 560.57 

 Stator 5 inlet: 579.02 Stator 5 exit: 586.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.88 

Fan Bypass Relative Humidity 0.20 

LPC Inlet Relative Humidity 1.92 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 432.78 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.78 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.13 

Additional Water at LPC Exit 0.0008427 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 373.41 5513.2 0.5893 3249.09 5.4875 772.64 28.307 1.439 79.800 2600.1 2443.2 1691.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 373.41 4.267 457.74 -20.96 0.0000 1208.21 2.854 407.97 3685.8 0.7800 1.40084 0.0000295 373.40 0.011 0.0000

FS1 Inlet.Fl_O 373.41 4.267 457.74 -20.96 0.0000 1208.21 3.336 426.59 4168.2 0.6035 1.40084 0.0000295 373.40 0.011 0.0000

FS12 Splitter.Fl_02 315.85 4.265 457.74 -20.96 0.0000 1022.48 3.337 426.71 3531.8 0.6023 1.40084 0.0000295 315.84 0.009 0.0000

FS2 Splitter.Fl_01 57.56 4.265 457.74 -20.96 0.0000 186.33 3.778 442.13 830.5 0.4197 1.40084 0.0000295 57.56 0.002 0.0000

FS14 Fan.Fl_O 315.85 6.811 529.69 -3.70 0.0000 688.70 5.654 502.24 2606.7 0.5226 1.40008 0.0000295 315.84 0.009 0.0000

FS23 LPC.Fl_O 57.56 10.300 610.43 15.69 0.0000 89.09 9.224 591.52 412.6 0.4004 1.39856 0.0000295 57.56 0.002 0.0000

FS24 VaporIN.Fl_O 57.61 10.300 611.50 11.10 0.0000 89.24 9.219 592.47 412.6 0.4014 1.39841 0.0008721 57.56 0.050 0.0009

FS25 Bleed2.Fl_O 57.61 10.300 611.50 11.10 0.0000 89.24 9.219 592.47 412.6 0.4014 1.39841 0.0008721 57.56 0.050 0.0009

FS3 HPC.Fl_O 54.81 120.781 1307.56 183.97 0.0000 10.59 108.469 1270.71 49.7 0.4000 1.36127 0.0008721 54.77 0.048 0.0009

FS36 Bleed3.Fl_O 42.48 120.781 1307.56 183.97 0.0000 8.21 113.643 1286.58 49.3 0.3002 1.36127 0.0008721 42.44 0.037 0.0009

FS4 Burner.Fl_O 43.38 117.999 2600.14 157.99 0.0213 12.10 111.454 2566.43 74.6 0.2993 1.29270 0.0008721 42.44 0.037 0.0265

FS45 HPT.Fl_O 57.84 27.463 1699.57 -6.69 0.0159 56.02 24.718 1655.72 265.4 0.4004 1.32897 0.0008721 56.88 0.050 0.0201

FS49 LPT.Fl_O 58.51 6.304 1211.86 -134.67 0.0157 208.49 5.434 1165.36 860.2 0.4720 1.35642 0.0008721 57.56 0.050 0.0199

FS5 TEGV.Fl_O 58.51 6.304 1211.93 -134.67 0.0157 208.49 5.434 1165.42 860.2 0.4720 1.35642 0.0008721 57.56 0.050 0.0199

FS8 Core_Nozz.Fl_O 58.51 6.304 1212.06 -134.67 0.0157 208.50 3.363 1025.43 613.4 1.0000 1.35641 0.0008721 57.56 0.050 0.0199

FS17 FanDuctLkg.Fl_O 315.85 6.811 529.69 -3.70 0.0000 688.70 5.654 502.24 2606.7 0.5226 1.40008 0.0000295 315.84 0.009 0.0000

FS171 Bleed15.Fl_O 315.85 6.811 529.69 -3.70 0.0000 688.70 5.494 498.14 2481.9 0.5625 1.40008 0.0000295 315.84 0.009 0.0000

FS172 FanDuct.Fl_O 315.85 6.811 529.69 -3.70 0.0000 688.70 5.494 498.14 2481.9 0.5625 1.40008 0.0000295 315.84 0.009 0.0000

FS173 Byp_Nozz.Fl_O 315.85 6.811 529.69 -3.70 0.0000 688.70 3.597 441.29 2006.9 1.0000 1.40008 0.0000295 315.84 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1022.48 1.597 0.9114 3921.443 1.1572 0.9170 -7709.0 57.11 27.50

LPC 186.33 2.415 0.8589 3921.443 1.3336 0.8752 -2984.3 3.33 2.62

HPC 89.24 11.726 0.8613 10127.580 2.1383 0.8988 -13747.6 31.23 30.09

HPT 12.10 4.297 0.9091 215.655 1.3548 0.8897 13747.6 

LPT 56.02 4.356 0.9124 89.359 1.3995 0.8952 10693.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1188.02 1.583 0.9132 3884.052 0.0603 0.8607 1.0235 0.9980 0.9905

LPC 148.21 2.511 0.8223 1.036 0.0000 1.2572 0.9364 1.0445 0.0003

HPC 81.17 11.221 0.8702 9857.585 13.0271 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.205 0.9090 1.296 4.2053 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.524 0.9191 1.005 3.5244 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–21
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3685.85 8967.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1199 966.04 97.54 27.463

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6740 966.04 97.54 6.304

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 931.10 88.89 34.606

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1145.44 142.48 78.798

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 931.10 88.89 34.606

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1307.56 183.97 120.781

Splitter 5.4875 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 931.10 88.89 34.606

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10996.6 6566.1 13747.6 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 611.50 11.10 10.300

LP_Shaft 3683.9 15245.3 10693.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.5775 1307.56 183.97 117.999

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7555 1307.56 183.97 66.212

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1307.56 183.97 120.781

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1307.56 183.97 120.781

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1307.56 183.97 120.781

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.69 -3.70 6.811

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.69 -3.70 6.811

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.69 -3.70 6.811

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.69 -3.70 6.811

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2600.12 0.9995 0.0230 0.90252 0.02126 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.209 0.9816 1.0000 0.9800 613.40 1.000 1521.3 3078.7

Byp_Nozz 2.387 0.9815 1.0000 0.9800 2006.86 1.000 1009.5 11401.7

NASA/TM—2013-218094 I–22
************************************************************************************************************************************ 

Date:05/13/13 Time:07:06:12 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 453.04 Stator 1 exit: 469.53 Stator 2 inlet: 489.43 Stator 2 exit: 497.59 

 Stator 3 inlet: 521.69 Stator 3 exit: 529.91 Stator 4 inlet: 552.69 Stator 4 exit: 560.24 

 Stator 5 inlet: 578.36 Stator 5 exit: 585.50 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.72 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 1.87 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 424.11 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.80 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.75 

Additional Water at LPC Exit 0.0008620 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 369.50 5306.5 0.5897 3129.48 5.5280 772.64 27.657 1.397 76.800 2568.0 2413.5 1670.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 369.50 4.267 457.74 -20.96 0.0000 1195.55 2.854 407.97 3647.2 0.7800 1.40084 0.0000295 369.49 0.011 0.0000

FS1 Inlet.Fl_O 369.50 4.267 457.74 -20.96 0.0000 1195.55 3.363 427.60 4168.2 0.5930 1.40084 0.0000295 369.49 0.011 0.0000

FS12 Splitter.Fl_02 312.90 4.265 457.74 -20.96 0.0000 1012.92 3.362 427.60 3531.8 0.5929 1.40084 0.0000295 312.89 0.009 0.0000

FS2 Splitter.Fl_01 56.60 4.265 457.74 -20.96 0.0000 183.23 3.796 442.75 830.5 0.4110 1.40084 0.0000295 56.60 0.002 0.0000

FS14 Fan.Fl_O 312.90 6.737 528.05 -4.10 0.0000 688.70 5.592 500.68 2606.7 0.5226 1.40010 0.0000295 312.89 0.009 0.0000

FS23 LPC.Fl_O 56.60 10.260 609.04 15.36 0.0000 87.85 9.222 590.79 412.6 0.3936 1.39859 0.0000295 56.60 0.002 0.0000

FS24 VaporIN.Fl_O 56.65 10.260 610.14 10.66 0.0000 88.00 9.217 591.77 412.6 0.3946 1.39844 0.0008914 56.60 0.050 0.0009

FS25 Bleed2.Fl_O 56.65 10.260 610.14 10.66 0.0000 88.00 9.217 591.77 412.6 0.3946 1.39844 0.0008914 56.60 0.050 0.0009

FS3 HPC.Fl_O 53.90 118.005 1297.61 181.29 0.0000 10.62 105.903 1260.75 49.7 0.4012 1.36188 0.0008914 53.86 0.048 0.0009

FS36 Bleed3.Fl_O 41.77 118.005 1297.61 181.29 0.0000 8.23 110.991 1276.63 49.3 0.3011 1.36188 0.0008914 41.74 0.037 0.0009

FS4 Burner.Fl_O 42.64 115.288 2568.04 155.90 0.0208 12.10 108.891 2534.65 74.6 0.2991 1.29394 0.0008914 41.74 0.037 0.0260

FS45 HPT.Fl_O 56.86 26.816 1678.19 -6.76 0.0155 56.05 24.133 1634.72 265.4 0.4004 1.33020 0.0008914 55.94 0.050 0.0197

FS49 LPT.Fl_O 57.52 6.155 1195.86 -133.00 0.0154 208.55 5.305 1149.83 860.2 0.4719 1.35765 0.0008914 56.60 0.050 0.0195

FS5 TEGV.Fl_O 57.52 6.155 1195.93 -133.00 0.0154 208.55 5.305 1149.89 860.2 0.4719 1.35764 0.0008914 56.60 0.050 0.0195

FS8 Core_Nozz.Fl_O 57.52 6.155 1196.06 -133.00 0.0154 208.57 3.282 1011.39 613.4 1.0000 1.35763 0.0008914 56.60 0.050 0.0195

FS17 FanDuctLkg.Fl_O 312.90 6.737 528.05 -4.10 0.0000 688.70 5.592 500.68 2606.7 0.5226 1.40010 0.0000295 312.89 0.009 0.0000

FS171 Bleed15.Fl_O 312.90 6.737 528.05 -4.10 0.0000 688.70 5.434 496.59 2481.9 0.5625 1.40010 0.0000295 312.89 0.009 0.0000

FS172 FanDuct.Fl_O 312.90 6.737 528.05 -4.10 0.0000 688.70 5.434 496.59 2481.9 0.5625 1.40010 0.0000295 312.89 0.009 0.0000

FS173 Byp_Nozz.Fl_O 312.90 6.737 528.05 -4.10 0.0000 688.70 3.558 439.91 2006.9 1.0000 1.40010 0.0000295 312.89 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1012.92 1.580 0.9094 3888.842 1.1536 0.9151 -7462.2 59.24 28.27

LPC 183.23 2.406 0.8625 3888.842 1.3305 0.8783 -2908.0 3.61 2.87

HPC 88.00 11.501 0.8614 10094.302 2.1268 0.8986 -13344.0 32.12 30.91 

HPT 12.10 4.299 0.9085 216.045 1.3560 0.8892 13344.1 

LPT 56.05 4.357 0.9118 89.179 1.4005 0.8946 10370.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1176.91 1.566 0.9113 3851.762 0.0597 0.8607 1.0235 0.9980 0.9905

LPC 146.11 2.478 0.8217 1.027 0.0000 1.2541 0.9513 1.0497 0.0003

HPC 80.04 11.006 0.8703 9825.195 12.9518 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.208 0.9085 1.298 4.2078 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9186 1.003 3.5249 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–23
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3647.24 8873.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0848 960.19 95.97 26.816

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6628 960.19 95.97 6.155

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.68 87.44 33.964

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1137.41 140.34 77.062

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.68 87.44 33.964

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1297.61 181.29 118.005

Splitter 5.5280 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 925.68 87.44 33.964

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10948.3 6401.4 13344.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 610.14 10.66 10.260

LP_Shaft 3653.3 14908.6 10370.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4684 1297.61 181.29 115.288

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6600 1297.61 181.29 64.682

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1297.61 181.29 118.005

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1297.61 181.29 118.005

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1297.61 181.29 118.005

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 528.05 -4.10 6.737

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 528.05 -4.10 6.737

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 528.05 -4.10 6.737

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 528.05 -4.10 6.737

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2568.02 0.9995 0.0230 0.86930 0.02083 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.157 0.9815 1.0000 0.9800 613.40 1.000 1511.5 2964.7

Byp_Nozz 2.361 0.9815 1.0000 0.9800 2006.86 1.000 1008.0 11215.0

NASA/TM—2013-218094 I–24
 10μm, ISA +36R

************************************************************************************************************************************ 

Date:05/13/13 Time:07:24:08 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 38/ 1/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 463.97 Stator 1 exit: 483.46 Stator 2 inlet: 506.07 Stator 2 exit: 513.64 

 Stator 3 inlet: 543.80 Stator 3 exit: 552.19 Stator 4 inlet: 580.37 Stator 4 exit: 588.48 

 Stator 5 inlet: 610.26 Stator 5 exit: 618.17 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.44 

Fan Bypass Relative Humidity 0.19 

LPC Inlet Relative Humidity 2.52 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 494.89 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 457.51 

Additional Water at LPC Exit 0.0010505 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 387.77 6807.3 0.6127 4171.04 5.2905 789.49 32.263 1.709 100.000 2922.2 2743.4 1912.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.77 4.267 477.92 -16.44 0.0000 1282.06 2.854 425.97 3911.3 0.7800 1.40068 0.0000851 387.74 0.033 0.0001

FS1 Inlet.Fl_O 387.77 4.267 477.92 -16.44 0.0000 1282.06 3.151 438.20 4168.2 0.6725 1.40068 0.0000851 387.74 0.033 0.0001

FS12 Splitter.Fl_02 326.13 4.265 477.92 -16.44 0.0000 1078.79 3.174 439.19 3531.8 0.6634 1.40068 0.0000851 326.10 0.028 0.0001

FS2 Splitter.Fl_01 61.64 4.265 477.92 -16.44 0.0000 203.91 3.661 457.51 830.5 0.4718 1.40068 0.0000851 61.64 0.005 0.0001

FS14 Fan.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS23 LPC.Fl_O 61.64 10.520 648.20 24.47 0.0000 96.27 9.203 623.99 412.6 0.4416 1.39756 0.0000851 61.64 0.005 0.0001

FS24 VaporIN.Fl_O 61.71 10.520 649.45 18.74 0.0000 96.47 9.195 625.06 412.6 0.4430 1.39737 0.0011356 61.64 0.070 0.0011

FS25 Bleed2.Fl_O 61.71 10.520 649.45 18.74 0.0000 96.47 9.195 625.06 412.6 0.4430 1.39737 0.0011356 61.64 0.070 0.0011

FS3 HPC.Fl_O 58.72 137.658 1428.86 214.09 0.0000 10.40 124.168 1390.75 49.7 0.3926 1.35413 0.0011356 58.65 0.067 0.0011

FS36 Bleed3.Fl_O 45.50 137.658 1428.86 214.09 0.0000 8.06 129.821 1407.11 49.3 0.2952 1.35413 0.0011356 45.45 0.052 0.0011

FS4 Burner.Fl_O 46.66 134.488 2922.17 182.01 0.0255 12.10 127.064 2885.43 74.6 0.3008 1.28077 0.0011356 45.45 0.052 0.0317

FS45 HPT.Fl_O 62.14 31.487 1921.74 -2.84 0.0190 55.83 28.365 1873.87 265.4 0.4007 1.31714 0.0011356 60.92 0.069 0.0241

FS49 LPT.Fl_O 62.87 7.253 1380.52 -148.68 0.0188 207.83 6.258 1329.20 860.2 0.4726 1.34395 0.0011356 61.64 0.070 0.0239

FS5 TEGV.Fl_O 62.87 7.253 1380.58 -148.68 0.0188 207.83 6.258 1329.26 860.2 0.4726 1.34394 0.0011356 61.64 0.070 0.0239

FS8 Core_Nozz.Fl_O 62.87 7.253 1380.71 -148.68 0.0188 207.84 3.883 1174.12 613.4 1.0000 1.34393 0.0011356 61.64 0.070 0.0239

FS17 FanDuctLkg.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS171 Bleed15.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS172 FanDuct.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS173 Byp_Nozz.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 3.833 469.91 2006.9 1.0000 1.39952 0.0000851 326.10 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.79 1.702 0.9114 4139.469 1.1801 0.9178 -9525.9 36.68 23.09

LPC 203.91 2.467 0.8251 4139.469 1.3563 0.8457 -3567.8 2.97 2.24

HPC 96.47 13.086 0.8585 10352.276 2.2001 0.8978 -16641.9 26.20 25.41

HPT 12.10 4.271 0.9122 214.295 1.3425 0.8903 16641.9 

LPT 55.83 4.341 0.9167 90.642 1.3885 0.9005 13093.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.45 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2221 0.8391 0.9892 0.0003

HPC 87.73 12.517 0.8674 10076.291 13.4793 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1806 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.513 0.9235 1.020 3.5132 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–25
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3911.32 9515.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.2709 1047.82 116.41 31.487

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7220 1047.82 116.41 7.253

TEGV 0.0000 0.4726 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1008.71 106.65 38.490

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1248.21 167.20 89.346

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1008.71 106.65 38.490

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1428.86 214.09 137.658

Splitter 5.2905 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1008.71 106.65 38.490

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11584.2 7545.2 16641.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 649.45 18.74 10.520

LP_Shaft 3973.5 17306.7 13093.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.0458 1428.86 214.09 134.488

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.1652 1428.86 214.09 75.571

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1428.86 214.09 137.658

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1428.86 214.09 137.658

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1428.86 214.09 137.658

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2922.17 0.9995 0.0230 1.15862 0.02549 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.541 0.9809 1.0000 0.9800 613.40 1.000 1620.9 3798.7

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1041.7 12523.7

NASA/TM—2013-218094 I–26
************************************************************************************************************************************ 

Date:05/13/13 Time:07:24:44 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 469.82 Stator 1 exit: 487.88 Stator 2 inlet: 509.30 Stator 2 exit: 517.60 

 Stator 3 inlet: 544.42 Stator 3 exit: 553.00 Stator 4 inlet: 578.30 Stator 4 exit: 586.27 

 Stator 5 inlet: 606.20 Stator 5 exit: 613.82 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.45 

Fan Bypass Relative Humidity 0.23 

LPC Inlet Relative Humidity 2.24 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 457.71 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.74 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 460.46 

Additional Water at LPC Exit 0.0011431 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 372.12 5898.4 0.6054 3571.07 5.4231 789.49 29.440 1.518 84.000 2764.0 2597.0 1805.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 372.12 4.267 477.92 -16.44 0.0000 1230.32 2.854 425.97 3753.5 0.7800 1.40068 0.0000851 372.09 0.032 0.0001

FS1 Inlet.Fl_O 372.12 4.267 477.92 -16.44 0.0000 1230.32 3.285 443.46 4168.2 0.6227 1.40068 0.0000851 372.09 0.032 0.0001

FS12 Splitter.Fl_02 314.19 4.265 477.92 -16.44 0.0000 1039.29 3.292 443.80 3531.8 0.6194 1.40068 0.0000851 314.16 0.027 0.0001

FS2 Splitter.Fl_01 57.93 4.265 477.92 -16.44 0.0000 191.64 3.744 460.46 830.5 0.4350 1.40068 0.0000851 57.93 0.005 0.0001

FS14 Fan.Fl_O 314.19 6.943 556.26 2.35 0.0000 688.65 5.764 527.45 2606.7 0.5226 1.39966 0.0000851 314.16 0.027 0.0001

FS23 LPC.Fl_O 57.93 10.389 640.38 22.58 0.0000 91.06 9.247 619.50 412.6 0.4115 1.39778 0.0000851 57.93 0.005 0.0001

FS24 VaporIN.Fl_O 58.00 10.389 641.75 16.35 0.0000 91.26 9.240 620.70 412.6 0.4129 1.39757 0.0012282 57.93 0.071 0.0012

FS25 Bleed2.Fl_O 58.00 10.389 641.75 16.35 0.0000 91.26 9.240 620.70 412.6 0.4129 1.39757 0.0012282 57.93 0.071 0.0012

FS3 HPC.Fl_O 55.19 125.614 1380.13 200.82 0.0000 10.53 112.958 1342.03 49.7 0.3981 1.35690 0.0012282 55.12 0.068 0.0012

FS36 Bleed3.Fl_O 42.77 125.614 1380.13 200.82 0.0000 8.16 118.273 1358.41 49.3 0.2990 1.35690 0.0012282 42.72 0.052 0.0012

FS4 Burner.Fl_O 43.76 122.721 2764.00 172.00 0.0232 12.10 115.930 2728.71 74.6 0.3000 1.28663 0.0012282 42.72 0.052 0.0291

FS45 HPT.Fl_O 58.31 28.642 1813.72 -3.22 0.0173 55.95 25.789 1767.73 265.4 0.4008 1.32277 0.0012282 57.25 0.070 0.0222

FS49 LPT.Fl_O 58.99 6.591 1298.42 -140.33 0.0171 208.13 5.684 1249.39 860.2 0.4722 1.34999 0.0012282 57.93 0.071 0.0219

FS5 TEGV.Fl_O 58.99 6.591 1298.49 -140.33 0.0171 208.13 5.684 1249.46 860.2 0.4722 1.34999 0.0012282 57.93 0.071 0.0220

FS8 Core_Nozz.Fl_O 58.99 6.591 1298.62 -140.33 0.0171 208.14 3.522 1101.53 613.4 1.0000 1.34998 0.0012282 57.93 0.071 0.0220

FS17 FanDuctLkg.Fl_O 314.19 6.943 556.26 2.35 0.0000 688.65 5.764 527.45 2606.7 0.5226 1.39966 0.0000851 314.16 0.027 0.0001

FS171 Bleed15.Fl_O 314.19 6.943 556.26 2.35 0.0000 688.65 5.601 523.15 2481.9 0.5626 1.39966 0.0000851 314.16 0.027 0.0001

FS172 FanDuct.Fl_O 314.19 6.943 556.26 2.35 0.0000 688.65 5.601 523.15 2481.9 0.5626 1.39966 0.0000851 314.16 0.027 0.0001

FS173 Byp_Nozz.Fl_O 314.19 6.943 556.26 2.35 0.0000 688.65 3.667 463.46 2006.9 1.0000 1.39966 0.0000851 314.16 0.027 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1039.29 1.628 0.9121 3983.460 1.1639 0.9179 -8353.4 51.66 26.14

LPC 191.64 2.436 0.8514 3983.460 1.3399 0.8687 -3198.7 2.91 2.10

HPC 91.26 12.091 0.8607 10183.487 2.1506 0.8985 -14771.2 29.85 28.84

HPT 12.10 4.285 0.9109 215.460 1.3487 0.8905 14771.3 

LPT 55.95 4.346 0.9148 89.786 1.3937 0.8982 11551.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1207.56 1.614 0.9139 3945.478 0.0614 0.8607 1.0235 0.9980 0.9905

LPC 152.44 2.576 0.8239 1.052 0.0000 1.2571 0.9113 1.0334 0.0003

HPC 83.00 11.569 0.8696 9912.002 13.1441 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.194 0.9109 1.295 4.1936 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.517 0.9216 1.010 3.5166 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–27
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3753.47 9131.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1344 1018.59 108.59 28.642

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6786 1018.59 108.59 6.591

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 981.54 99.36 35.738

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1208.63 156.55 81.828

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 981.54 99.36 35.738

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1380.13 200.82 125.614

Splitter 5.4231 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 981.54 99.36 35.738

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11327.5 6848.8 14771.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 641.75 16.35 10.389

LP_Shaft 3823.8 15866.9 11551.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.6225 1380.13 200.82 122.721

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7949 1380.13 200.82 68.908

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1380.13 200.82 125.614

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1380.13 200.82 125.614

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1380.13 200.82 125.614

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 556.26 2.35 6.943

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 556.26 2.35 6.943

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 556.26 2.35 6.943

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 556.26 2.35 6.943

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2763.99 0.9995 0.0230 0.99196 0.02322 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.309 0.9816 1.0000 0.9800 613.40 1.000 1573.5 3295.0

Byp_Nozz 2.433 0.9814 1.0000 0.9800 2006.86 1.000 1034.6 11734.5

NASA/TM—2013-218094 I–28
************************************************************************************************************************************ 

Date:05/13/13 Time:07:25:20 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 21/ 35/ 1/19 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 471.54 Stator 1 exit: 489.16 Stator 2 inlet: 510.24 Stator 2 exit: 518.67 

 Stator 3 inlet: 544.60 Stator 3 exit: 553.19 Stator 4 inlet: 577.67 Stator 4 exit: 585.60 

 Stator 5 inlet: 604.98 Stator 5 exit: 612.52 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.20 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 2.16 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 445.14 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.77 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 461.41 

Additional Water at LPC Exit 0.0011781 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 366.87 5602.3 0.6042 3385.05 5.4780 789.49 28.503 1.457 79.800 2713.8 2550.6 1771.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 366.87 4.267 477.92 -16.44 0.0000 1212.95 2.854 425.97 3700.5 0.7800 1.40068 0.0000851 366.84 0.031 0.0001

FS1 Inlet.Fl_O 366.87 4.267 477.92 -16.44 0.0000 1212.95 3.325 445.00 4168.2 0.6076 1.40068 0.0000851 366.84 0.031 0.0001

FS12 Splitter.Fl_02 310.23 4.265 477.92 -16.44 0.0000 1026.23 3.327 445.15 3531.8 0.6061 1.40068 0.0000851 310.21 0.026 0.0001

FS2 Splitter.Fl_01 56.63 4.265 477.92 -16.44 0.0000 187.34 3.771 461.41 830.5 0.4226 1.40068 0.0000851 56.63 0.005 0.0001

FS14 Fan.Fl_O 310.23 6.840 553.72 1.74 0.0000 688.65 5.678 525.04 2606.7 0.5226 1.39970 0.0000851 310.21 0.026 0.0001

FS23 LPC.Fl_O 56.63 10.331 638.03 22.02 0.0000 89.35 9.243 618.14 412.6 0.4020 1.39784 0.0000851 56.63 0.005 0.0001

FS24 VaporIN.Fl_O 56.70 10.331 639.45 15.59 0.0000 89.56 9.237 619.40 412.6 0.4033 1.39763 0.0012632 56.63 0.072 0.0013

FS25 Bleed2.Fl_O 56.70 10.331 639.45 15.59 0.0000 89.56 9.237 619.40 412.6 0.4033 1.39763 0.0012632 56.63 0.072 0.0013

FS3 HPC.Fl_O 53.95 121.614 1364.61 196.58 0.0000 10.57 109.247 1326.50 49.7 0.3999 1.35780 0.0012632 53.88 0.068 0.0013

FS36 Bleed3.Fl_O 41.81 121.614 1364.61 196.58 0.0000 8.20 114.444 1342.90 49.3 0.3002 1.35780 0.0012632 41.76 0.053 0.0013

FS4 Burner.Fl_O 42.75 118.813 2713.83 168.74 0.0225 12.10 112.236 2679.03 74.6 0.2998 1.28851 0.0012632 41.76 0.053 0.0283

FS45 HPT.Fl_O 56.98 27.704 1779.91 -3.36 0.0168 55.99 24.940 1734.52 265.4 0.4009 1.32460 0.0012632 55.97 0.071 0.0216

FS49 LPT.Fl_O 57.64 6.373 1272.88 -137.75 0.0166 208.23 5.495 1224.58 860.2 0.4722 1.35193 0.0012632 56.63 0.072 0.0214

FS5 TEGV.Fl_O 57.64 6.373 1272.94 -137.75 0.0166 208.24 5.495 1224.64 860.2 0.4722 1.35192 0.0012632 56.63 0.072 0.0214

FS8 Core_Nozz.Fl_O 57.64 6.373 1273.08 -137.74 0.0166 208.25 3.404 1079.01 613.4 1.0000 1.35191 0.0012632 56.63 0.072 0.0214

FS17 FanDuctLkg.Fl_O 310.23 6.840 553.72 1.74 0.0000 688.65 5.678 525.04 2606.7 0.5226 1.39970 0.0000851 310.21 0.026 0.0001

FS171 Bleed15.Fl_O 310.23 6.840 553.72 1.74 0.0000 688.65 5.518 520.76 2481.9 0.5626 1.39970 0.0000851 310.21 0.026 0.0001

FS172 FanDuct.Fl_O 310.23 6.840 553.72 1.74 0.0000 688.65 5.518 520.76 2481.9 0.5626 1.39970 0.0000851 310.21 0.026 0.0001

FS173 Byp_Nozz.Fl_O 310.23 6.840 553.72 1.74 0.0000 688.65 3.613 461.34 2006.9 1.0000 1.39970 0.0000851 310.21 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1026.23 1.604 0.9118 3934.513 1.1586 0.9175 -7980.7 56.27 27.19

LPC 187.34 2.422 0.8578 3934.513 1.3350 0.8742 -3081.4 3.23 2.49

HPC 89.56 11.772 0.8613 10135.831 2.1340 0.8987 -14166.9 31.13 30.01

HPT 12.10 4.289 0.9102 216.036 1.3505 0.8900 14167.0 

LPT 55.99 4.347 0.9141 89.521 1.3953 0.8974 11062.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1192.37 1.590 0.9136 3896.998 0.0606 0.8607 1.0235 0.9980 0.9905

LPC 149.06 2.525 0.8226 1.039 0.0000 1.2568 0.9328 1.0428 0.0003

HPC 81.45 11.265 0.8702 9865.617 13.0344 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.197 0.9102 1.298 4.1975 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.518 0.9208 1.007 3.5176 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–29
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3700.49 9002.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0865 1009.37 106.09 27.704

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6634 1009.37 106.09 6.373

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.97 97.04 34.813

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1196.05 153.14 79.326

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.97 97.04 34.813

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1364.61 196.58 121.614

Splitter 5.4780 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 972.97 97.04 34.813

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11254.3 6611.4 14167.0 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 639.45 15.59 10.331

LP_Shaft 3776.8 15383.2 11062.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4739 1364.61 196.58 118.813

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6648 1364.61 196.58 66.699

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1364.61 196.58 121.614

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1364.61 196.58 121.614

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1364.61 196.58 121.614

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.72 1.74 6.840

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.72 1.74 6.840

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.72 1.74 6.840

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.72 1.74 6.840

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2713.81 0.9995 0.0230 0.94029 0.02252 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.233 0.9816 1.0000 0.9800 613.40 1.000 1558.4 3129.1

Byp_Nozz 2.397 0.9814 1.0000 0.9800 2006.86 1.000 1032.2 11475.4

NASA/TM—2013-218094 I–30
************************************************************************************************************************************ 

Date:05/13/13 Time:07:25:54 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 472.72 Stator 1 exit: 490.05 Stator 2 inlet: 510.93 Stator 2 exit: 519.45 

 Stator 3 inlet: 544.81 Stator 3 exit: 553.41 Stator 4 inlet: 577.36 Stator 4 exit: 585.27 

 Stator 5 inlet: 604.30 Stator 5 exit: 611.78 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.03 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 2.10 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 436.14 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 462.07 

Additional Water at LPC Exit 0.0012042 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 363.04 5392.0 0.6042 3257.78 5.5193 789.49 27.840 1.415 76.800 2679.5 2518.9 1748.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.04 4.267 477.92 -16.44 0.0000 1200.29 2.854 425.97 3661.8 0.7800 1.40068 0.0000851 363.01 0.031 0.0001

FS1 Inlet.Fl_O 363.04 4.267 477.92 -16.44 0.0000 1200.29 3.353 446.07 4168.2 0.5969 1.40068 0.0000851 363.01 0.031 0.0001

FS12 Splitter.Fl_02 307.35 4.265 477.92 -16.44 0.0000 1016.68 3.352 446.10 3531.8 0.5966 1.40068 0.0000851 307.32 0.026 0.0001

FS2 Splitter.Fl_01 55.69 4.265 477.92 -16.44 0.0000 184.21 3.790 462.07 830.5 0.4138 1.40068 0.0000851 55.68 0.005 0.0001

FS14 Fan.Fl_O 307.35 6.766 551.94 1.31 0.0000 688.66 5.617 523.35 2606.7 0.5226 1.39972 0.0000851 307.32 0.026 0.0001

FS23 LPC.Fl_O 55.69 10.292 636.56 21.66 0.0000 88.09 9.244 617.38 412.6 0.3950 1.39788 0.0000851 55.68 0.005 0.0001

FS24 VaporIN.Fl_O 55.75 10.292 638.02 15.10 0.0000 88.29 9.237 618.67 412.6 0.3964 1.39767 0.0012893 55.68 0.072 0.0013

FS25 Bleed2.Fl_O 55.75 10.292 638.02 15.10 0.0000 88.29 9.237 618.67 412.6 0.3964 1.39767 0.0012893 55.68 0.072 0.0013

FS3 HPC.Fl_O 53.05 118.786 1354.04 193.69 0.0000 10.60 106.630 1315.93 49.7 0.4012 1.35842 0.0012893 52.98 0.068 0.0013

FS36 Bleed3.Fl_O 41.11 118.786 1354.04 193.69 0.0000 8.22 111.741 1332.36 49.3 0.3011 1.35842 0.0012893 41.06 0.053 0.0013

FS4 Burner.Fl_O 42.02 116.051 2679.48 166.52 0.0220 12.09 109.624 2645.03 74.6 0.2996 1.28980 0.0012893 41.06 0.053 0.0278

FS45 HPT.Fl_O 56.01 27.043 1756.83 -3.44 0.0164 56.01 24.342 1711.84 265.4 0.4009 1.32587 0.0012893 55.03 0.071 0.0212

FS49 LPT.Fl_O 56.66 6.219 1255.46 -135.96 0.0163 208.30 5.362 1207.66 860.2 0.4721 1.35326 0.0012893 55.68 0.072 0.0210

FS5 TEGV.Fl_O 56.66 6.219 1255.52 -135.96 0.0163 208.30 5.362 1207.72 860.2 0.4721 1.35325 0.0012893 55.68 0.072 0.0210

FS8 Core_Nozz.Fl_O 56.66 6.219 1255.66 -135.96 0.0163 208.31 3.321 1063.67 613.4 1.0000 1.35324 0.0012893 55.68 0.072 0.0210

FS17 FanDuctLkg.Fl_O 307.35 6.766 551.94 1.31 0.0000 688.66 5.617 523.35 2606.7 0.5226 1.39972 0.0000851 307.32 0.026 0.0001

FS171 Bleed15.Fl_O 307.35 6.766 551.94 1.31 0.0000 688.66 5.458 519.08 2481.9 0.5626 1.39972 0.0000851 307.32 0.026 0.0001

FS172 FanDuct.Fl_O 307.35 6.766 551.94 1.31 0.0000 688.66 5.458 519.08 2481.9 0.5626 1.39972 0.0000851 307.32 0.026 0.0001

FS173 Byp_Nozz.Fl_O 307.35 6.766 551.94 1.31 0.0000 688.66 3.573 459.86 2006.9 1.0000 1.39972 0.0000851 307.32 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1016.68 1.587 0.9106 3901.451 1.1549 0.9162 -7720.9 58.40 27.97

LPC 184.21 2.413 0.8616 3901.451 1.3319 0.8775 -3002.1 3.50 2.79

HPC 88.29 11.541 0.8614 10101.747 2.1223 0.8985 -13746.1 32.05 30.86

HPT 12.09 4.291 0.9097 216.442 1.3518 0.8898 13746.1 

LPT 56.01 4.348 0.9136 89.350 1.3964 0.8968 10723.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1181.29 1.573 0.9124 3864.251 0.0600 0.8607 1.0235 0.9980 0.9905

LPC 146.92 2.491 0.8219 1.030 0.0000 1.2537 0.9480 1.0483 0.0003

HPC 80.30 11.045 0.8703 9832.441 12.9566 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.200 0.9097 1.301 4.2001 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.518 0.9203 1.005 3.5184 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–31
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3661.85 8908.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0517 1003.16 104.39 27.043

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6523 1003.16 104.39 6.219

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 967.22 95.46 34.161

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1187.54 150.83 77.559 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 967.22 95.46 34.161

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1354.04 193.69 118.786

Splitter 5.5193 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 967.22 95.46 34.161

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11203.8 6443.9 13746.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 638.02 15.10 10.292

LP_Shaft 3745.1 15038.0 10723.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.3659 1354.04 193.69 116.051

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.5703 1354.04 193.69 65.139

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1354.04 193.69 118.786

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1354.04 193.69 118.786

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1354.04 193.69 118.786

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 551.94 1.31 6.766

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 551.94 1.31 6.766

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 551.94 1.31 6.766

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 551.94 1.31 6.766

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2679.46 0.9995 0.0230 0.90494 0.02204 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.179 0.9815 1.0000 0.9800 613.40 1.000 1547.9 3012.1

Byp_Nozz 2.371 0.9815 1.0000 0.9800 2006.86 1.000 1030.5 11288.0

NASA/TM—2013-218094 I–32
 25μm, ISA +18R

************************************************************************************************************************************ 

Date:05/13/13 Time:09:33:46 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 36/ 1/20 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 444.04 Stator 1 exit: 462.66 Stator 2 inlet: 484.20 Stator 2 exit: 491.28 

 Stator 3 inlet: 520.22 Stator 3 exit: 528.14 Stator 4 inlet: 555.22 Stator 4 exit: 562.91 

 Stator 5 inlet: 583.82 Stator 5 exit: 591.34 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.21 

Fan Bypass Relative Humidity 0.15 

LPC Inlet Relative Humidity 2.30 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 485.39 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 438.10 

Additional Water at LPC Exit 0.0000959 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 396.35 6795.2 0.5973 4059.07 5.2814 772.64 32.335 1.706 100.000 2814.3 2641.1 1834.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 396.35 4.267 457.74 -20.96 0.0000 1282.43 2.854 407.97 3912.3 0.7800 1.40084 0.0000295 396.34 0.012 0.0000

FS1 Inlet.Fl_O 396.35 4.267 457.74 -20.96 0.0000 1282.43 3.150 419.66 4168.2 0.6728 1.40084 0.0000295 396.34 0.012 0.0000

FS12 Splitter.Fl_02 333.25 4.265 457.74 -20.96 0.0000 1078.81 3.174 420.64 3531.8 0.6633 1.40084 0.0000295 333.24 0.010 0.0000

FS2 Splitter.Fl_01 63.10 4.265 457.74 -20.96 0.0000 204.27 3.659 438.10 830.5 0.4729 1.40084 0.0000295 63.10 0.002 0.0000

FS14 Fan.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS23 LPC.Fl_O 63.10 10.461 620.31 18.07 0.0000 96.94 9.130 596.71 412.6 0.4454 1.39831 0.0000295 63.10 0.002 0.0000

FS24 VaporIN.Fl_O 63.11 10.461 620.48 17.56 0.0000 96.96 9.129 596.86 412.6 0.4456 1.39830 0.0001254 63.10 0.008 0.0001

FS25 Bleed2.Fl_O 63.11 10.461 620.48 17.56 0.0000 96.96 9.129 596.86 412.6 0.4456 1.39830 0.0001254 63.10 0.008 0.0001

FS3 HPC.Fl_O 60.04 137.969 1373.28 205.18 0.0000 10.41 124.454 1336.42 49.7 0.3921 1.35748 0.0001254 60.04 0.008 0.0001

FS36 Bleed3.Fl_O 46.53 137.969 1373.28 205.18 0.0000 8.07 130.117 1352.21 49.3 0.2949 1.35748 0.0001254 46.53 0.006 0.0001

FS4 Burner.Fl_O 47.66 134.792 2814.27 174.94 0.0242 12.10 127.336 2778.54 74.6 0.3003 1.28478 0.0001254 46.53 0.006 0.0293

FS45 HPT.Fl_O 63.49 31.497 1843.73 -2.90 0.0181 55.86 28.373 1797.37 265.4 0.4001 1.32114 0.0001254 62.36 0.008 0.0220

FS49 LPT.Fl_O 64.23 7.237 1320.50 -142.50 0.0179 208.11 6.243 1270.87 860.2 0.4723 1.34829 0.0001254 63.10 0.008 0.0218

FS5 TEGV.Fl_O 64.23 7.237 1320.57 -142.50 0.0179 208.11 6.243 1270.93 860.2 0.4723 1.34829 0.0001254 63.10 0.008 0.0218

FS8 Core_Nozz.Fl_O 64.23 7.237 1320.70 -142.50 0.0179 208.12 3.870 1121.06 613.4 1.0000 1.34828 0.0001254 63.10 0.008 0.0218

FS17 FanDuctLkg.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS171 Bleed15.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS172 FanDuct.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS173 Byp_Nozz.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 3.833 450.06 2006.9 1.0000 1.39992 0.0000295 333.24 0.010 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.81 1.702 0.9114 4139.469 1.1801 0.9178 -9322.3 36.69 23.09

LPC 204.27 2.453 0.8226 4139.469 1.3552 0.8433 -3483.9 2.97 2.24

HPC 96.96 13.189 0.8584 10372.775 2.2133 0.8979 -16345.8 25.82 25.04

HPT 12.10 4.280 0.9118 213.860 1.3470 0.8911 16345.8 

LPT 55.86 4.352 0.9155 90.565 1.3927 0.8988 12806.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.47 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2243 0.8312 0.9862 0.0003

HPC 88.19 12.615 0.8672 10096.243 13.5168 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.189 0.9118 1.285 4.1886 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9223 1.019 3.5211 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–33
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3912.28 9518.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3223 1004.71 111.37 31.497

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7383 1004.71 111.37 7.237

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.92 101.99 38.513

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1198.47 160.15 89.516

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.92 101.99 38.513

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1373.28 205.18 137.969

Splitter 5.2814 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.92 101.99 38.513

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11345.2 7567.1 16345.8 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 620.48 17.56 10.461

LP_Shaft 3888.7 17295.7 12806.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.2053 1373.28 205.18 134.792

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.3048 1373.28 205.18 75.707

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.28 205.18 137.969

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.28 205.18 137.969

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.28 205.18 137.969

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2814.27 0.9995 0.0230 1.12752 0.02423 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.536 0.9809 1.0000 0.9800 613.40 1.000 1585.9 3789.3

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1019.5 12523.9

NASA/TM—2013-218094 I–34
************************************************************************************************************************************ 

Date:05/13/13 Time:09:34:22 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 450.19 Stator 1 exit: 467.34 Stator 2 inlet: 487.68 Stator 2 exit: 495.58 

 Stator 3 inlet: 521.05 Stator 3 exit: 529.20 Stator 4 inlet: 553.27 Stator 4 exit: 560.86 

 Stator 5 inlet: 579.84 Stator 5 exit: 587.09 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.12 

Fan Bypass Relative Humidity 0.18 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 445.56 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.75 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 441.19 

Additional Water at LPC Exit 0.0001101 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 378.74 5799.6 0.5904 3424.35 5.4253 772.64 29.236 1.498 84.000 2646.6 2486.1 1722.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 378.74 4.267 457.74 -20.96 0.0000 1225.45 2.854 407.97 3738.4 0.7800 1.40084 0.0000295 378.73 0.011 0.0000

FS1 Inlet.Fl_O 378.74 4.267 457.74 -20.96 0.0000 1225.45 3.296 425.15 4168.2 0.6183 1.40084 0.0000295 378.73 0.011 0.0000

FS12 Splitter.Fl_02 319.79 4.265 457.74 -20.96 0.0000 1035.24 3.303 425.46 3531.8 0.6151 1.40084 0.0000295 319.78 0.009 0.0000

FS2 Splitter.Fl_01 58.94 4.265 457.74 -20.96 0.0000 190.82 3.750 441.19 830.5 0.4326 1.40084 0.0000295 58.94 0.002 0.0000

FS14 Fan.Fl_O 319.79 6.912 532.08 -3.13 0.0000 688.70 5.737 504.50 2606.7 0.5226 1.40004 0.0000295 319.78 0.009 0.0000

FS23 LPC.Fl_O 58.94 10.333 612.28 16.14 0.0000 91.08 9.197 592.28 412.6 0.4115 1.39852 0.0000295 58.94 0.002 0.0000

FS24 VaporIN.Fl_O 58.95 10.333 612.46 15.55 0.0000 91.11 9.196 592.44 412.6 0.4117 1.39850 0.0001396 58.94 0.008 0.0001

FS25 Bleed2.Fl_O 58.95 10.333 612.46 15.55 0.0000 91.11 9.196 592.44 412.6 0.4117 1.39850 0.0001396 58.94 0.008 0.0001

FS3 HPC.Fl_O 56.09 124.744 1321.16 191.58 0.0000 10.55 112.151 1284.35 49.7 0.3980 1.36057 0.0001396 56.08 0.008 0.0001

FS36 Bleed3.Fl_O 43.47 124.744 1321.16 191.58 0.0000 8.17 117.438 1300.18 49.3 0.2989 1.36057 0.0001396 43.47 0.006 0.0001

FS4 Burner.Fl_O 44.42 121.871 2646.63 164.64 0.0219 12.10 115.114 2612.48 74.6 0.2995 1.29107 0.0001396 43.47 0.006 0.0265

FS45 HPT.Fl_O 59.21 28.387 1730.31 -2.86 0.0163 55.99 25.554 1685.89 265.4 0.4003 1.32733 0.0001396 58.25 0.008 0.0199

FS49 LPT.Fl_O 59.90 6.516 1234.74 -133.29 0.0161 208.46 5.617 1187.55 860.2 0.4721 1.35478 0.0001396 58.94 0.008 0.0197

FS5 TEGV.Fl_O 59.90 6.516 1234.81 -133.29 0.0161 208.46 5.617 1187.61 860.2 0.4721 1.35478 0.0001396 58.94 0.008 0.0197

FS8 Core_Nozz.Fl_O 59.90 6.516 1234.94 -133.29 0.0161 208.47 3.477 1045.47 613.4 1.0000 1.35477 0.0001396 58.94 0.008 0.0197

FS17 FanDuctLkg.Fl_O 319.79 6.912 532.08 -3.13 0.0000 688.70 5.737 504.50 2606.7 0.5226 1.40004 0.0000295 319.78 0.009 0.0000

FS171 Bleed15.Fl_O 319.79 6.912 532.08 -3.13 0.0000 688.70 5.575 500.39 2481.9 0.5625 1.40004 0.0000295 319.78 0.009 0.0000

FS172 FanDuct.Fl_O 319.79 6.912 532.08 -3.13 0.0000 688.70 5.575 500.39 2481.9 0.5625 1.40004 0.0000295 319.78 0.009 0.0000

FS173 Byp_Nozz.Fl_O 319.79 6.912 532.08 -3.13 0.0000 688.70 3.650 443.28 2006.9 1.0000 1.40004 0.0000295 319.78 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1035.24 1.621 0.9117 3968.903 1.1624 0.9175 -8064.3 53.03 26.46

LPC 190.82 2.423 0.8521 3968.903 1.3376 0.8692 -3093.4 2.96 2.15

HPC 91.11 12.072 0.8607 10179.543 2.1571 0.8986 -14326.3 29.85 28.83

HPT 12.10 4.293 0.9099 215.019 1.3534 0.8903 14326.3 

LPT 55.99 4.357 0.9131 89.634 1.3983 0.8961 11157.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1202.85 1.606 0.9135 3931.060 0.0611 0.8607 1.0235 0.9980 0.9905

LPC 151.28 2.560 0.8233 1.048 0.0000 1.2613 0.9120 1.0350 0.0003

HPC 82.86 11.550 0.8696 9908.163 13.1455 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.202 0.9099 1.292 4.2020 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9199 1.008 3.5246 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–35
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3738.44 9095.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1694 973.60 103.56 28.387

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6897 973.60 103.56 6.516

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 938.03 94.76 35.504

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1156.20 149.33 81.268

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 938.03 94.76 35.504

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1321.16 191.58 124.744

Splitter 5.4253 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 938.03 94.76 35.504

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11061.7 6802.1 14326.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.46 15.55 10.333

LP_Shaft 3728.5 15717.2 11157.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.7311 1321.16 191.58 121.871

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.8898 1321.16 191.58 68.398

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1321.16 191.58 124.744

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1321.16 191.58 124.744

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1321.16 191.58 124.744

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.912

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.912

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.912

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.912

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2646.61 0.9995 0.0230 0.95121 0.02188 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.283 0.9816 1.0000 0.9800 613.40 1.000 1534.9 3240.2

Byp_Nozz 2.422 0.9814 1.0000 0.9800 2006.86 1.000 1011.8 11654.5

NASA/TM—2013-218094 I–36
************************************************************************************************************************************ 

Date:05/13/13 Time:09:34:58 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 451.81 Stator 1 exit: 468.55 Stator 2 inlet: 488.59 Stator 2 exit: 496.62 

 Stator 3 inlet: 521.26 Stator 3 exit: 529.43 Stator 4 inlet: 552.74 Stator 4 exit: 560.29 

 Stator 5 inlet: 578.76 Stator 5 exit: 585.94 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.88 

Fan Bypass Relative Humidity 0.20 

LPC Inlet Relative Humidity 1.93 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 433.38 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.78 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.09 

Additional Water at LPC Exit 0.0001148 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 373.42 5508.1 0.5896 3247.58 5.4804 772.64 28.311 1.439 79.800 2598.9 2441.9 1690.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 373.42 4.267 457.74 -20.96 0.0000 1208.25 2.854 407.97 3686.0 0.7800 1.40084 0.0000295 373.41 0.011 0.0000

FS1 Inlet.Fl_O 373.42 4.267 457.74 -20.96 0.0000 1208.25 3.335 426.59 4168.2 0.6035 1.40084 0.0000295 373.41 0.011 0.0000

FS12 Splitter.Fl_02 315.80 4.265 457.74 -20.96 0.0000 1022.31 3.338 426.73 3531.8 0.6021 1.40084 0.0000295 315.79 0.009 0.0000

FS2 Splitter.Fl_01 57.62 4.265 457.74 -20.96 0.0000 186.54 3.776 442.09 830.5 0.4203 1.40084 0.0000295 57.62 0.002 0.0000

FS14 Fan.Fl_O 315.80 6.810 529.66 -3.71 0.0000 688.70 5.653 502.21 2606.7 0.5226 1.40008 0.0000295 315.79 0.009 0.0000

FS23 LPC.Fl_O 57.62 10.280 610.14 15.62 0.0000 89.34 9.199 591.11 412.6 0.4018 1.39857 0.0000295 57.62 0.002 0.0000

FS24 VaporIN.Fl_O 57.63 10.280 610.33 15.01 0.0000 89.37 9.198 591.27 412.6 0.4020 1.39854 0.0001442 57.62 0.008 0.0001

FS25 Bleed2.Fl_O 57.63 10.280 610.33 15.01 0.0000 89.37 9.198 591.27 412.6 0.4020 1.39854 0.0001442 57.62 0.008 0.0001

FS3 HPC.Fl_O 54.83 120.797 1306.23 187.69 0.0000 10.59 108.497 1269.44 49.7 0.3997 1.36147 0.0001442 54.83 0.008 0.0001

FS36 Bleed3.Fl_O 42.50 120.797 1306.23 187.69 0.0000 8.20 113.666 1285.28 49.3 0.3001 1.36147 0.0001442 42.49 0.006 0.0001

FS4 Burner.Fl_O 43.40 118.015 2598.87 161.65 0.0212 12.10 111.472 2565.18 74.6 0.2992 1.29288 0.0001442 42.49 0.006 0.0258

FS45 HPT.Fl_O 57.86 27.464 1698.37 -2.84 0.0158 56.02 24.721 1654.56 265.4 0.4003 1.32915 0.0001442 56.95 0.008 0.0194

FS49 LPT.Fl_O 58.53 6.302 1210.77 -130.68 0.0157 208.54 5.433 1164.29 860.2 0.4720 1.35661 0.0001442 57.62 0.008 0.0192

FS5 TEGV.Fl_O 58.53 6.302 1210.83 -130.68 0.0157 208.54 5.433 1164.35 860.2 0.4720 1.35660 0.0001442 57.62 0.008 0.0192

FS8 Core_Nozz.Fl_O 58.53 6.302 1210.97 -130.68 0.0157 208.55 3.362 1024.42 613.4 1.0000 1.35659 0.0001442 57.62 0.008 0.0192

FS17 FanDuctLkg.Fl_O 315.80 6.810 529.66 -3.71 0.0000 688.70 5.653 502.21 2606.7 0.5226 1.40008 0.0000295 315.79 0.009 0.0000

FS171 Bleed15.Fl_O 315.80 6.810 529.66 -3.71 0.0000 688.70 5.493 498.11 2481.9 0.5625 1.40008 0.0000295 315.79 0.009 0.0000

FS172 FanDuct.Fl_O 315.80 6.810 529.66 -3.71 0.0000 688.70 5.493 498.11 2481.9 0.5625 1.40008 0.0000295 315.79 0.009 0.0000

FS173 Byp_Nozz.Fl_O 315.80 6.810 529.66 -3.71 0.0000 688.70 3.596 441.26 2006.9 1.0000 1.40008 0.0000295 315.79 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1022.31 1.597 0.9114 3920.858 1.1571 0.9170 -7704.5 57.15 27.51

LPC 186.54 2.411 0.8584 3920.858 1.3329 0.8747 -2982.0 3.34 2.63

HPC 89.37 11.750 0.8613 10131.152 2.1402 0.8988 -13739.2 31.12 29.99

HPT 12.10 4.297 0.9091 215.577 1.3551 0.8897 13739.2 

LPT 56.02 4.358 0.9123 89.378 1.3998 0.8952 10686.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1187.83 1.583 0.9132 3883.473 0.0603 0.8607 1.0235 0.9980 0.9905

LPC 148.17 2.511 0.8223 1.036 0.0000 1.2589 0.9336 1.0439 0.0003

HPC 81.28 11.244 0.8702 9861.062 13.0364 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9090 1.296 4.2057 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9191 1.005 3.5256 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–37
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3685.97 8967.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1208 964.77 101.35 27.464

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6743 964.77 101.35 6.302

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.84 92.72 34.594

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1144.14 146.25 78.801

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.84 92.72 34.594

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1306.23 187.69 120.797

Splitter 5.4804 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.84 92.72 34.594

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10989.9 6566.0 13739.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 610.33 15.01 10.280

LP_Shaft 3683.4 15237.7 10686.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.5802 1306.23 187.69 118.015

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7578 1306.23 187.69 66.220

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.23 187.69 120.797

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.23 187.69 120.797

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.23 187.69 120.797

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2598.85 0.9995 0.0230 0.90211 0.02123 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.208 0.9816 1.0000 0.9800 613.40 1.000 1520.3 3077.2

Byp_Nozz 2.386 0.9815 1.0000 0.9800 2006.86 1.000 1009.5 11398.4

NASA/TM—2013-218094 I–38
************************************************************************************************************************************ 

Date:05/13/13 Time:09:35:32 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 452.90 Stator 1 exit: 469.37 Stator 2 inlet: 489.22 Stator 2 exit: 497.33 

 Stator 3 inlet: 521.44 Stator 3 exit: 529.62 Stator 4 inlet: 552.42 Stator 4 exit: 559.96 

 Stator 5 inlet: 578.10 Stator 5 exit: 585.24 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.72 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 1.88 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 424.73 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.70 

Additional Water at LPC Exit 0.0001183 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 369.50 5301.1 0.5900 3127.72 5.5201 772.64 27.662 1.398 76.800 2566.5 2412.0 1669.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 369.50 4.267 457.74 -20.96 0.0000 1195.58 2.854 407.97 3647.3 0.7800 1.40084 0.0000295 369.49 0.011 0.0000

FS1 Inlet.Fl_O 369.50 4.267 457.74 -20.96 0.0000 1195.58 3.363 427.60 4168.2 0.5930 1.40084 0.0000295 369.49 0.011 0.0000

FS12 Splitter.Fl_02 312.83 4.265 457.74 -20.96 0.0000 1012.72 3.362 427.62 3531.8 0.5927 1.40084 0.0000295 312.82 0.009 0.0000

FS2 Splitter.Fl_01 56.67 4.265 457.74 -20.96 0.0000 183.46 3.795 442.70 830.5 0.4116 1.40084 0.0000295 56.67 0.002 0.0000

FS14 Fan.Fl_O 312.83 6.735 528.02 -4.11 0.0000 688.70 5.591 500.65 2606.7 0.5226 1.40010 0.0000295 312.82 0.009 0.0000

FS23 LPC.Fl_O 56.67 10.241 608.73 15.28 0.0000 88.10 9.198 590.37 412.6 0.3950 1.39860 0.0000295 56.67 0.002 0.0000

FS24 VaporIN.Fl_O 56.68 10.241 608.93 14.65 0.0000 88.12 9.197 590.54 412.6 0.3951 1.39858 0.0001478 56.67 0.008 0.0001

FS25 Bleed2.Fl_O 56.68 10.241 608.93 14.65 0.0000 88.12 9.197 590.54 412.6 0.3951 1.39858 0.0001478 56.67 0.008 0.0001

FS3 HPC.Fl_O 53.93 118.028 1296.17 185.07 0.0000 10.62 105.936 1259.37 49.7 0.4009 1.36209 0.0001478 53.92 0.008 0.0001

FS36 Bleed3.Fl_O 41.79 118.028 1296.17 185.07 0.0000 8.23 111.020 1275.22 49.3 0.3009 1.36209 0.0001478 41.79 0.006 0.0001

FS4 Burner.Fl_O 42.66 115.310 2566.49 159.63 0.0208 12.10 108.915 2533.12 74.6 0.2990 1.29413 0.0001478 41.79 0.006 0.0252

FS45 HPT.Fl_O 56.88 26.819 1676.79 -2.82 0.0155 56.05 24.137 1633.37 265.4 0.4003 1.33040 0.0001478 56.01 0.008 0.0190

FS49 LPT.Fl_O 57.55 6.153 1194.61 -128.91 0.0153 208.59 5.304 1148.61 860.2 0.4719 1.35785 0.0001478 56.67 0.008 0.0188

FS5 TEGV.Fl_O 57.55 6.153 1194.67 -128.91 0.0153 208.60 5.304 1148.67 860.2 0.4719 1.35784 0.0001478 56.67 0.008 0.0188

FS8 Core_Nozz.Fl_O 57.55 6.153 1194.81 -128.91 0.0153 208.61 3.281 1010.25 613.4 1.0000 1.35783 0.0001478 56.67 0.008 0.0188

FS17 FanDuctLkg.Fl_O 312.83 6.735 528.02 -4.11 0.0000 688.70 5.591 500.65 2606.7 0.5226 1.40010 0.0000295 312.82 0.009 0.0000

FS171 Bleed15.Fl_O 312.83 6.735 528.02 -4.11 0.0000 688.70 5.433 496.56 2481.9 0.5625 1.40010 0.0000295 312.82 0.009 0.0000

FS172 FanDuct.Fl_O 312.83 6.735 528.02 -4.11 0.0000 688.70 5.433 496.56 2481.9 0.5625 1.40010 0.0000295 312.82 0.009 0.0000

FS173 Byp_Nozz.Fl_O 312.83 6.735 528.02 -4.11 0.0000 688.70 3.557 439.89 2006.9 1.0000 1.40010 0.0000295 312.82 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1012.72 1.579 0.9094 3888.172 1.1535 0.9150 -7457.2 59.28 28.29

LPC 183.46 2.401 0.8622 3888.172 1.3299 0.8780 -2905.6 3.61 2.87

HPC 88.12 11.525 0.8614 10097.708 2.1286 0.8986 -13335.0 32.02 30.82

HPT 12.10 4.300 0.9085 215.968 1.3562 0.8892 13335.1 

LPT 56.05 4.359 0.9118 89.201 1.4008 0.8945 10362.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1176.68 1.566 0.9112 3851.098 0.0597 0.8607 1.0235 0.9980 0.9905

LPC 146.06 2.477 0.8217 1.027 0.0000 1.2561 0.9487 1.0493 0.0003

HPC 80.15 11.029 0.8703 9828.510 12.9606 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.208 0.9085 1.298 4.2081 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9186 1.003 3.5261 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–39
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3647.32 8873.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0857 958.84 99.86 26.819

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6631 958.84 99.86 6.153

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.34 91.34 33.954

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1136.00 144.17 77.069

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.34 91.34 33.954

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1296.17 185.07 118.028

Splitter 5.5201 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.34 91.34 33.954

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10941.1 6401.3 13335.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 608.93 14.65 10.241

LP_Shaft 3652.7 14900.5 10362.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4715 1296.17 185.07 115.310

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6627 1296.17 185.07 64.693

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1296.17 185.07 118.028

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1296.17 185.07 118.028

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1296.17 185.07 118.028

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 528.02 -4.11 6.735

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 528.02 -4.11 6.735

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 528.02 -4.11 6.735

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 528.02 -4.11 6.735

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2566.47 0.9995 0.0230 0.86881 0.02079 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.156 0.9815 1.0000 0.9800 613.40 1.000 1510.4 2963.3

Byp_Nozz 2.360 0.9815 1.0000 0.9800 2006.86 1.000 1007.9 11211.2

NASA/TM—2013-218094 I–40
 25μm, ISA +36R

************************************************************************************************************************************ 

Date:05/13/13 Time:10:02:43 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 25/ 53/ 2/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 463.74 Stator 1 exit: 483.21 Stator 2 inlet: 505.74 Stator 2 exit: 513.20 

 Stator 3 inlet: 543.41 Stator 3 exit: 551.73 Stator 4 inlet: 579.99 Stator 4 exit: 588.05 

 Stator 5 inlet: 609.88 Stator 5 exit: 617.77 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.44 

Fan Bypass Relative Humidity 0.19 

LPC Inlet Relative Humidity 2.52 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 495.61 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 457.45 

Additional Water at LPC Exit 0.0001483 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 387.84 6803.9 0.6131 4171.48 5.2846 789.49 32.270 1.709 100.000 2922.3 2743.4 1912.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.84 4.267 477.92 -16.44 0.0000 1282.29 2.854 425.97 3912.0 0.7800 1.40068 0.0000851 387.81 0.033 0.0001

FS1 Inlet.Fl_O 387.84 4.267 477.92 -16.44 0.0000 1282.29 3.150 438.18 4168.2 0.6727 1.40068 0.0000851 387.81 0.033 0.0001

FS12 Splitter.Fl_02 326.13 4.265 477.92 -16.44 0.0000 1078.79 3.174 439.19 3531.8 0.6634 1.40068 0.0000851 326.10 0.028 0.0001

FS2 Splitter.Fl_01 61.71 4.265 477.92 -16.44 0.0000 204.14 3.660 457.45 830.5 0.4725 1.40068 0.0000851 61.71 0.005 0.0001

FS14 Fan.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS23 LPC.Fl_O 61.71 10.484 647.79 24.37 0.0000 96.67 9.159 623.34 412.6 0.4440 1.39757 0.0000851 61.71 0.005 0.0001

FS24 VaporIN.Fl_O 61.72 10.484 648.03 23.57 0.0000 96.70 9.158 623.54 412.6 0.4442 1.39754 0.0002334 61.71 0.014 0.0002

FS25 Bleed2.Fl_O 61.72 10.484 648.03 23.57 0.0000 96.70 9.158 623.54 412.6 0.4442 1.39754 0.0002334 61.71 0.014 0.0002

FS3 HPC.Fl_O 58.73 137.687 1427.73 218.81 0.0000 10.40 124.213 1389.70 49.7 0.3923 1.35435 0.0002334 58.71 0.014 0.0002

FS36 Bleed3.Fl_O 45.51 137.687 1427.73 218.81 0.0000 8.06 129.858 1406.02 49.3 0.2950 1.35435 0.0002334 45.50 0.011 0.0002

FS4 Burner.Fl_O 46.67 134.516 2922.28 186.59 0.0255 12.10 127.093 2885.54 74.6 0.3007 1.28094 0.0002334 45.50 0.011 0.0308

FS45 HPT.Fl_O 62.16 31.489 1921.32 1.89 0.0190 55.83 28.368 1873.47 265.4 0.4006 1.31730 0.0002334 60.99 0.014 0.0232

FS49 LPT.Fl_O 62.88 7.250 1379.92 -143.86 0.0188 207.91 6.255 1328.59 860.2 0.4726 1.34411 0.0002334 61.71 0.014 0.0230

FS5 TEGV.Fl_O 62.88 7.250 1379.98 -143.86 0.0188 207.91 6.255 1328.65 860.2 0.4726 1.34411 0.0002334 61.71 0.014 0.0230

FS8 Core_Nozz.Fl_O 62.88 7.250 1380.11 -143.86 0.0188 207.92 3.882 1173.53 613.4 1.0000 1.34410 0.0002334 61.71 0.014 0.0230

FS17 FanDuctLkg.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS171 Bleed15.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS172 FanDuct.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS173 Byp_Nozz.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 3.833 469.91 2006.9 1.0000 1.39952 0.0000851 326.10 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.79 1.702 0.9114 4139.469 1.1801 0.9178 -9525.9 36.68 23.09

LPC 204.14 2.458 0.8236 4139.469 1.3554 0.8443 -3563.2 2.97 2.24

HPC 96.70 13.133 0.8585 10361.858 2.2032 0.8978 -16636.2 26.04 25.26

HPT 12.10 4.272 0.9122 214.253 1.3427 0.8903 16636.3 

LPT 55.83 4.343 0.9167 90.652 1.3888 0.9005 13088.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.45 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2236 0.8344 0.9874 0.0003

HPC 87.95 12.561 0.8673 10085.617 13.4951 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1812 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.515 0.9235 1.020 3.5146 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–41
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3912.02 9516.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.2714 1046.53 121.19 31.489

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7221 1046.53 121.19 7.250

TEGV 0.0000 0.4726 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.41 111.43 38.469

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1247.01 171.95 89.350

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.41 111.43 38.469

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1427.73 218.81 137.687

Splitter 5.2846 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.41 111.43 38.469

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11582.1 7544.0 16636.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 648.03 23.57 10.484

LP_Shaft 3973.5 17300.5 13088.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.0474 1427.73 218.81 134.516

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.1667 1427.73 218.81 75.584

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.73 218.81 137.687

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.73 218.81 137.687

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.73 218.81 137.687

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2922.28 0.9995 0.0230 1.15874 0.02546 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.540 0.9809 1.0000 0.9800 613.40 1.000 1620.2 3797.0

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1041.7 12523.6

NASA/TM—2013-218094 I–42
************************************************************************************************************************************ 

Date:05/13/13 Time:10:03:19 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 469.62 Stator 1 exit: 487.66 Stator 2 inlet: 509.01 Stator 2 exit: 517.25 

 Stator 3 inlet: 544.09 Stator 3 exit: 552.62 Stator 4 inlet: 577.97 Stator 4 exit: 585.92 

 Stator 5 inlet: 605.89 Stator 5 exit: 613.49 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.44 

Fan Bypass Relative Humidity 0.23 

LPC Inlet Relative Humidity 2.25 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 458.48 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.74 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 460.40 

Additional Water at LPC Exit 0.0001661 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 372.14 5892.0 0.6058 3569.54 5.4147 789.49 29.444 1.518 84.000 2763.0 2595.9 1804.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 372.14 4.267 477.92 -16.44 0.0000 1230.39 2.854 425.97 3753.7 0.7800 1.40068 0.0000851 372.11 0.032 0.0001

FS1 Inlet.Fl_O 372.14 4.267 477.92 -16.44 0.0000 1230.39 3.285 443.45 4168.2 0.6228 1.40068 0.0000851 372.11 0.032 0.0001

FS12 Splitter.Fl_02 314.13 4.265 477.92 -16.44 0.0000 1039.10 3.292 443.82 3531.8 0.6192 1.40068 0.0000851 314.10 0.027 0.0001

FS2 Splitter.Fl_01 58.01 4.265 477.92 -16.44 0.0000 191.90 3.743 460.40 830.5 0.4357 1.40068 0.0000851 58.01 0.005 0.0001

FS14 Fan.Fl_O 314.13 6.942 556.22 2.34 0.0000 688.65 5.763 527.42 2606.7 0.5226 1.39966 0.0000851 314.10 0.027 0.0001

FS23 LPC.Fl_O 58.01 10.359 639.99 22.49 0.0000 91.42 9.210 618.92 412.6 0.4135 1.39779 0.0000851 58.01 0.005 0.0001

FS24 VaporIN.Fl_O 58.02 10.359 640.24 21.59 0.0000 91.45 9.209 619.14 412.6 0.4138 1.39776 0.0002511 58.01 0.015 0.0003

FS25 Bleed2.Fl_O 58.02 10.359 640.24 21.59 0.0000 91.45 9.209 619.14 412.6 0.4138 1.39776 0.0002511 58.01 0.015 0.0003

FS3 HPC.Fl_O 55.21 125.630 1378.62 205.87 0.0000 10.53 112.990 1340.59 49.7 0.3978 1.35715 0.0002511 55.20 0.014 0.0003

FS36 Bleed3.Fl_O 42.79 125.630 1378.62 205.87 0.0000 8.16 118.298 1356.94 49.3 0.2988 1.35715 0.0002511 42.78 0.011 0.0003

FS4 Burner.Fl_O 43.78 122.737 2762.97 176.94 0.0232 12.10 115.948 2727.69 74.6 0.2999 1.28685 0.0002511 42.78 0.011 0.0282

FS45 HPT.Fl_O 58.34 28.643 1812.51 1.94 0.0173 55.95 25.790 1766.55 265.4 0.4007 1.32298 0.0002511 57.33 0.014 0.0212

FS49 LPT.Fl_O 59.01 6.588 1297.24 -135.02 0.0171 208.21 5.681 1248.22 860.2 0.4722 1.35022 0.0002511 58.01 0.015 0.0210

FS5 TEGV.Fl_O 59.01 6.588 1297.30 -135.02 0.0171 208.21 5.681 1248.28 860.2 0.4723 1.35021 0.0002511 58.01 0.015 0.0210

FS8 Core_Nozz.Fl_O 59.01 6.588 1297.43 -135.02 0.0171 208.22 3.521 1100.42 613.4 1.0000 1.35020 0.0002511 58.01 0.015 0.0210

FS17 FanDuctLkg.Fl_O 314.13 6.942 556.22 2.34 0.0000 688.65 5.763 527.42 2606.7 0.5226 1.39966 0.0000851 314.10 0.027 0.0001

FS171 Bleed15.Fl_O 314.13 6.942 556.22 2.34 0.0000 688.65 5.600 523.12 2481.9 0.5626 1.39966 0.0000851 314.10 0.027 0.0001 

FS172 FanDuct.Fl_O 314.13 6.942 556.22 2.34 0.0000 688.65 5.600 523.12 2481.9 0.5626 1.39966 0.0000851 314.10 0.027 0.0001

FS173 Byp_Nozz.Fl_O 314.13 6.942 556.22 2.34 0.0000 688.65 3.666 463.44 2006.9 1.0000 1.39966 0.0000851 314.10 0.027 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1039.10 1.628 0.9121 3982.795 1.1638 0.9179 -8348.2 51.72 26.15

LPC 191.90 2.429 0.8504 3982.795 1.3391 0.8677 -3195.2 2.91 2.10

HPC 91.45 12.127 0.8606 10188.703 2.1533 0.8985 -14761.5 29.71 28.71

HPT 12.10 4.285 0.9109 215.356 1.3490 0.8905 14761.6 

LPT 55.95 4.348 0.9147 89.801 1.3941 0.8982 11543.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1207.34 1.613 0.9139 3944.819 0.0614 0.8607 1.0235 0.9980 0.9905

LPC 152.38 2.575 0.8239 1.052 0.0000 1.2593 0.9073 1.0322 0.0003

HPC 83.17 11.603 0.8695 9917.079 13.1570 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.194 0.9109 1.294 4.1941 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.518 0.9215 1.010 3.5181 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–43
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3753.69 9131.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1353 1017.06 113.73 28.643

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6789 1017.06 113.73 6.588

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 980.01 104.52 35.719

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1207.11 161.65 81.827

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 980.01 104.52 35.719

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1378.62 205.87 125.630

Splitter 5.4147 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 980.01 104.52 35.719

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11319.9 6848.9 14761.6 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 640.24 21.59 10.359

LP_Shaft 3823.1 15857.9 11543.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.6251 1378.62 205.87 122.737

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7971 1378.62 205.87 68.915

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.62 205.87 125.630

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.62 205.87 125.630

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.62 205.87 125.630

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2762.96 0.9995 0.0230 0.99154 0.02318 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.308 0.9816 1.0000 0.9800 613.40 1.000 1572.3 3292.9

Byp_Nozz 2.432 0.9814 1.0000 0.9800 2006.86 1.000 1034.5 11730.7

NASA/TM—2013-218094 I–44
************************************************************************************************************************************ 

Date:05/13/13 Time:10:03:55 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 471.34 Stator 1 exit: 488.94 Stator 2 inlet: 509.96 Stator 2 exit: 518.33 

 Stator 3 inlet: 544.28 Stator 3 exit: 552.83 Stator 4 inlet: 577.35 Stator 4 exit: 585.26 

 Stator 5 inlet: 604.69 Stator 5 exit: 612.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.19 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 2.16 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 445.95 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.77 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 461.35 

Additional Water at LPC Exit 0.0001730 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 366.89 5595.6 0.6046 3383.12 5.4687 789.49 28.508 1.457 79.800 2712.4 2549.2 1770.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 366.89 4.267 477.92 -16.44 0.0000 1213.02 2.854 425.97 3700.7 0.7800 1.40068 0.0000851 366.85 0.031 0.0001

FS1 Inlet.Fl_O 366.89 4.267 477.92 -16.44 0.0000 1213.02 3.325 444.99 4168.2 0.6076 1.40068 0.0000851 366.85 0.031 0.0001

FS12 Splitter.Fl_02 310.17 4.265 477.92 -16.44 0.0000 1026.01 3.328 445.17 3531.8 0.6058 1.40068 0.0000851 310.14 0.026 0.0001

FS2 Splitter.Fl_01 56.72 4.265 477.92 -16.44 0.0000 187.62 3.770 461.35 830.5 0.4234 1.40068 0.0000851 56.71 0.005 0.0001

FS14 Fan.Fl_O 310.17 6.839 553.68 1.73 0.0000 688.65 5.677 525.00 2606.7 0.5226 1.39970 0.0000851 310.14 0.026 0.0001

FS23 LPC.Fl_O 56.72 10.303 637.63 21.92 0.0000 89.70 9.209 617.57 412.6 0.4039 1.39785 0.0000851 56.71 0.005 0.0001

FS24 VaporIN.Fl_O 56.73 10.303 637.89 20.99 0.0000 89.73 9.208 617.81 412.6 0.4041 1.39782 0.0002581 56.71 0.015 0.0003

FS25 Bleed2.Fl_O 56.73 10.303 637.89 20.99 0.0000 89.73 9.208 617.81 412.6 0.4041 1.39782 0.0002581 56.71 0.015 0.0003

FS3 HPC.Fl_O 53.98 121.635 1362.94 201.75 0.0000 10.57 109.284 1324.91 49.7 0.3996 1.35806 0.0002581 53.96 0.014 0.0003

FS36 Bleed3.Fl_O 41.83 121.635 1362.94 201.75 0.0000 8.19 114.474 1341.28 49.3 0.3000 1.35806 0.0002581 41.82 0.011 0.0003

FS4 Burner.Fl_O 42.77 118.833 2712.39 173.82 0.0225 12.10 112.259 2677.61 74.6 0.2996 1.28875 0.0002581 41.82 0.011 0.0273

FS45 HPT.Fl_O 57.00 27.706 1778.43 1.96 0.0168 55.99 24.943 1733.08 265.4 0.4007 1.32483 0.0002581 56.05 0.014 0.0206

FS49 LPT.Fl_O 57.67 6.370 1271.48 -132.25 0.0166 208.30 5.493 1223.20 860.2 0.4722 1.35217 0.0002581 56.71 0.015 0.0204

FS5 TEGV.Fl_O 57.67 6.370 1271.54 -132.25 0.0166 208.31 5.493 1223.27 860.2 0.4722 1.35217 0.0002581 56.71 0.015 0.0204

FS8 Core_Nozz.Fl_O 57.67 6.370 1271.67 -132.25 0.0166 208.32 3.402 1077.71 613.4 1.0000 1.35216 0.0002581 56.71 0.015 0.0204

FS17 FanDuctLkg.Fl_O 310.17 6.839 553.68 1.73 0.0000 688.65 5.677 525.00 2606.7 0.5226 1.39970 0.0000851 310.14 0.026 0.0001

FS171 Bleed15.Fl_O 310.17 6.839 553.68 1.73 0.0000 688.65 5.517 520.72 2481.9 0.5626 1.39970 0.0000851 310.14 0.026 0.0001

FS172 FanDuct.Fl_O 310.17 6.839 553.68 1.73 0.0000 688.65 5.517 520.72 2481.9 0.5626 1.39970 0.0000851 310.14 0.026 0.0001

FS173 Byp_Nozz.Fl_O 310.17 6.839 553.68 1.73 0.0000 688.65 3.612 461.31 2006.9 1.0000 1.39970 0.0000851 310.14 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1026.01 1.604 0.9117 3933.757 1.1585 0.9174 -7974.7 56.32 27.21

LPC 187.62 2.416 0.8570 3933.757 1.3342 0.8735 -3078.3 3.23 2.50

HPC 89.73 11.805 0.8612 10140.735 2.1366 0.8987 -14156.4 30.99 29.88 

HPT 12.10 4.289 0.9102 215.934 1.3508 0.8900 14156.4 

LPT 55.99 4.349 0.9140 89.541 1.3957 0.8973 11053.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1192.12 1.590 0.9136 3896.249 0.0606 0.8607 1.0235 0.9980 0.9905

LPC 149.01 2.524 0.8226 1.039 0.0000 1.2591 0.9291 1.0419 0.0003

HPC 81.61 11.296 0.8702 9870.389 13.0466 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.198 0.9102 1.298 4.1980 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.519 0.9208 1.007 3.5192 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–45
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3700.68 9002.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0876 1007.74 111.37 27.706

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6637 1007.74 111.37 6.370

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.35 102.33 34.796

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1194.40 158.37 79.329

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.35 102.33 34.796

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1362.94 201.75 121.635

Splitter 5.4687 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.35 102.33 34.796

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11246.0 6611.3 14156.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.89 20.99 10.303

LP_Shaft 3776.1 15373.6 11053.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4771 1362.94 201.75 118.833

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6676 1362.94 201.75 66.708

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.94 201.75 121.635

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.94 201.75 121.635

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.94 201.75 121.635

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.68 1.73 6.839

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.68 1.73 6.839

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.68 1.73 6.839

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.68 1.73 6.839

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2712.37 0.9995 0.0230 0.93976 0.02247 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.232 0.9816 1.0000 0.9800 613.40 1.000 1557.1 3127.1

Byp_Nozz 2.396 0.9814 1.0000 0.9800 2006.86 1.000 1032.2 11471.1

NASA/TM—2013-218094 I–46
************************************************************************************************************************************ 

Date:05/13/13 Time:10:04:30 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 472.53 Stator 1 exit: 489.84 Stator 2 inlet: 510.66 Stator 2 exit: 519.13 

 Stator 3 inlet: 544.50 Stator 3 exit: 553.07 Stator 4 inlet: 577.06 Stator 4 exit: 584.95 

 Stator 5 inlet: 604.02 Stator 5 exit: 611.50 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.03 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 2.11 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 436.97 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 462.01 

Additional Water at LPC Exit 0.0001782 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 363.05 5385.0 0.6045 3255.09 5.5094 789.49 27.844 1.415 76.800 2677.6 2517.0 1747.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.05 4.267 477.92 -16.44 0.0000 1200.33 2.854 425.97 3662.0 0.7800 1.40068 0.0000851 363.02 0.031 0.0001

FS1 Inlet.Fl_O 363.05 4.267 477.92 -16.44 0.0000 1200.33 3.353 446.06 4168.2 0.5970 1.40068 0.0000851 363.02 0.031 0.0001

FS12 Splitter.Fl_02 307.28 4.265 477.92 -16.44 0.0000 1016.44 3.352 446.12 3531.8 0.5964 1.40068 0.0000851 307.25 0.026 0.0001

FS2 Splitter.Fl_01 55.77 4.265 477.92 -16.44 0.0000 184.49 3.789 462.01 830.5 0.4146 1.40068 0.0000851 55.77 0.005 0.0001

FS14 Fan.Fl_O 307.28 6.764 551.90 1.30 0.0000 688.66 5.615 523.31 2606.7 0.5226 1.39973 0.0000851 307.25 0.026 0.0001

FS23 LPC.Fl_O 55.77 10.268 636.19 21.57 0.0000 88.41 9.213 616.85 412.6 0.3968 1.39789 0.0000851 55.77 0.005 0.0001

FS24 VaporIN.Fl_O 55.78 10.268 636.45 20.61 0.0000 88.44 9.212 617.09 412.6 0.3970 1.39786 0.0002632 55.77 0.015 0.0003

FS25 Bleed2.Fl_O 55.78 10.268 636.45 20.61 0.0000 88.44 9.212 617.09 412.6 0.3970 1.39786 0.0002632 55.77 0.015 0.0003

FS3 HPC.Fl_O 53.08 118.804 1352.21 198.94 0.0000 10.60 106.663 1314.18 49.7 0.4009 1.35869 0.0002632 53.06 0.014 0.0003

FS36 Bleed3.Fl_O 41.14 118.804 1352.21 198.94 0.0000 8.22 111.766 1330.57 49.3 0.3009 1.35869 0.0002632 41.12 0.011 0.0003

FS4 Burner.Fl_O 42.04 116.068 2677.57 171.67 0.0220 12.09 109.644 2643.14 74.6 0.2994 1.29006 0.0002632 41.12 0.011 0.0268

FS45 HPT.Fl_O 56.03 27.046 1755.32 2.00 0.0164 56.01 24.346 1710.38 265.4 0.4007 1.32611 0.0002632 55.12 0.015 0.0202

FS49 LPT.Fl_O 56.69 6.217 1254.04 -130.35 0.0162 208.37 5.360 1206.27 860.2 0.4721 1.35350 0.0002632 55.77 0.015 0.0199

FS5 TEGV.Fl_O 56.69 6.217 1254.11 -130.35 0.0162 208.38 5.360 1206.33 860.2 0.4721 1.35350 0.0002632 55.77 0.015 0.0199

FS8 Core_Nozz.Fl_O 56.69 6.217 1254.24 -130.35 0.0162 208.39 3.319 1062.36 613.4 1.0000 1.35349 0.0002632 55.77 0.015 0.0199

FS17 FanDuctLkg.Fl_O 307.28 6.764 551.90 1.30 0.0000 688.66 5.615 523.31 2606.7 0.5226 1.39973 0.0000851 307.25 0.026 0.0001

FS171 Bleed15.Fl_O 307.28 6.764 551.90 1.30 0.0000 688.66 5.456 519.04 2481.9 0.5626 1.39973 0.0000851 307.25 0.026 0.0001

FS172 FanDuct.Fl_O 307.28 6.764 551.90 1.30 0.0000 688.66 5.456 519.04 2481.9 0.5626 1.39973 0.0000851 307.25 0.026 0.0001

FS173 Byp_Nozz.Fl_O 307.28 6.764 551.90 1.30 0.0000 688.66 3.572 459.82 2006.9 1.0000 1.39973 0.0000851 307.25 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1016.44 1.586 0.9105 3900.605 1.1548 0.9162 -7714.3 58.46 27.99

LPC 184.49 2.408 0.8610 3900.605 1.3312 0.8770 -2999.6 3.51 2.79

HPC 88.44 11.570 0.8614 10105.824 2.1246 0.8985 -13733.0 31.92 30.74

HPT 12.09 4.291 0.9097 216.341 1.3518 0.8892 13733.0 

LPT 56.01 4.351 0.9135 89.369 1.3968 0.8967 10714.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1181.00 1.573 0.9124 3863.413 0.0599 0.8607 1.0235 0.9980 0.9905

LPC 146.87 2.490 0.8219 1.030 0.0000 1.2562 0.9448 1.0476 0.0003

HPC 80.44 11.072 0.8703 9836.410 12.9676 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.200 0.9097 1.300 4.2003 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9203 1.005 3.5201 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–47
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3661.98 8908.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0528 1001.43 109.77 27.046

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6527 1001.43 109.77 6.217

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.51 100.86 34.146

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1185.75 156.14 77.560

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.51 100.86 34.146

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1352.21 198.94 118.804

Splitter 5.5094 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.51 100.86 34.146

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11194.6 6443.1 13733.0 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 636.45 20.61 10.268

LP_Shaft 3744.2 15029.0 10714.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.3693 1352.21 198.94 116.068

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.5733 1352.21 198.94 65.147

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1352.21 198.94 118.804

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1352.21 198.94 118.804

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1352.21 198.94 118.804

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 551.90 1.30 6.764

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 551.90 1.30 6.764

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 551.90 1.30 6.764

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 551.90 1.30 6.764

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2677.55 0.9995 0.0230 0.90419 0.02199 

 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.178 0.9815 1.0000 0.9800 613.40 1.000 1546.6 3010.3

Byp_Nozz 2.370 0.9815 1.0000 0.9800 2006.86 1.000 1030.5 11283.2

NASA/TM—2013-218094 I–48
 50μm, ISA +18R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:24:24 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 38/ 1/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 444.03 Stator 1 exit: 462.65 Stator 2 inlet: 484.18 Stator 2 exit: 491.25 

 Stator 3 inlet: 520.20 Stator 3 exit: 528.10 Stator 4 inlet: 555.20 Stator 4 exit: 562.88 

 Stator 5 inlet: 583.79 Stator 5 exit: 591.31 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.21 

Fan Bypass Relative Humidity 0.15 

LPC Inlet Relative Humidity 2.30 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 485.44 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 438.10 

Additional Water at LPC Exit 0.0000220 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 396.35 6795.0 0.5974 4059.25 5.2809 772.64 32.336 1.706 100.000 2814.3 2641.2 1834.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 396.35 4.267 457.74 -20.96 0.0000 1282.45 2.854 407.97 3912.3 0.7800 1.40084 0.0000295 396.34 0.012 0.0000

FS1 Inlet.Fl_O 396.35 4.267 457.74 -20.96 0.0000 1282.45 3.150 419.66 4168.2 0.6728 1.40084 0.0000295 396.34 0.012 0.0000

FS12 Splitter.Fl_02 333.25 4.265 457.74 -20.96 0.0000 1078.81 3.174 420.64 3531.8 0.6633 1.40084 0.0000295 333.24 0.010 0.0000

FS2 Splitter.Fl_01 63.10 4.265 457.74 -20.96 0.0000 204.28 3.659 438.10 830.5 0.4729 1.40084 0.0000295 63.10 0.002 0.0000

FS14 Fan.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS23 LPC.Fl_O 63.10 10.457 620.27 18.06 0.0000 96.98 9.125 596.65 412.6 0.4457 1.39831 0.0000295 63.10 0.002 0.0000

FS24 VaporIN.Fl_O 63.11 10.457 620.35 17.95 0.0000 96.99 9.125 596.72 412.6 0.4457 1.39831 0.0000515 63.10 0.003 0.0001

FS25 Bleed2.Fl_O 63.11 10.457 620.35 17.95 0.0000 96.99 9.125 596.72 412.6 0.4457 1.39831 0.0000515 63.10 0.003 0.0001

FS3 HPC.Fl_O 60.04 137.970 1373.20 205.57 0.0000 10.41 124.457 1336.34 49.7 0.3921 1.35749 0.0000515 60.04 0.003 0.0001

FS36 Bleed3.Fl_O 46.53 137.970 1373.20 205.57 0.0000 8.07 130.119 1352.13 49.3 0.2948 1.35749 0.0000515 46.53 0.002 0.0001

FS4 Burner.Fl_O 47.66 134.793 2814.34 175.32 0.0242 12.10 127.337 2778.61 74.6 0.3003 1.28479 0.0000515 46.53 0.002 0.0292

FS45 HPT.Fl_O 63.49 31.497 1843.74 -2.52 0.0181 55.86 28.373 1797.37 265.4 0.4001 1.32115 0.0000515 62.36 0.003 0.0219

FS49 LPT.Fl_O 64.23 7.238 1320.50 -142.11 0.0179 208.11 6.243 1270.87 860.2 0.4723 1.34830 0.0000515 63.10 0.003 0.0217

FS5 TEGV.Fl_O 64.23 7.238 1320.57 -142.11 0.0179 208.11 6.243 1270.93 860.2 0.4723 1.34830 0.0000515 63.10 0.003 0.0217

FS8 Core_Nozz.Fl_O 64.23 7.238 1320.70 -142.11 0.0179 208.12 3.870 1121.05 613.4 1.0000 1.34829 0.0000515 63.10 0.003 0.0217

FS17 FanDuctLkg.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS171 Bleed15.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS172 FanDuct.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS173 Byp_Nozz.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 3.833 450.06 2006.9 1.0000 1.39992 0.0000295 333.24 0.010 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.81 1.702 0.9114 4139.469 1.1801 0.9178 -9322.3 36.69 23.09

LPC 204.28 2.452 0.8224 4139.469 1.3551 0.8432 -3483.4 2.97 2.24

HPC 96.99 13.194 0.8584 10373.799 2.2136 0.8979 -16345.6 25.80 25.03

HPT 12.10 4.280 0.9118 213.857 1.3470 0.8911 16345.5 

LPT 55.86 4.352 0.9155 90.565 1.3927 0.8988 12805.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.47 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2245 0.8307 0.9860 0.0003

HPC 88.21 12.619 0.8672 10097.240 13.5185 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.189 0.9118 1.285 4.1887 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9223 1.019 3.5210 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–49
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3912.33 9518.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3223 1004.61 111.76 31.497

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7383 1004.61 111.76 7.238

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.82 102.38 38.510

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1198.38 160.54 89.515

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.82 102.38 38.510

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1373.20 205.57 137.970

Splitter 5.2809 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.82 102.38 38.510

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11345.2 7567.0 16345.5 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 620.35 17.95 10.457

LP_Shaft 3888.7 17295.0 12805.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.2054 1373.20 205.57 134.793

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.3049 1373.20 205.57 75.708

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.20 205.57 137.970

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.20 205.57 137.970

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.20 205.57 137.970

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2814.34 0.9995 0.0230 1.12757 0.02423 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.536 0.9809 1.0000 0.9800 613.40 1.000 1585.8 3789.3

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1019.5 12523.9

NASA/TM—2013-218094 I–50
************************************************************************************************************************************ 

Date:07/05/13 Time:09:25:02 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 34/ 1/18 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 450.18 Stator 1 exit: 467.32 Stator 2 inlet: 487.66 Stator 2 exit: 495.55 

 Stator 3 inlet: 521.02 Stator 3 exit: 529.17 Stator 4 inlet: 553.24 Stator 4 exit: 560.82 

 Stator 5 inlet: 579.81 Stator 5 exit: 587.06 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.12 

Fan Bypass Relative Humidity 0.18 

LPC Inlet Relative Humidity 2.01 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 445.62 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.75 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 441.19 

Additional Water at LPC Exit 0.0000241 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 378.74 5799.1 0.5905 3424.22 5.4245 772.64 29.237 1.498 84.000 2646.5 2486.0 1722.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 378.74 4.267 457.74 -20.96 0.0000 1225.45 2.854 407.97 3738.5 0.7800 1.40084 0.0000295 378.73 0.011 0.0000

FS1 Inlet.Fl_O 378.74 4.267 457.74 -20.96 0.0000 1225.45 3.296 425.15 4168.2 0.6183 1.40084 0.0000295 378.73 0.011 0.0000

FS12 Splitter.Fl_02 319.79 4.265 457.74 -20.96 0.0000 1035.22 3.303 425.46 3531.8 0.6151 1.40084 0.0000295 319.78 0.009 0.0000

FS2 Splitter.Fl_01 58.95 4.265 457.74 -20.96 0.0000 190.84 3.750 441.19 830.5 0.4326 1.40084 0.0000295 58.95 0.002 0.0000

FS14 Fan.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.737 504.50 2606.7 0.5226 1.40004 0.0000295 319.78 0.009 0.0000

FS23 LPC.Fl_O 58.95 10.331 612.25 16.13 0.0000 91.11 9.194 592.23 412.6 0.4117 1.39852 0.0000295 58.95 0.002 0.0000

FS24 VaporIN.Fl_O 58.95 10.331 612.33 16.01 0.0000 91.12 9.194 592.31 412.6 0.4117 1.39851 0.0000535 58.95 0.003 0.0001

FS25 Bleed2.Fl_O 58.95 10.331 612.33 16.01 0.0000 91.12 9.194 592.31 412.6 0.4117 1.39851 0.0000535 58.95 0.003 0.0001

FS3 HPC.Fl_O 56.09 124.751 1321.02 192.02 0.0000 10.55 112.160 1284.22 49.7 0.3980 1.36059 0.0000535 56.09 0.003 0.0001

FS36 Bleed3.Fl_O 43.47 124.751 1321.02 192.02 0.0000 8.17 117.446 1300.04 49.3 0.2989 1.36059 0.0000535 43.47 0.002 0.0001

FS4 Burner.Fl_O 44.42 121.878 2646.52 165.07 0.0219 12.10 115.121 2612.38 74.6 0.2995 1.29109 0.0000535 43.47 0.002 0.0264

FS45 HPT.Fl_O 59.22 28.388 1730.19 -2.41 0.0163 55.99 25.556 1685.78 265.4 0.4003 1.32734 0.0000535 58.26 0.003 0.0199

FS49 LPT.Fl_O 59.90 6.516 1234.63 -132.82 0.0161 208.45 5.618 1187.45 860.2 0.4721 1.35480 0.0000535 58.95 0.003 0.0196

FS5 TEGV.Fl_O 59.90 6.516 1234.70 -132.82 0.0161 208.46 5.618 1187.51 860.2 0.4721 1.35480 0.0000535 58.95 0.003 0.0196

FS8 Core_Nozz.Fl_O 59.90 6.516 1234.83 -132.82 0.0161 208.47 3.477 1045.37 613.4 1.0000 1.35479 0.0000535 58.95 0.003 0.0196

FS17 FanDuctLkg.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.737 504.50 2606.7 0.5226 1.40004 0.0000295 319.78 0.009 0.0000

FS171 Bleed15.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.575 500.38 2481.9 0.5625 1.40004 0.0000295 319.78 0.009 0.0000

FS172 FanDuct.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.575 500.38 2481.9 0.5625 1.40004 0.0000295 319.78 0.009 0.0000

FS173 Byp_Nozz.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 3.650 443.27 2006.9 1.0000 1.40004 0.0000295 319.78 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1035.22 1.621 0.9117 3968.836 1.1624 0.9175 -8063.8 53.03 26.46

LPC 190.84 2.422 0.8520 3968.836 1.3376 0.8691 -3093.1 2.96 2.16

HPC 91.12 12.075 0.8607 10180.008 2.1574 0.8986 -14325.4 29.83 28.82

HPT 12.10 4.293 0.9099 215.009 1.3534 0.8903 14325.4 

LPT 55.99 4.357 0.9131 89.635 1.3983 0.8961 11156.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1202.83 1.606 0.9135 3930.994 0.0611 0.8607 1.0235 0.9980 0.9905

LPC 151.27 2.560 0.8233 1.048 0.0000 1.2616 0.9117 1.0349 0.0003

HPC 82.87 11.553 0.8696 9908.615 13.1467 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.202 0.9099 1.292 4.2020 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9199 1.008 3.5247 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–51
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3738.46 9095.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1695 973.46 104.02 28.388

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6898 973.46 104.02 6.516

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 937.89 95.22 35.503

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1156.06 149.78 81.271

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 937.89 95.22 35.503

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1321.02 192.02 124.751

Splitter 5.4245 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 937.89 95.22 35.503

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11061.0 6802.1 14325.4 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.33 16.01 10.331

LP_Shaft 3728.4 15716.3 11156.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.7313 1321.02 192.02 121.878

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.8901 1321.02 192.02 68.402

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1321.02 192.02 124.751

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1321.02 192.02 124.751

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1321.02 192.02 124.751

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2646.51 0.9995 0.0230 0.95117 0.02188 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.283 0.9816 1.0000 0.9800 613.40 1.000 1534.8 3240.1

Byp_Nozz 2.422 0.9814 1.0000 0.9800 2006.86 1.000 1011.8 11654.2

NASA/TM—2013-218094 I–52
************************************************************************************************************************************ 

Date:07/05/13 Time:09:25:38 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 451.80 Stator 1 exit: 468.53 Stator 2 inlet: 488.56 Stator 2 exit: 496.59 

 Stator 3 inlet: 521.23 Stator 3 exit: 529.40 Stator 4 inlet: 552.71 Stator 4 exit: 560.26 

 Stator 5 inlet: 578.73 Stator 5 exit: 585.91 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.88 

Fan Bypass Relative Humidity 0.20 

LPC Inlet Relative Humidity 1.93 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 433.45 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.78 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.08 

Additional Water at LPC Exit 0.0000248 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 373.42 5507.5 0.5896 3247.43 5.4795 772.64 28.311 1.439 79.800 2598.7 2441.8 1690.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 373.42 4.267 457.74 -20.96 0.0000 1208.25 2.854 407.97 3686.0 0.7800 1.40084 0.0000295 373.41 0.011 0.0000

FS1 Inlet.Fl_O 373.42 4.267 457.74 -20.96 0.0000 1208.25 3.335 426.59 4168.2 0.6035 1.40084 0.0000295 373.41 0.011 0.0000

FS12 Splitter.Fl_02 315.79 4.265 457.74 -20.96 0.0000 1022.29 3.338 426.73 3531.8 0.6021 1.40084 0.0000295 315.78 0.009 0.0000

FS2 Splitter.Fl_01 57.63 4.265 457.74 -20.96 0.0000 186.57 3.776 442.08 830.5 0.4204 1.40084 0.0000295 57.63 0.002 0.0000

FS14 Fan.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.653 502.21 2606.7 0.5226 1.40008 0.0000295 315.78 0.009 0.0000

FS23 LPC.Fl_O 57.63 10.278 610.11 15.61 0.0000 89.37 9.196 591.06 412.6 0.4020 1.39857 0.0000295 57.63 0.002 0.0000

FS24 VaporIN.Fl_O 57.63 10.278 610.19 15.49 0.0000 89.38 9.195 591.13 412.6 0.4020 1.39856 0.0000543 57.63 0.003 0.0001

FS25 Bleed2.Fl_O 57.63 10.278 610.19 15.49 0.0000 89.38 9.195 591.13 412.6 0.4020 1.39856 0.0000543 57.63 0.003 0.0001

FS3 HPC.Fl_O 54.84 120.799 1306.08 188.16 0.0000 10.59 108.500 1269.30 49.7 0.3997 1.36150 0.0000543 54.83 0.003 0.0001

FS36 Bleed3.Fl_O 42.50 120.799 1306.08 188.16 0.0000 8.20 113.669 1285.13 49.3 0.3000 1.36150 0.0000543 42.50 0.002 0.0001

FS4 Burner.Fl_O 43.40 118.017 2598.74 162.11 0.0212 12.10 111.475 2565.05 74.6 0.2992 1.29291 0.0000543 42.50 0.002 0.0257

FS45 HPT.Fl_O 57.86 27.465 1698.24 -2.37 0.0158 56.02 24.721 1654.44 265.4 0.4003 1.32917 0.0000543 56.96 0.003 0.0193

FS49 LPT.Fl_O 58.53 6.302 1210.65 -130.19 0.0157 208.54 5.433 1164.17 860.2 0.4720 1.35663 0.0000543 57.63 0.003 0.0191

FS5 TEGV.Fl_O 58.53 6.302 1210.71 -130.19 0.0157 208.55 5.433 1164.23 860.2 0.4720 1.35662 0.0000543 57.63 0.003 0.0191

FS8 Core_Nozz.Fl_O 58.53 6.302 1210.85 -130.19 0.0157 208.56 3.362 1024.31 613.4 1.0000 1.35661 0.0000543 57.63 0.003 0.0191

FS17 FanDuctLkg.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.653 502.21 2606.7 0.5226 1.40008 0.0000295 315.78 0.009 0.0000

FS171 Bleed15.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.493 498.11 2481.9 0.5625 1.40008 0.0000295 315.78 0.009 0.0000

FS172 FanDuct.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.493 498.11 2481.9 0.5625 1.40008 0.0000295 315.78 0.009 0.0000

FS173 Byp_Nozz.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 3.596 441.26 2006.9 1.0000 1.40008 0.0000295 315.78 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1022.29 1.597 0.9114 3920.781 1.1571 0.9170 -7703.9 57.15 27.51

LPC 186.57 2.410 0.8583 3920.781 1.3329 0.8746 -2981.8 3.34 2.63

HPC 89.38 11.753 0.8613 10131.613 2.1405 0.8988 -13738.3 31.11 29.98

HPT 12.10 4.297 0.9091 215.567 1.3551 0.8897 13738.3 

LPT 56.02 4.358 0.9123 89.379 1.3998 0.8952 10685.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1187.80 1.583 0.9132 3883.396 0.0603 0.8607 1.0235 0.9980 0.9905

LPC 148.17 2.511 0.8223 1.036 0.0000 1.2591 0.9333 1.0438 0.0003

HPC 81.29 11.247 0.8702 9861.511 13.0375 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9090 1.296 4.2057 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9191 1.005 3.5257 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–53
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3685.98 8967.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1209 964.62 101.82 27.465

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6743 964.62 101.82 6.302

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.70 93.19 34.593

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1143.99 146.72 78.801 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.70 93.19 34.593

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1306.08 188.16 120.799

Splitter 5.4795 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.70 93.19 34.593

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10989.2 6566.0 13738.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 610.19 15.49 10.278

LP_Shaft 3683.3 15236.9 10685.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.5805 1306.08 188.16 118.017

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7581 1306.08 188.16 66.221

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.08 188.16 120.799

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.08 188.16 120.799

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.08 188.16 120.799

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2598.72 0.9995 0.0230 0.90206 0.02123 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.208 0.9816 1.0000 0.9800 613.40 1.000 1520.2 3077.0

Byp_Nozz 2.386 0.9815 1.0000 0.9800 2006.86 1.000 1009.5 11397.9

NASA/TM—2013-218094 I–54
************************************************************************************************************************************ 

Date:07/05/13 Time:09:26:12 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 452.89 Stator 1 exit: 469.36 Stator 2 inlet: 489.20 Stator 2 exit: 497.31 

 Stator 3 inlet: 521.41 Stator 3 exit: 529.59 Stator 4 inlet: 552.40 Stator 4 exit: 559.93 

 Stator 5 inlet: 578.07 Stator 5 exit: 585.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.72 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 1.88 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 424.80 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.70 

Additional Water at LPC Exit 0.0000254 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 369.51 5300.3 0.5901 3127.57 5.5192 772.64 27.660 1.397 76.800 2566.4 2411.8 1669.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 369.51 4.267 457.74 -20.96 0.0000 1195.58 2.854 407.97 3647.3 0.7800 1.40084 0.0000295 369.49 0.011 0.0000

FS1 Inlet.Fl_O 369.51 4.267 457.74 -20.96 0.0000 1195.58 3.363 427.59 4168.2 0.5930 1.40084 0.0000295 369.49 0.011 0.0000

FS12 Splitter.Fl_02 312.83 4.265 457.74 -20.96 0.0000 1012.69 3.362 427.62 3531.8 0.5927 1.40084 0.0000295 312.82 0.009 0.0000

FS2 Splitter.Fl_01 56.68 4.265 457.74 -20.96 0.0000 183.48 3.795 442.70 830.5 0.4117 1.40084 0.0000295 56.68 0.002 0.0000

FS14 Fan.Fl_O 312.83 6.735 528.01 -4.11 0.0000 688.70 5.591 500.64 2606.7 0.5226 1.40010 0.0000295 312.82 0.009 0.0000

FS23 LPC.Fl_O 56.68 10.238 608.70 15.27 0.0000 88.14 9.193 590.31 412.6 0.3952 1.39860 0.0000295 56.68 0.002 0.0000

FS24 VaporIN.Fl_O 56.68 10.238 608.78 15.15 0.0000 88.15 9.193 590.38 412.6 0.3953 1.39859 0.0000549 56.68 0.003 0.0001

FS25 Bleed2.Fl_O 56.68 10.238 608.78 15.15 0.0000 88.15 9.193 590.38 412.6 0.3953 1.39859 0.0000549 56.68 0.003 0.0001

FS3 HPC.Fl_O 53.93 118.020 1296.01 185.55 0.0000 10.62 105.929 1259.22 49.7 0.4009 1.36211 0.0000549 53.93 0.003 0.0001

FS36 Bleed3.Fl_O 41.80 118.020 1296.01 185.55 0.0000 8.23 111.013 1275.06 49.3 0.3009 1.36211 0.0000549 41.79 0.002 0.0001

FS4 Burner.Fl_O 42.67 115.302 2566.36 160.10 0.0208 12.10 108.907 2532.99 74.6 0.2990 1.29415 0.0000549 41.79 0.002 0.0252

FS45 HPT.Fl_O 56.89 26.817 1676.65 -2.33 0.0155 56.05 24.135 1633.23 265.4 0.4003 1.33042 0.0000549 56.01 0.003 0.0189

FS49 LPT.Fl_O 57.55 6.152 1194.48 -128.41 0.0153 208.62 5.303 1148.48 860.2 0.4719 1.35787 0.0000549 56.68 0.003 0.0187

FS5 TEGV.Fl_O 57.55 6.152 1194.55 -128.41 0.0153 208.62 5.303 1148.54 860.2 0.4719 1.35786 0.0000549 56.68 0.003 0.0187

FS8 Core_Nozz.Fl_O 57.55 6.152 1194.68 -128.40 0.0153 208.63 3.280 1010.13 613.4 1.0000 1.35785 0.0000549 56.68 0.003 0.0187

FS17 FanDuctLkg.Fl_O 312.83 6.735 528.01 -4.11 0.0000 688.70 5.591 500.64 2606.7 0.5226 1.40010 0.0000295 312.82 0.009 0.0000

FS171 Bleed15.Fl_O 312.83 6.735 528.01 -4.11 0.0000 688.70 5.433 496.56 2481.9 0.5625 1.40010 0.0000295 312.82 0.009 0.0000

FS172 FanDuct.Fl_O 312.83 6.735 528.01 -4.11 0.0000 688.70 5.433 496.56 2481.9 0.5625 1.40010 0.0000295 312.82 0.009 0.0000

FS173 Byp_Nozz.Fl_O 312.83 6.735 528.01 -4.11 0.0000 688.70 3.557 439.88 2006.9 1.0000 1.40010 0.0000295 312.82 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1012.69 1.579 0.9094 3888.090 1.1535 0.9150 -7456.6 59.29 28.29

LPC 183.48 2.401 0.8620 3888.090 1.3298 0.8778 -2905.3 3.61 2.87

HPC 88.15 11.528 0.8614 10098.210 2.1289 0.8986 -13334.1 32.00 30.80

HPT 12.10 4.300 0.9085 215.958 1.3562 0.8892 13334.1 

LPT 56.05 4.359 0.9118 89.203 1.4008 0.8945 10362.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1176.65 1.566 0.9112 3851.017 0.0597 0.8607 1.0235 0.9980 0.9905

LPC 146.06 2.477 0.8217 1.027 0.0000 1.2562 0.9482 1.0491 0.0003

HPC 80.17 11.032 0.8703 9828.998 12.9618 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.208 0.9085 1.298 4.2082 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9185 1.003 3.5263 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–55
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3647.33 8873.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0858 958.68 100.35 26.817

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6632 958.68 100.35 6.152

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.19 91.83 33.950

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1135.85 144.65 77.063

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.19 91.83 33.950

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1296.01 185.55 118.020

Splitter 5.5192 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.19 91.83 33.950

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10940.3 6401.3 13334.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 608.78 15.15 10.238

LP_Shaft 3652.6 14899.6 10362.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4718 1296.01 185.55 115.302

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6630 1296.01 185.55 64.689

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1296.01 185.55 118.020

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1296.01 185.55 118.020

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1296.01 185.55 118.020

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2566.34 0.9995 0.0230 0.86877 0.02079 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.156 0.9815 1.0000 0.9800 613.40 1.000 1510.3 2963.0

Byp_Nozz 2.360 0.9815 1.0000 0.9800 2006.86 1.000 1007.9 11210.7

NASA/TM—2013-218094 I–56
 50μm, ISA +36R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:35:17 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 36/ 1/20 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 463.71 Stator 1 exit: 483.18 Stator 2 inlet: 505.70 Stator 2 exit: 513.15 

 Stator 3 inlet: 543.36 Stator 3 exit: 551.67 Stator 4 inlet: 579.94 Stator 4 exit: 588.00 

 Stator 5 inlet: 609.83 Stator 5 exit: 617.71 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.44 

Fan Bypass Relative Humidity 0.19 

LPC Inlet Relative Humidity 2.52 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 495.70 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 457.44 

Additional Water at LPC Exit 0.0000239 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 387.85 6803.9 0.6132 4172.01 5.2838 789.49 32.274 1.710 100.000 2922.5 2743.6 1912.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.85 4.267 477.92 -16.44 0.0000 1282.32 2.854 425.97 3912.1 0.7800 1.40068 0.0000851 387.82 0.033 0.0001

FS1 Inlet.Fl_O 387.85 4.267 477.92 -16.44 0.0000 1282.32 3.150 438.17 4168.2 0.6727 1.40068 0.0000851 387.82 0.033 0.0001

FS12 Splitter.Fl_02 326.13 4.265 477.92 -16.44 0.0000 1078.79 3.174 439.19 3531.8 0.6634 1.40068 0.0000851 326.10 0.028 0.0001

FS2 Splitter.Fl_01 61.72 4.265 477.92 -16.44 0.0000 204.17 3.659 457.44 830.5 0.4726 1.40068 0.0000851 61.72 0.005 0.0001

FS14 Fan.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS23 LPC.Fl_O 61.72 10.479 647.76 24.36 0.0000 96.73 9.153 623.27 412.6 0.4443 1.39757 0.0000851 61.72 0.005 0.0001

FS24 VaporIN.Fl_O 61.72 10.479 647.85 24.25 0.0000 96.74 9.152 623.36 412.6 0.4444 1.39757 0.0001090 61.72 0.007 0.0001

FS25 Bleed2.Fl_O 61.72 10.479 647.85 24.25 0.0000 96.74 9.152 623.36 412.6 0.4444 1.39757 0.0001090 61.72 0.007 0.0001

FS3 HPC.Fl_O 58.73 137.704 1427.67 219.49 0.0000 10.40 124.235 1389.65 49.7 0.3922 1.35437 0.0001090 58.72 0.006 0.0001

FS36 Bleed3.Fl_O 45.52 137.704 1427.67 219.49 0.0000 8.06 129.878 1405.97 49.3 0.2950 1.35437 0.0001090 45.51 0.005 0.0001

FS4 Burner.Fl_O 46.67 134.533 2922.53 187.25 0.0255 12.10 127.111 2885.79 74.6 0.3007 1.28095 0.0001090 45.51 0.005 0.0307

FS45 HPT.Fl_O 62.16 31.492 1921.42 2.55 0.0190 55.83 28.372 1873.58 265.4 0.4005 1.31732 0.0001090 60.99 0.007 0.0231

FS49 LPT.Fl_O 62.88 7.251 1379.99 -143.20 0.0188 207.89 6.256 1328.67 860.2 0.4725 1.34412 0.0001090 61.72 0.007 0.0228

FS5 TEGV.Fl_O 62.88 7.251 1380.05 -143.20 0.0188 207.90 6.256 1328.73 860.2 0.4725 1.34412 0.0001090 61.72 0.007 0.0228

FS8 Core_Nozz.Fl_O 62.88 7.251 1380.18 -143.20 0.0188 207.91 3.882 1173.58 613.4 1.0000 1.34411 0.0001090 61.72 0.007 0.0228

FS17 FanDuctLkg.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS171 Bleed15.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS172 FanDuct.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS173 Byp_Nozz.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 3.833 469.91 2006.9 1.0000 1.39952 0.0000851 326.10 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.79 1.702 0.9114 4139.469 1.1801 0.9178 -9525.9 36.68 23.09

LPC 204.17 2.457 0.8233 4139.469 1.3554 0.8440 -3563.0 2.97 2.24

HPC 96.74 13.140 0.8585 10363.492 2.2037 0.8978 -16636.9 26.01 25.23

HPT 12.10 4.272 0.9122 214.250 1.3428 0.8903 16636.9 

LPT 55.83 4.343 0.9167 90.650 1.3888 0.9005 13088.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.45 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2237 0.8337 0.9870 0.0003

HPC 87.99 12.568 0.8673 10087.208 13.4977 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1813 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.515 0.9235 1.020 3.5146 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–57
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3912.12 9517.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.2714 1046.42 121.87 31.492

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7222 1046.42 121.87 7.251

TEGV 0.0000 0.4725 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.29 112.10 38.469

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1246.92 172.63 89.359

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.29 112.10 38.469

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1427.67 219.49 137.704

Splitter 5.2838 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.29 112.10 38.469

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11582.4 7544.1 16636.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 647.85 24.25 10.479

LP_Shaft 3973.5 17300.3 13088.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.0476 1427.67 219.49 134.533

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.1668 1427.67 219.49 75.594

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.67 219.49 137.704

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.67 219.49 137.704

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.67 219.49 137.704

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2922.53 0.9995 0.0230 1.15889 0.02546 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.541 0.9809 1.0000 0.9800 613.40 1.000 1620.2 3797.3

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1041.7 12523.7

NASA/TM—2013-218094 I–58
************************************************************************************************************************************ 

Date:07/05/13 Time:09:35:58 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 25/ 39/ 1/23 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 469.60 Stator 1 exit: 487.63 Stator 2 inlet: 508.98 Stator 2 exit: 517.20 

 Stator 3 inlet: 544.05 Stator 3 exit: 552.57 Stator 4 inlet: 577.92 Stator 4 exit: 585.87 

 Stator 5 inlet: 605.84 Stator 5 exit: 613.45 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.44 

Fan Bypass Relative Humidity 0.23 

LPC Inlet Relative Humidity 2.25 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 458.59 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.74 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 460.40 

Additional Water at LPC Exit 0.0000276 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 372.15 5891.2 0.6059 3569.34 5.4136 789.49 29.445 1.518 84.000 2762.8 2595.8 1803.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 372.15 4.267 477.92 -16.44 0.0000 1230.41 2.854 425.97 3753.7 0.7800 1.40068 0.0000851 372.11 0.032 0.0001

FS1 Inlet.Fl_O 372.15 4.267 477.92 -16.44 0.0000 1230.41 3.284 443.45 4168.2 0.6228 1.40068 0.0000851 372.11 0.032 0.0001

FS12 Splitter.Fl_02 314.12 4.265 477.92 -16.44 0.0000 1039.08 3.292 443.82 3531.8 0.6192 1.40068 0.0000851 314.09 0.027 0.0001

FS2 Splitter.Fl_01 58.02 4.265 477.92 -16.44 0.0000 191.94 3.743 460.40 830.5 0.4358 1.40068 0.0000851 58.02 0.005 0.0001

FS14 Fan.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.763 527.41 2606.7 0.5226 1.39966 0.0000851 314.09 0.027 0.0001

FS23 LPC.Fl_O 58.02 10.355 639.92 22.47 0.0000 91.47 9.205 618.83 412.6 0.4138 1.39779 0.0000851 58.02 0.005 0.0001

FS24 VaporIN.Fl_O 58.03 10.355 640.02 22.34 0.0000 91.48 9.204 618.91 412.6 0.4139 1.39778 0.0001126 58.02 0.007 0.0001

FS25 Bleed2.Fl_O 58.03 10.355 640.02 22.34 0.0000 91.48 9.204 618.91 412.6 0.4139 1.39778 0.0001126 58.02 0.007 0.0001

FS3 HPC.Fl_O 55.21 125.632 1378.40 206.59 0.0000 10.53 112.994 1340.39 49.7 0.3977 1.35718 0.0001126 55.21 0.006 0.0001

FS36 Bleed3.Fl_O 42.79 125.632 1378.40 206.59 0.0000 8.16 118.300 1356.73 49.3 0.2987 1.35718 0.0001126 42.78 0.005 0.0001

FS4 Burner.Fl_O 43.78 122.738 2762.82 177.64 0.0232 12.10 115.950 2727.55 74.6 0.2999 1.28688 0.0001126 42.78 0.005 0.0280

FS45 HPT.Fl_O 58.34 28.643 1812.34 2.67 0.0173 55.95 25.791 1766.39 265.4 0.4006 1.32301 0.0001126 57.34 0.006 0.0211

FS49 LPT.Fl_O 59.02 6.587 1297.07 -134.27 0.0171 208.22 5.681 1248.05 860.2 0.4723 1.35025 0.0001126 58.02 0.007 0.0208

FS5 TEGV.Fl_O 59.02 6.587 1297.13 -134.27 0.0171 208.22 5.681 1248.12 860.2 0.4723 1.35024 0.0001126 58.02 0.007 0.0208

FS8 Core_Nozz.Fl_O 59.02 6.587 1297.26 -134.27 0.0171 208.23 3.520 1100.26 613.4 1.0000 1.35023 0.0001126 58.02 0.007 0.0208

FS17 FanDuctLkg.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.763 527.41 2606.7 0.5226 1.39966 0.0000851 314.09 0.027 0.0001

FS171 Bleed15.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.600 523.11 2481.9 0.5626 1.39966 0.0000851 314.09 0.027 0.0001

FS172 FanDuct.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.600 523.11 2481.9 0.5626 1.39966 0.0000851 314.09 0.027 0.0001

FS173 Byp_Nozz.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 3.666 463.43 2006.9 1.0000 1.39966 0.0000851 314.09 0.027 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1039.08 1.628 0.9120 3982.719 1.1638 0.9179 -8347.6 51.73 26.15

LPC 191.94 2.428 0.8503 3982.719 1.3390 0.8676 -3194.6 2.91 2.10

HPC 91.48 12.132 0.8606 10189.485 2.1537 0.8985 -14760.1 29.69 28.69

HPT 12.10 4.285 0.9109 215.341 1.3490 0.8905 14760.1 

LPT 55.95 4.348 0.9147 89.803 1.3941 0.8982 11542.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1207.31 1.613 0.9139 3944.744 0.0614 0.8607 1.0235 0.9980 0.9905

LPC 152.37 2.575 0.8239 1.052 0.0000 1.2597 0.9067 1.0320 0.0003

HPC 83.20 11.608 0.8695 9917.840 13.1589 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.194 0.9109 1.294 4.1941 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.518 0.9215 1.010 3.5183 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–59
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3753.73 9131.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1354 1016.84 114.46 28.643

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6789 1016.84 114.46 6.587

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 979.79 105.25 35.716

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1206.89 162.37 81.826

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 979.79 105.25 35.716

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1378.40 206.59 125.632

Splitter 5.4136 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 979.79 105.25 35.716

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11318.9 6848.9 14760.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 640.02 22.34 10.355

LP_Shaft 3823.1 15856.5 11542.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.6254 1378.40 206.59 122.738

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7974 1378.40 206.59 68.916

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.40 206.59 125.632

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.40 206.59 125.632

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.40 206.59 125.632

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2762.81 0.9995 0.0230 0.99148 0.02317 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.308 0.9816 1.0000 0.9800 613.40 1.000 1572.2 3292.6

Byp_Nozz 2.432 0.9814 1.0000 0.9800 2006.86 1.000 1034.5 11730.3

NASA/TM—2013-218094 I–60
************************************************************************************************************************************ 

Date:07/05/13 Time:09:36:33 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 471.32 Stator 1 exit: 488.91 Stator 2 inlet: 509.92 Stator 2 exit: 518.28 

 Stator 3 inlet: 544.23 Stator 3 exit: 552.77 Stator 4 inlet: 577.31 Stator 4 exit: 585.21 

 Stator 5 inlet: 604.64 Stator 5 exit: 612.16 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.19 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 2.16 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 446.07 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.77 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 461.34 

Additional Water at LPC Exit 0.0000291 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 366.89 5594.6 0.6047 3382.81 5.4673 789.49 28.509 1.457 79.800 2712.2 2548.9 1770.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 366.89 4.267 477.92 -16.44 0.0000 1213.02 2.854 425.97 3700.7 0.7800 1.40068 0.0000851 366.86 0.031 0.0001

FS1 Inlet.Fl_O 366.89 4.267 477.92 -16.44 0.0000 1213.02 3.325 444.99 4168.2 0.6076 1.40068 0.0000851 366.86 0.031 0.0001

FS12 Splitter.Fl_02 310.16 4.265 477.92 -16.44 0.0000 1025.97 3.328 445.18 3531.8 0.6058 1.40068 0.0000851 310.13 0.026 0.0001

FS2 Splitter.Fl_01 56.73 4.265 477.92 -16.44 0.0000 187.66 3.769 461.34 830.5 0.4235 1.40068 0.0000851 56.72 0.005 0.0001

FS14 Fan.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.677 524.99 2606.7 0.5226 1.39970 0.0000851 310.13 0.026 0.0001

FS23 LPC.Fl_O 56.73 10.300 637.58 21.91 0.0000 89.74 9.205 617.51 412.6 0.4041 1.39785 0.0000851 56.72 0.005 0.0001

FS24 VaporIN.Fl_O 56.73 10.300 637.68 21.76 0.0000 89.75 9.205 617.59 412.6 0.4042 1.39785 0.0001142 56.72 0.006 0.0001

FS25 Bleed2.Fl_O 56.73 10.300 637.68 21.76 0.0000 89.75 9.205 617.59 412.6 0.4042 1.39785 0.0001142 56.72 0.006 0.0001

FS3 HPC.Fl_O 53.98 121.641 1362.71 202.50 0.0000 10.57 109.293 1324.70 49.7 0.3995 1.35810 0.0001142 53.97 0.006 0.0001

FS36 Bleed3.Fl_O 41.83 121.641 1362.71 202.50 0.0000 8.19 114.481 1341.05 49.3 0.3000 1.35810 0.0001142 41.83 0.005 0.0001

FS4 Burner.Fl_O 42.77 118.840 2712.18 174.55 0.0225 12.10 112.266 2677.40 74.6 0.2996 1.28878 0.0001142 41.83 0.005 0.0272

FS45 HPT.Fl_O 57.01 27.707 1778.22 2.72 0.0168 55.99 24.944 1732.88 265.4 0.4006 1.32487 0.0001142 56.06 0.006 0.0204

FS49 LPT.Fl_O 57.67 6.370 1271.28 -131.47 0.0166 208.31 5.493 1223.01 860.2 0.4721 1.35221 0.0001142 56.72 0.006 0.0202

FS5 TEGV.Fl_O 57.67 6.370 1271.34 -131.47 0.0166 208.31 5.493 1223.07 860.2 0.4722 1.35220 0.0001142 56.72 0.006 0.0202

FS8 Core_Nozz.Fl_O 57.67 6.370 1271.47 -131.47 0.0166 208.33 3.402 1077.52 613.4 1.0000 1.35219 0.0001142 56.72 0.006 0.0202

FS17 FanDuctLkg.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.677 524.99 2606.7 0.5226 1.39970 0.0000851 310.13 0.026 0.0001

FS171 Bleed15.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.516 520.71 2481.9 0.5626 1.39970 0.0000851 310.13 0.026 0.0001

FS172 FanDuct.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.516 520.71 2481.9 0.5626 1.39970 0.0000851 310.13 0.026 0.0001

FS173 Byp_Nozz.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 3.612 461.30 2006.9 1.0000 1.39970 0.0000851 310.13 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1025.97 1.604 0.9117 3933.633 1.1585 0.9174 -7973.7 56.33 27.21

LPC 187.66 2.415 0.8569 3933.633 1.3341 0.8734 -3078.1 3.24 2.50

HPC 89.75 11.810 0.8612 10141.348 2.1370 0.8987 -14154.9 30.97 29.86

HPT 12.10 4.289 0.9102 215.920 1.3509 0.8900 14154.9 

LPT 55.99 4.350 0.9140 89.543 1.3957 0.8973 11051.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1192.08 1.590 0.9136 3896.126 0.0605 0.8607 1.0235 0.9980 0.9905

LPC 149.00 2.524 0.8226 1.039 0.0000 1.2595 0.9287 1.0418 0.0003

HPC 81.63 11.300 0.8701 9870.986 13.0483 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.198 0.9102 1.298 4.1981 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.519 0.9208 1.007 3.5195 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–61
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3700.69 9002.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0877 1007.51 112.13 27.707

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6638 1007.51 112.13 6.370

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.12 103.09 34.795

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1194.17 159.12 79.332

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.12 103.09 34.795

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1362.71 202.50 121.641

Splitter 5.4673 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.12 103.09 34.795

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11244.8 6611.3 14154.9 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.68 21.76 10.300

LP_Shaft 3775.9 15372.2 11051.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4776 1362.71 202.50 118.840

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6680 1362.71 202.50 66.712

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.71 202.50 121.641

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.71 202.50 121.641

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.71 202.50 121.641

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2712.16 0.9995 0.0230 0.93967 0.02246 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.232 0.9816 1.0000 0.9800 613.40 1.000 1556.9 3126.8

Byp_Nozz 2.396 0.9814 1.0000 0.9800 2006.86 1.000 1032.2 11470.4

NASA/TM—2013-218094 I–62
************************************************************************************************************************************ 

Date:07/05/13 Time:09:37:07 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 472.50 Stator 1 exit: 489.81 Stator 2 inlet: 510.62 Stator 2 exit: 519.08 

 Stator 3 inlet: 544.45 Stator 3 exit: 553.01 Stator 4 inlet: 577.01 Stator 4 exit: 584.90 

 Stator 5 inlet: 603.97 Stator 5 exit: 611.45 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.03 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 2.11 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 437.10 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 462.00 

Additional Water at LPC Exit 0.0000303 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 363.05 5383.7 0.6046 3254.93 5.5077 789.49 27.845 1.415 76.800 2677.4 2516.8 1746.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.05 4.267 477.92 -16.44 0.0000 1200.34 2.854 425.97 3662.0 0.7800 1.40068 0.0000851 363.02 0.031 0.0001

FS1 Inlet.Fl_O 363.05 4.267 477.92 -16.44 0.0000 1200.34 3.353 446.06 4168.2 0.5970 1.40068 0.0000851 363.02 0.031 0.0001

FS12 Splitter.Fl_02 307.26 4.265 477.92 -16.44 0.0000 1016.40 3.353 446.12 3531.8 0.5963 1.40068 0.0000851 307.24 0.026 0.0001

FS2 Splitter.Fl_01 55.79 4.265 477.92 -16.44 0.0000 184.54 3.788 462.00 830.5 0.4147 1.40068 0.0000851 55.78 0.005 0.0001

FS14 Fan.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.615 523.30 2606.7 0.5226 1.39973 0.0000851 307.24 0.026 0.0001

FS23 LPC.Fl_O 55.79 10.263 636.11 21.55 0.0000 88.47 9.207 616.75 412.6 0.3971 1.39789 0.0000851 55.78 0.005 0.0001

FS24 VaporIN.Fl_O 55.79 10.263 636.21 21.40 0.0000 88.48 9.207 616.83 412.6 0.3972 1.39789 0.0001153 55.78 0.006 0.0001

FS25 Bleed2.Fl_O 55.79 10.263 636.21 21.40 0.0000 88.48 9.207 616.83 412.6 0.3972 1.39789 0.0001153 55.78 0.006 0.0001

FS3 HPC.Fl_O 53.08 118.805 1351.96 199.70 0.0000 10.60 106.666 1313.94 49.7 0.4008 1.35873 0.0001153 53.08 0.006 0.0001

FS36 Bleed3.Fl_O 41.14 118.805 1351.96 199.70 0.0000 8.22 111.768 1330.33 49.3 0.3009 1.35873 0.0001153 41.13 0.005 0.0001

FS4 Burner.Fl_O 42.04 116.069 2677.35 172.42 0.0220 12.09 109.646 2642.93 74.6 0.2994 1.29010 0.0001153 41.13 0.005 0.0266

FS45 HPT.Fl_O 56.04 27.045 1754.90 2.78 0.0164 56.01 24.346 1709.96 265.4 0.4007 1.32616 0.0001153 55.13 0.006 0.0200

FS49 LPT.Fl_O 56.69 6.216 1253.67 -129.52 0.0162 208.39 5.359 1205.91 860.2 0.4721 1.35355 0.0001153 55.78 0.006 0.0198

FS5 TEGV.Fl_O 56.69 6.216 1253.74 -129.52 0.0162 208.39 5.359 1205.97 860.2 0.4721 1.35355 0.0001153 55.78 0.006 0.0198

FS8 Core_Nozz.Fl_O 56.69 6.216 1253.87 -129.52 0.0162 208.40 3.319 1062.03 613.4 1.0000 1.35354 0.0001153 55.78 0.006 0.0198

FS17 FanDuctLkg.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.615 523.30 2606.7 0.5226 1.39973 0.0000851 307.24 0.026 0.0001

FS171 Bleed15.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.456 519.03 2481.9 0.5626 1.39973 0.0000851 307.24 0.026 0.0001

FS172 FanDuct.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.456 519.03 2481.9 0.5626 1.39973 0.0000851 307.24 0.026 0.0001

FS173 Byp_Nozz.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 3.572 459.82 2006.9 1.0000 1.39973 0.0000851 307.24 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1016.40 1.586 0.9105 3900.457 1.1548 0.9162 -7713.2 58.47 27.99

LPC 184.54 2.406 0.8609 3900.457 1.3310 0.8769 -2998.9 3.51 2.79

HPC 88.48 11.576 0.8614 10106.712 2.1250 0.8986 -13732.3 31.90 30.71

HPT 12.09 4.292 0.9097 216.327 1.3521 0.8896 13732.3 

LPT 56.01 4.351 0.9135 89.376 1.3969 0.8967 10712.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1180.95 1.573 0.9124 3863.266 0.0599 0.8607 1.0235 0.9980 0.9905

LPC 146.86 2.490 0.8219 1.030 0.0000 1.2566 0.9440 1.0474 0.0003

HPC 80.47 11.078 0.8703 9837.273 12.9696 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.201 0.9097 1.300 4.2005 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9203 1.005 3.5203 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–63
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3661.99 8908.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0530 1001.18 110.55 27.045

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6527 1001.18 110.55 6.216

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.26 101.64 34.142

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1185.50 156.91 77.559

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.26 101.64 34.142

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1351.96 199.70 118.805

Splitter 5.5077 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.26 101.64 34.142

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11193.4 6443.4 13732.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 636.21 21.40 10.263

LP_Shaft 3744.1 15026.5 10712.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.3700 1351.96 199.70 116.069

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.5739 1351.96 199.70 65.147

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1351.96 199.70 118.805

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1351.96 199.70 118.805

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1351.96 199.70 118.805

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2677.34 0.9995 0.0230 0.90415 0.02198 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.178 0.9815 1.0000 0.9800 613.40 1.000 1546.4 3009.8

Byp_Nozz 2.370 0.9815 1.0000 0.9800 2006.86 1.000 1030.5 11282.4

NASA/TM—2013-218094 I–64
 100μm, ISA +18R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:47:54 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 38/ 1/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 444.03 Stator 1 exit: 462.65 Stator 2 inlet: 484.17 Stator 2 exit: 491.24 

 Stator 3 inlet: 520.19 Stator 3 exit: 528.10 Stator 4 inlet: 555.19 Stator 4 exit: 562.88 

 Stator 5 inlet: 583.79 Stator 5 exit: 591.31 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.21 

Fan Bypass Relative Humidity 0.15 

LPC Inlet Relative Humidity 2.30 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 485.45 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 438.10 

Additional Water at LPC Exit 0.0000151 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 396.35 6794.7 0.5974 4059.10 5.2809 772.64 32.334 1.706 100.000 2814.3 2641.1 1834.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 396.35 4.267 457.74 -20.96 0.0000 1282.45 2.854 407.97 3912.3 0.7800 1.40084 0.0000295 396.34 0.012 0.0000

FS1 Inlet.Fl_O 396.35 4.267 457.74 -20.96 0.0000 1282.45 3.150 419.65 4168.2 0.6728 1.40084 0.0000295 396.34 0.012 0.0000

FS12 Splitter.Fl_02 333.25 4.265 457.74 -20.96 0.0000 1078.81 3.174 420.64 3531.8 0.6633 1.40084 0.0000295 333.24 0.010 0.0000

FS2 Splitter.Fl_01 63.11 4.265 457.74 -20.96 0.0000 204.29 3.659 438.10 830.5 0.4730 1.40084 0.0000295 63.10 0.002 0.0000

FS14 Fan.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS23 LPC.Fl_O 63.11 10.456 620.26 18.06 0.0000 96.99 9.124 596.63 412.6 0.4457 1.39831 0.0000295 63.10 0.002 0.0000

FS24 VaporIN.Fl_O 63.11 10.456 620.33 17.99 0.0000 97.00 9.124 596.69 412.6 0.4458 1.39831 0.0000445 63.10 0.003 0.0000

FS25 Bleed2.Fl_O 63.11 10.456 620.33 17.99 0.0000 97.00 9.124 596.69 412.6 0.4458 1.39831 0.0000445 63.10 0.003 0.0000

FS3 HPC.Fl_O 60.05 137.963 1373.15 205.60 0.0000 10.41 124.449 1336.29 49.7 0.3921 1.35750 0.0000445 60.04 0.003 0.0000

FS36 Bleed3.Fl_O 46.54 137.963 1373.15 205.60 0.0000 8.07 130.111 1352.09 49.3 0.2948 1.35750 0.0000445 46.53 0.002 0.0000

FS4 Burner.Fl_O 47.66 134.786 2814.26 175.35 0.0242 12.11 127.330 2778.52 74.6 0.3003 1.28479 0.0000445 46.53 0.002 0.0292

FS45 HPT.Fl_O 63.50 31.495 1843.67 -2.48 0.0181 55.86 28.371 1797.31 265.4 0.4001 1.32115 0.0000445 62.36 0.003 0.0219

FS49 LPT.Fl_O 64.23 7.237 1320.43 -142.07 0.0179 208.13 6.242 1270.79 860.2 0.4724 1.34831 0.0000445 63.10 0.003 0.0217

FS5 TEGV.Fl_O 64.23 7.237 1320.50 -142.07 0.0179 208.13 6.242 1270.85 860.2 0.4724 1.34830 0.0000445 63.10 0.003 0.0217

FS8 Core_Nozz.Fl_O 64.23 7.237 1320.63 -142.07 0.0179 208.14 3.870 1120.99 613.4 1.0000 1.34829 0.0000445 63.10 0.003 0.0217

FS17 FanDuctLkg.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 6.024 512.21 2606.7 0.5226 1.39992 0.0000295 333.24 0.010 0.0000

FS171 Bleed15.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS172 FanDuct.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 5.854 508.03 2481.9 0.5625 1.39992 0.0000295 333.24 0.010 0.0000

FS173 Byp_Nozz.Fl_O 333.25 7.257 540.20 -1.18 0.0000 688.69 3.833 450.06 2006.9 1.0000 1.39992 0.0000295 333.24 0.010 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.81 1.702 0.9114 4139.469 1.1801 0.9178 -9322.3 36.69 23.09

LPC 204.29 2.452 0.8224 4139.469 1.3550 0.8432 -3483.1 2.97 2.24

HPC 97.00 13.194 0.8584 10373.882 2.2136 0.8979 -16345.1 25.80 25.03

HPT 12.11 4.280 0.9118 213.858 1.3470 0.8911 16345.1 

LPT 55.86 4.352 0.9155 90.566 1.3928 0.8988 12805.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.47 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2244 0.8306 0.9860 0.0003

HPC 88.22 12.620 0.8672 10097.321 13.5183 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.189 0.9118 1.285 4.1887 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.521 0.9223 1.019 3.5213 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–65
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3912.34 9518.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.3223 1004.57 111.79 31.495

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7383 1004.57 111.79 7.237

TEGV 0.0000 0.4724 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.78 102.41 38.508

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1198.34 160.57 89.511

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.78 102.41 38.508

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1373.15 205.60 137.963

Splitter 5.2809 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 966.78 102.41 38.508

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11345.1 7566.9 16345.1 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 620.33 17.99 10.456

LP_Shaft 3888.7 17295.0 12805.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.2054 1373.15 205.60 134.786

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.3049 1373.15 205.60 75.704

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.15 205.60 137.963

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.15 205.60 137.963

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1373.15 205.60 137.963

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 540.20 -1.18 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2814.25 0.9995 0.0230 1.12753 0.02423 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.536 0.9809 1.0000 0.9800 613.40 1.000 1585.8 3789.0

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1019.5 12523.9

NASA/TM—2013-218094 I–66
************************************************************************************************************************************ 

Date:07/05/13 Time:09:48:31 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 450.18 Stator 1 exit: 467.32 Stator 2 inlet: 487.66 Stator 2 exit: 495.55 

 Stator 3 inlet: 521.02 Stator 3 exit: 529.17 Stator 4 inlet: 553.24 Stator 4 exit: 560.82 

 Stator 5 inlet: 579.81 Stator 5 exit: 587.06 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.12 

Fan Bypass Relative Humidity 0.18 

LPC Inlet Relative Humidity 2.01 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 445.63 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.75 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 441.19 

Additional Water at LPC Exit 0.0000152 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 378.74 5799.0 0.5905 3424.20 5.4244 772.64 29.236 1.498 84.000 2646.5 2485.9 1722.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 378.74 4.267 457.74 -20.96 0.0000 1225.46 2.854 407.97 3738.5 0.7800 1.40084 0.0000295 378.73 0.011 0.0000

FS1 Inlet.Fl_O 378.74 4.267 457.74 -20.96 0.0000 1225.46 3.296 425.15 4168.2 0.6183 1.40084 0.0000295 378.73 0.011 0.0000

FS12 Splitter.Fl_02 319.79 4.265 457.74 -20.96 0.0000 1035.23 3.303 425.46 3531.8 0.6151 1.40084 0.0000295 319.78 0.009 0.0000

FS2 Splitter.Fl_01 58.95 4.265 457.74 -20.96 0.0000 190.85 3.750 441.19 830.5 0.4326 1.40084 0.0000295 58.95 0.002 0.0000

FS14 Fan.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.737 504.50 2606.7 0.5226 1.40004 0.0000295 319.78 0.009 0.0000

FS23 LPC.Fl_O 58.95 10.330 612.23 16.12 0.0000 91.12 9.193 592.21 412.6 0.4118 1.39852 0.0000295 58.95 0.002 0.0000

FS24 VaporIN.Fl_O 58.95 10.330 612.30 16.05 0.0000 91.13 9.193 592.28 412.6 0.4118 1.39851 0.0000446 58.95 0.003 0.0000

FS25 Bleed2.Fl_O 58.95 10.330 612.30 16.05 0.0000 91.13 9.193 592.28 412.6 0.4118 1.39851 0.0000446 58.95 0.003 0.0000

FS3 HPC.Fl_O 56.09 124.744 1320.99 192.07 0.0000 10.55 112.152 1284.18 49.7 0.3980 1.36059 0.0000446 56.09 0.003 0.0000

FS36 Bleed3.Fl_O 43.47 124.744 1320.99 192.07 0.0000 8.17 117.439 1300.01 49.3 0.2989 1.36059 0.0000446 43.47 0.002 0.0000

FS4 Burner.Fl_O 44.42 121.871 2646.49 165.11 0.0219 12.10 115.114 2612.35 74.6 0.2995 1.29109 0.0000446 43.47 0.002 0.0264

FS45 HPT.Fl_O 59.22 28.387 1730.17 -2.36 0.0163 55.99 25.554 1685.75 265.4 0.4003 1.32735 0.0000446 58.26 0.003 0.0199

FS49 LPT.Fl_O 59.91 6.515 1234.61 -132.77 0.0161 208.47 5.617 1187.42 860.2 0.4721 1.35480 0.0000446 58.95 0.003 0.0196

FS5 TEGV.Fl_O 59.91 6.515 1234.67 -132.77 0.0161 208.47 5.617 1187.48 860.2 0.4721 1.35480 0.0000446 58.95 0.003 0.0196

FS8 Core_Nozz.Fl_O 59.91 6.515 1234.81 -132.77 0.0161 208.48 3.477 1045.35 613.4 1.0000 1.35479 0.0000446 58.95 0.003 0.0196

FS17 FanDuctLkg.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.737 504.50 2606.7 0.5226 1.40004 0.0000295 319.78 0.009 0.0000

FS171 Bleed15.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.575 500.38 2481.9 0.5625 1.40004 0.0000295 319.78 0.009 0.0000

FS172 FanDuct.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 5.575 500.38 2481.9 0.5625 1.40004 0.0000295 319.78 0.009 0.0000

FS173 Byp_Nozz.Fl_O 319.79 6.911 532.08 -3.13 0.0000 688.70 3.650 443.27 2006.9 1.0000 1.40004 0.0000295 319.78 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1035.23 1.621 0.9117 3968.841 1.1624 0.9175 -8063.8 53.03 26.46

LPC 190.85 2.422 0.8520 3968.841 1.3375 0.8691 -3092.8 2.96 2.16

HPC 91.13 12.076 0.8607 10180.126 2.1574 0.8986 -14325.3 29.83 28.82 

HPT 12.10 4.293 0.9099 215.008 1.3534 0.8903 14325.2 

LPT 55.99 4.357 0.9131 89.636 1.3983 0.8961 11156.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1202.83 1.606 0.9135 3930.998 0.0611 0.8607 1.0235 0.9980 0.9905

LPC 151.27 2.560 0.8233 1.048 0.0000 1.2615 0.9115 1.0349 0.0003

HPC 82.88 11.554 0.8696 9908.731 13.1468 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.202 0.9099 1.292 4.2020 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.525 0.9199 1.008 3.5247 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–67
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3738.47 9095.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1695 973.43 104.06 28.387

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6898 973.43 104.06 6.515

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 937.86 95.26 35.501

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1156.04 149.82 81.267

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 937.86 95.26 35.501

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1320.99 192.07 124.744

Splitter 5.4244 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 937.86 95.26 35.501

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11060.9 6802.1 14325.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 612.30 16.05 10.330

LP_Shaft 3728.4 15716.1 11156.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.7314 1320.99 192.07 121.871

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.8901 1320.99 192.07 68.398

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1320.99 192.07 124.744

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1320.99 192.07 124.744

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1320.99 192.07 124.744

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 532.08 -3.13 6.911

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2646.48 0.9995 0.0230 0.95117 0.02188 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.283 0.9816 1.0000 0.9800 613.40 1.000 1534.8 3240.0

Byp_Nozz 2.422 0.9814 1.0000 0.9800 2006.86 1.000 1011.8 11654.2

NASA/TM—2013-218094 I–68
************************************************************************************************************************************ 

Date:07/05/13 Time:09:49:07 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 451.80 Stator 1 exit: 468.53 Stator 2 inlet: 488.56 Stator 2 exit: 496.59 

 Stator 3 inlet: 521.23 Stator 3 exit: 529.40 Stator 4 inlet: 552.71 Stator 4 exit: 560.26 

 Stator 5 inlet: 578.74 Stator 5 exit: 585.91 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.88 

Fan Bypass Relative Humidity 0.20 

LPC Inlet Relative Humidity 1.93 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 433.45 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.78 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.08 

Additional Water at LPC Exit 0.0000152 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 373.42 5507.4 0.5896 3247.42 5.4794 772.64 28.311 1.439 79.800 2598.7 2441.7 1690.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 373.42 4.267 457.74 -20.96 0.0000 1208.26 2.854 407.97 3686.0 0.7800 1.40084 0.0000295 373.41 0.011 0.0000

FS1 Inlet.Fl_O 373.42 4.267 457.74 -20.96 0.0000 1208.26 3.335 426.59 4168.2 0.6035 1.40084 0.0000295 373.41 0.011 0.0000

FS12 Splitter.Fl_02 315.79 4.265 457.74 -20.96 0.0000 1022.29 3.338 426.73 3531.8 0.6021 1.40084 0.0000295 315.78 0.009 0.0000

FS2 Splitter.Fl_01 57.63 4.265 457.74 -20.96 0.0000 186.57 3.776 442.08 830.5 0.4204 1.40084 0.0000295 57.63 0.002 0.0000

FS14 Fan.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.653 502.21 2606.7 0.5226 1.40008 0.0000295 315.78 0.009 0.0000

FS23 LPC.Fl_O 57.63 10.277 610.10 15.61 0.0000 89.38 9.195 591.05 412.6 0.4020 1.39857 0.0000295 57.63 0.002 0.0000

FS24 VaporIN.Fl_O 57.63 10.277 610.17 15.54 0.0000 89.39 9.195 591.11 412.6 0.4021 1.39856 0.0000447 57.63 0.003 0.0000

FS25 Bleed2.Fl_O 57.63 10.277 610.17 15.54 0.0000 89.39 9.195 591.11 412.6 0.4021 1.39856 0.0000447 57.63 0.003 0.0000

FS3 HPC.Fl_O 54.84 120.798 1306.06 188.21 0.0000 10.59 108.499 1269.28 49.7 0.3997 1.36150 0.0000447 54.84 0.002 0.0000

FS36 Bleed3.Fl_O 42.50 120.798 1306.06 188.21 0.0000 8.20 113.667 1285.12 49.3 0.3001 1.36150 0.0000447 42.50 0.002 0.0000

FS4 Burner.Fl_O 43.40 118.016 2598.73 162.16 0.0212 12.10 111.473 2565.04 74.6 0.2992 1.29291 0.0000447 42.50 0.002 0.0257

FS45 HPT.Fl_O 57.86 27.464 1698.23 -2.31 0.0158 56.02 24.720 1654.42 265.4 0.4003 1.32917 0.0000447 56.96 0.003 0.0193

FS49 LPT.Fl_O 58.53 6.302 1210.63 -130.14 0.0157 208.55 5.432 1164.15 860.2 0.4720 1.35663 0.0000447 57.63 0.003 0.0191

FS5 TEGV.Fl_O 58.53 6.302 1210.70 -130.14 0.0157 208.55 5.432 1164.21 860.2 0.4720 1.35663 0.0000447 57.63 0.003 0.0191

FS8 Core_Nozz.Fl_O 58.53 6.302 1210.83 -130.14 0.0157 208.56 3.361 1024.30 613.4 1.0000 1.35662 0.0000447 57.63 0.003 0.0191

FS17 FanDuctLkg.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.653 502.21 2606.7 0.5226 1.40008 0.0000295 315.78 0.009 0.0000

FS171 Bleed15.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.493 498.11 2481.9 0.5625 1.40008 0.0000295 315.78 0.009 0.0000

FS172 FanDuct.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 5.493 498.11 2481.9 0.5625 1.40008 0.0000295 315.78 0.009 0.0000

FS173 Byp_Nozz.Fl_O 315.79 6.810 529.66 -3.71 0.0000 688.70 3.596 441.26 2006.9 1.0000 1.40008 0.0000295 315.78 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1022.29 1.597 0.9114 3920.781 1.1571 0.9170 -7703.9 57.15 27.51

LPC 186.57 2.410 0.8583 3920.781 1.3329 0.8746 -2981.7 3.34 2.63

HPC 89.39 11.754 0.8613 10131.674 2.1405 0.8988 -13738.2 31.10 29.98

HPT 12.10 4.297 0.9091 215.566 1.3551 0.8897 13738.2 

LPT 56.02 4.358 0.9123 89.380 1.3998 0.8952 10685.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1187.80 1.583 0.9132 3883.397 0.0603 0.8607 1.0235 0.9980 0.9905

LPC 148.17 2.511 0.8223 1.036 0.0000 1.2591 0.9332 1.0438 0.0003

HPC 81.30 11.247 0.8702 9861.570 13.0377 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.206 0.9090 1.296 4.2057 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9191 1.005 3.5257 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–69
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3685.99 8967.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1209 964.61 101.87 27.464

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6743 964.61 101.87 6.302

TEGV 0.0000 0.4720 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.68 93.24 34.592

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1143.97 146.77 78.800

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.68 93.24 34.592

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1306.06 188.21 120.798

Splitter 5.4794 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 929.68 93.24 34.592

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10989.1 6566.0 13738.2 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 610.17 15.54 10.277

LP_Shaft 3683.3 15236.7 10685.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.5805 1306.06 188.21 118.016

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7581 1306.06 188.21 66.220

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.06 188.21 120.798

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.06 188.21 120.798

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1306.06 188.21 120.798

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 529.66 -3.71 6.810

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2598.71 0.9995 0.0230 0.90206 0.02123 

 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.208 0.9816 1.0000 0.9800 613.40 1.000 1520.2 3077.0

Byp_Nozz 2.386 0.9815 1.0000 0.9800 2006.86 1.000 1009.5 11397.9

NASA/TM—2013-218094 I–70
************************************************************************************************************************************ 

Date:07/05/13 Time:09:49:42 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 18/ 32/ 1/16 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 452.89 Stator 1 exit: 469.36 Stator 2 inlet: 489.19 Stator 2 exit: 497.30 

 Stator 3 inlet: 521.41 Stator 3 exit: 529.59 Stator 4 inlet: 552.40 Stator 4 exit: 559.93 

 Stator 5 inlet: 578.07 Stator 5 exit: 585.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.72 

Fan Bypass Relative Humidity 0.21 

LPC Inlet Relative Humidity 1.88 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 424.81 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 442.70 

Additional Water at LPC Exit 0.0000152 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 369.50 5300.3 0.5901 3127.54 5.5191 772.64 27.662 1.398 76.800 2566.3 2411.8 1668.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 369.50 4.267 457.74 -20.96 0.0000 1195.58 2.854 407.97 3647.3 0.7800 1.40084 0.0000295 369.49 0.011 0.0000

FS1 Inlet.Fl_O 369.50 4.267 457.74 -20.96 0.0000 1195.58 3.363 427.60 4168.2 0.5930 1.40084 0.0000295 369.49 0.011 0.0000

FS12 Splitter.Fl_02 312.82 4.265 457.74 -20.96 0.0000 1012.69 3.362 427.63 3531.8 0.5927 1.40084 0.0000295 312.82 0.009 0.0000

FS2 Splitter.Fl_01 56.68 4.265 457.74 -20.96 0.0000 183.49 3.795 442.70 830.5 0.4117 1.40084 0.0000295 56.68 0.002 0.0000

FS14 Fan.Fl_O 312.82 6.735 528.01 -4.11 0.0000 688.70 5.591 500.64 2606.7 0.5226 1.40010 0.0000295 312.82 0.009 0.0000

FS23 LPC.Fl_O 56.68 10.238 608.70 15.27 0.0000 88.14 9.194 590.31 412.6 0.3952 1.39860 0.0000295 56.68 0.002 0.0000

FS24 VaporIN.Fl_O 56.68 10.238 608.77 15.20 0.0000 88.15 9.194 590.37 412.6 0.3952 1.39859 0.0000447 56.68 0.003 0.0000

FS25 Bleed2.Fl_O 56.68 10.238 608.77 15.20 0.0000 88.15 9.194 590.37 412.6 0.3952 1.39859 0.0000447 56.68 0.003 0.0000

FS3 HPC.Fl_O 53.93 118.027 1295.99 185.60 0.0000 10.61 105.935 1259.20 49.7 0.4009 1.36211 0.0000447 53.93 0.002 0.0000

FS36 Bleed3.Fl_O 41.80 118.027 1295.99 185.60 0.0000 8.23 111.018 1275.04 49.3 0.3009 1.36211 0.0000447 41.80 0.002 0.0000

FS4 Burner.Fl_O 42.67 115.309 2566.34 160.16 0.0208 12.10 108.914 2532.97 74.6 0.2990 1.29415 0.0000447 41.80 0.002 0.0251

FS45 HPT.Fl_O 56.89 26.818 1676.63 -2.27 0.0155 56.05 24.137 1633.22 265.4 0.4003 1.33042 0.0000447 56.02 0.003 0.0189

FS49 LPT.Fl_O 57.55 6.153 1194.46 -128.35 0.0153 208.60 5.303 1148.47 860.2 0.4719 1.35787 0.0000447 56.68 0.003 0.0187

FS5 TEGV.Fl_O 57.55 6.153 1194.53 -128.35 0.0153 208.61 5.303 1148.53 860.2 0.4719 1.35787 0.0000447 56.68 0.003 0.0187

FS8 Core_Nozz.Fl_O 57.55 6.153 1194.67 -128.35 0.0153 208.62 3.281 1010.12 613.4 1.0000 1.35786 0.0000447 56.68 0.003 0.0187

FS17 FanDuctLkg.Fl_O 312.82 6.735 528.01 -4.11 0.0000 688.70 5.591 500.64 2606.7 0.5226 1.40010 0.0000295 312.82 0.009 0.0000

FS171 Bleed15.Fl_O 312.82 6.735 528.01 -4.11 0.0000 688.70 5.433 496.56 2481.9 0.5625 1.40010 0.0000295 312.82 0.009 0.0000

FS172 FanDuct.Fl_O 312.82 6.735 528.01 -4.11 0.0000 688.70 5.433 496.56 2481.9 0.5625 1.40010 0.0000295 312.82 0.009 0.0000

FS173 Byp_Nozz.Fl_O 312.82 6.735 528.01 -4.11 0.0000 688.70 3.557 439.88 2006.9 1.0000 1.40010 0.0000295 312.82 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1012.69 1.579 0.9094 3888.072 1.1535 0.9150 -7456.5 59.29 28.29

LPC 183.49 2.401 0.8620 3888.072 1.3298 0.8778 -2905.4 3.61 2.87

HPC 88.15 11.528 0.8614 10098.219 2.1289 0.8986 -13334.0 32.00 30.80

HPT 12.10 4.300 0.9085 215.957 1.3562 0.8892 13334.0 

LPT 56.05 4.359 0.9118 89.203 1.4008 0.8945 10361.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1176.64 1.566 0.9112 3850.999 0.0597 0.8607 1.0235 0.9980 0.9905

LPC 146.06 2.477 0.8217 1.027 0.0000 1.2562 0.9482 1.0491 0.0003

HPC 80.17 11.032 0.8703 9829.008 12.9619 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.208 0.9085 1.298 4.2082 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.526 0.9185 1.003 3.5263 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–71
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3647.32 8873.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0859 958.67 100.40 26.818

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6632 958.67 100.40 6.153

TEGV 0.0000 0.4719 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.17 91.88 33.952

FanDuct 0.0000 0.5625 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1135.83 144.71 77.067

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.17 91.88 33.952

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1295.99 185.60 118.027

Splitter 5.5191 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 924.17 91.88 33.952

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 10940.2 6401.3 13334.0 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 608.77 15.20 10.238

LP_Shaft 3652.6 14899.5 10361.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4718 1295.99 185.60 115.309

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6630 1295.99 185.60 64.692

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1295.99 185.60 118.027

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1295.99 185.60 118.027

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1295.99 185.60 118.027

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 528.01 -4.11 6.735

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2566.32 0.9995 0.0230 0.86876 0.02079 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.156 0.9815 1.0000 0.9800 613.40 1.000 1510.2 2963.1

Byp_Nozz 2.360 0.9815 1.0000 0.9800 2006.86 1.000 1007.9 11210.6

NASA/TM—2013-218094 I–72
 100μm, ISA +36R

************************************************************************************************************************************ 

Date:07/05/13 Time:09:59:54 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 38/ 1/22 Run by: Philip C Jorgenson PC: 100 

Temperature Stator 1 inlet: 463.71 Stator 1 exit: 483.17 Stator 2 inlet: 505.69 Stator 2 exit: 513.14 

 Stator 3 inlet: 543.36 Stator 3 exit: 551.66 Stator 4 inlet: 579.93 Stator 4 exit: 587.99 

 Stator 5 inlet: 609.83 Stator 5 exit: 617.71 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.44 

Fan Bypass Relative Humidity 0.19 

LPC Inlet Relative Humidity 2.52 

LPC Exit Relative Humidity 0.02 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 495.72 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.66 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 457.44 

Additional Water at LPC Exit 0.0000037 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 387.85 6803.7 0.6132 4171.96 5.2836 789.49 32.273 1.709 100.000 2922.5 2743.5 1912.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.85 4.267 477.92 -16.44 0.0000 1282.33 2.854 425.97 3912.1 0.7800 1.40068 0.0000851 387.82 0.033 0.0001

FS1 Inlet.Fl_O 387.85 4.267 477.92 -16.44 0.0000 1282.33 3.150 438.17 4168.2 0.6727 1.40068 0.0000851 387.82 0.033 0.0001

FS12 Splitter.Fl_02 326.13 4.265 477.92 -16.44 0.0000 1078.79 3.174 439.19 3531.8 0.6634 1.40068 0.0000851 326.10 0.028 0.0001

FS2 Splitter.Fl_01 61.72 4.265 477.92 -16.44 0.0000 204.18 3.659 457.44 830.5 0.4726 1.40068 0.0000851 61.72 0.005 0.0001

FS14 Fan.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS23 LPC.Fl_O 61.72 10.478 647.73 24.35 0.0000 96.75 9.151 623.23 412.6 0.4444 1.39757 0.0000851 61.72 0.005 0.0001

FS24 VaporIN.Fl_O 61.72 10.478 647.80 24.35 0.0000 96.75 9.150 623.29 412.6 0.4444 1.39757 0.0000888 61.72 0.005 0.0001

FS25 Bleed2.Fl_O 61.72 10.478 647.80 24.35 0.0000 96.75 9.150 623.29 412.6 0.4444 1.39757 0.0000888 61.72 0.005 0.0001

FS3 HPC.Fl_O 58.73 137.698 1427.61 219.58 0.0000 10.40 124.228 1389.59 49.7 0.3922 1.35438 0.0000888 58.73 0.005 0.0001

FS36 Bleed3.Fl_O 45.52 137.698 1427.61 219.58 0.0000 8.06 129.872 1405.91 49.3 0.2950 1.35438 0.0000888 45.51 0.004 0.0001

FS4 Burner.Fl_O 46.67 134.527 2922.48 187.34 0.0255 12.10 127.105 2885.75 74.6 0.3007 1.28096 0.0000888 45.51 0.004 0.0307

FS45 HPT.Fl_O 62.16 31.490 1921.38 2.65 0.0190 55.83 28.370 1873.53 265.4 0.4005 1.31732 0.0000888 61.00 0.005 0.0231

FS49 LPT.Fl_O 62.88 7.250 1379.95 -143.09 0.0188 207.90 6.256 1328.62 860.2 0.4725 1.34413 0.0000888 61.72 0.005 0.0228

FS5 TEGV.Fl_O 62.88 7.250 1380.01 -143.09 0.0188 207.91 6.256 1328.69 860.2 0.4725 1.34413 0.0000888 61.72 0.005 0.0228

FS8 Core_Nozz.Fl_O 62.88 7.250 1380.14 -143.09 0.0188 207.92 3.882 1173.55 613.4 1.0000 1.34412 0.0000888 61.72 0.005 0.0228

FS17 FanDuctLkg.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 6.025 534.77 2606.7 0.5227 1.39952 0.0000851 326.10 0.028 0.0001

FS171 Bleed15.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS172 FanDuct.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 5.854 530.41 2481.9 0.5626 1.39952 0.0000851 326.10 0.028 0.0001

FS173 Byp_Nozz.Fl_O 326.13 7.257 563.97 4.20 0.0000 688.63 3.833 469.91 2006.9 1.0000 1.39952 0.0000851 326.10 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1078.79 1.702 0.9114 4139.469 1.1801 0.9178 -9525.9 36.68 23.09

LPC 204.18 2.457 0.8233 4139.469 1.3553 0.8440 -3562.4 2.97 2.24

HPC 96.75 13.142 0.8585 10363.857 2.2038 0.8978 -16636.5 26.01 25.23

HPT 12.10 4.272 0.9122 214.249 1.3428 0.8903 16636.5 

LPT 55.83 4.343 0.9167 90.651 1.3888 0.9005 13088.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1253.45 1.686 0.9132 4100.000 0.0639 0.8607 1.0235 0.9980 0.9905

LPC 166.84 2.748 0.8341 1.093 0.0000 1.2238 0.8335 0.9870 0.0003

HPC 88.00 12.570 0.8673 10087.563 13.4980 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.181 0.9122 1.288 4.1813 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.515 0.9235 1.020 3.5146 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–73
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3912.13 9517.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.2714 1046.36 121.96 31.490

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.7222 1046.36 121.96 7.250

TEGV 0.0000 0.4725 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.23 112.20 38.466

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1246.86 172.73 89.354

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.23 112.20 38.466

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1427.61 219.58 137.698

Splitter 5.2836 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 1007.23 112.20 38.466

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11582.3 7544.0 16636.5 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 647.80 24.35 10.478

LP_Shaft 3973.5 17299.9 13088.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 7.0477 1427.61 219.58 134.527

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 6.1669 1427.61 219.58 75.590

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.61 219.58 137.698

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.61 219.58 137.698

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1427.61 219.58 137.698

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 563.97 4.20 7.257

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2922.48 0.9995 0.0230 1.15888 0.02546 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.540 0.9809 1.0000 0.9800 613.40 1.000 1620.1 3797.1

Byp_Nozz 2.543 0.9810 1.0000 0.9800 2006.86 1.000 1041.7 12523.7

NASA/TM—2013-218094 I–74
************************************************************************************************************************************ 

Date:07/05/13 Time:10:00:50 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 25/ 53/ 2/22 Run by: Philip C Jorgenson PC: 84 

Temperature Stator 1 inlet: 469.59 Stator 1 exit: 487.62 Stator 2 inlet: 508.97 Stator 2 exit: 517.19 

 Stator 3 inlet: 544.04 Stator 3 exit: 552.56 Stator 4 inlet: 577.92 Stator 4 exit: 585.86 

 Stator 5 inlet: 605.83 Stator 5 exit: 613.44 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.44 

Fan Bypass Relative Humidity 0.23 

LPC Inlet Relative Humidity 2.25 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 458.61 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.74 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 460.39 

Additional Water at LPC Exit 0.0000041 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 372.15 5891.0 0.6059 3569.31 5.4133 789.49 29.445 1.518 84.000 2762.8 2595.7 1803.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 372.15 4.267 477.92 -16.44 0.0000 1230.41 2.854 425.97 3753.7 0.7800 1.40068 0.0000851 372.11 0.032 0.0001

FS1 Inlet.Fl_O 372.15 4.267 477.92 -16.44 0.0000 1230.41 3.284 443.45 4168.2 0.6228 1.40068 0.0000851 372.11 0.032 0.0001

FS12 Splitter.Fl_02 314.12 4.265 477.92 -16.44 0.0000 1039.08 3.292 443.82 3531.8 0.6192 1.40068 0.0000851 314.09 0.027 0.0001

FS2 Splitter.Fl_01 58.03 4.265 477.92 -16.44 0.0000 191.95 3.743 460.39 830.5 0.4359 1.40068 0.0000851 58.02 0.005 0.0001

FS14 Fan.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.763 527.41 2606.7 0.5226 1.39966 0.0000851 314.09 0.027 0.0001

FS23 LPC.Fl_O 58.03 10.354 639.92 22.47 0.0000 91.48 9.204 618.81 412.6 0.4139 1.39779 0.0000851 58.02 0.005 0.0001

FS24 VaporIN.Fl_O 58.03 10.354 639.98 22.46 0.0000 91.48 9.204 618.88 412.6 0.4139 1.39779 0.0000891 58.02 0.005 0.0001

FS25 Bleed2.Fl_O 58.03 10.354 639.98 22.46 0.0000 91.48 9.204 618.88 412.6 0.4139 1.39779 0.0000891 58.02 0.005 0.0001

FS3 HPC.Fl_O 55.21 125.632 1378.37 206.71 0.0000 10.53 112.995 1340.35 49.7 0.3977 1.35719 0.0000891 55.21 0.005 0.0001

FS36 Bleed3.Fl_O 42.79 125.632 1378.37 206.71 0.0000 8.16 118.301 1356.70 49.3 0.2987 1.35719 0.0000891 42.79 0.004 0.0001

FS4 Burner.Fl_O 43.78 122.739 2762.79 177.76 0.0232 12.10 115.950 2727.52 74.6 0.2999 1.28688 0.0000891 42.79 0.004 0.0280

FS45 HPT.Fl_O 58.34 28.642 1812.31 2.80 0.0173 55.95 25.791 1766.36 265.4 0.4006 1.32302 0.0000891 57.34 0.005 0.0210

FS49 LPT.Fl_O 59.02 6.587 1297.04 -134.14 0.0171 208.22 5.681 1248.02 860.2 0.4723 1.35025 0.0000891 58.02 0.005 0.0208

FS5 TEGV.Fl_O 59.02 6.587 1297.10 -134.14 0.0171 208.23 5.681 1248.09 860.2 0.4723 1.35025 0.0000891 58.02 0.005 0.0208

FS8 Core_Nozz.Fl_O 59.02 6.587 1297.23 -134.14 0.0171 208.24 3.520 1100.23 613.4 1.0000 1.35024 0.0000891 58.02 0.005 0.0208

FS17 FanDuctLkg.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.763 527.41 2606.7 0.5226 1.39966 0.0000851 314.09 0.027 0.0001

FS171 Bleed15.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.600 523.11 2481.9 0.5626 1.39966 0.0000851 314.09 0.027 0.0001

FS172 FanDuct.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 5.600 523.11 2481.9 0.5626 1.39966 0.0000851 314.09 0.027 0.0001

FS173 Byp_Nozz.Fl_O 314.12 6.942 556.22 2.34 0.0000 688.65 3.666 463.43 2006.9 1.0000 1.39966 0.0000851 314.09 0.027 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1039.08 1.628 0.9120 3982.695 1.1638 0.9179 -8347.4 51.73 26.15

LPC 191.95 2.428 0.8502 3982.695 1.3390 0.8676 -3194.5 2.91 2.10

HPC 91.48 12.133 0.8606 10189.614 2.1538 0.8985 -14760.0 29.68 28.68

HPT 12.10 4.285 0.9109 215.339 1.3490 0.8905 14760.0 

LPT 55.95 4.348 0.9147 89.803 1.3941 0.8982 11542.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1207.30 1.613 0.9139 3944.720 0.0614 0.8607 1.0235 0.9980 0.9905

LPC 152.37 2.575 0.8239 1.052 0.0000 1.2597 0.9066 1.0320 0.0003

HPC 83.20 11.609 0.8695 9917.965 13.1591 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.194 0.9109 1.294 4.1942 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.518 0.9215 1.010 3.5183 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–75
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3753.73 9131.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.1354 1016.81 114.59 28.642

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6789 1016.81 114.59 6.587

TEGV 0.0000 0.4723 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 979.75 105.37 35.715

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1206.85 162.49 81.826

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 979.75 105.37 35.715

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1378.37 206.71 125.632

Splitter 5.4133 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 979.75 105.37 35.715

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11318.7 6848.9 14760.0 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 639.98 22.46 10.354

LP_Shaft 3823.0 15856.4 11542.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.6255 1378.37 206.71 122.739

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.7975 1378.37 206.71 68.916

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.37 206.71 125.632

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.37 206.71 125.632

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1378.37 206.71 125.632

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 556.22 2.34 6.942

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2762.79 0.9995 0.0230 0.99147 0.02317 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.308 0.9816 1.0000 0.9800 613.40 1.000 1572.1 3292.5

Byp_Nozz 2.432 0.9814 1.0000 0.9800 2006.86 1.000 1034.5 11730.2

NASA/TM—2013-218094 I–76
************************************************************************************************************************************ 

Date:07/05/13 Time:10:01:41 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 21/ 49/ 2/18 Run by: Philip C Jorgenson PC: 79 

Temperature Stator 1 inlet: 471.31 Stator 1 exit: 488.90 Stator 2 inlet: 509.91 Stator 2 exit: 518.28 

 Stator 3 inlet: 544.23 Stator 3 exit: 552.77 Stator 4 inlet: 577.30 Stator 4 exit: 585.21 

 Stator 5 inlet: 604.64 Stator 5 exit: 612.16 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.19 

Fan Bypass Relative Humidity 0.25 

LPC Inlet Relative Humidity 2.16 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 446.09 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.77 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 461.34 

Additional Water at LPC Exit 0.0000042 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 366.89 5594.4 0.6047 3382.79 5.4671 789.49 28.508 1.457 79.800 2712.2 2548.9 1770.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 366.89 4.267 477.92 -16.44 0.0000 1213.03 2.854 425.97 3700.7 0.7800 1.40068 0.0000851 366.86 0.031 0.0001

FS1 Inlet.Fl_O 366.89 4.267 477.92 -16.44 0.0000 1213.03 3.325 444.99 4168.2 0.6076 1.40068 0.0000851 366.86 0.031 0.0001

FS12 Splitter.Fl_02 310.16 4.265 477.92 -16.44 0.0000 1025.97 3.328 445.18 3531.8 0.6058 1.40068 0.0000851 310.13 0.026 0.0001

FS2 Splitter.Fl_01 56.73 4.265 477.92 -16.44 0.0000 187.66 3.769 461.34 830.5 0.4235 1.40068 0.0000851 56.73 0.005 0.0001

FS14 Fan.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.677 524.99 2606.7 0.5226 1.39970 0.0000851 310.13 0.026 0.0001

FS23 LPC.Fl_O 56.73 10.299 637.57 21.91 0.0000 89.75 9.204 617.49 412.6 0.4042 1.39785 0.0000851 56.73 0.005 0.0001

FS24 VaporIN.Fl_O 56.73 10.299 637.64 21.90 0.0000 89.76 9.204 617.55 412.6 0.4042 1.39785 0.0000893 56.73 0.005 0.0001

FS25 Bleed2.Fl_O 56.73 10.299 637.64 21.90 0.0000 89.76 9.204 617.55 412.6 0.4042 1.39785 0.0000893 56.73 0.005 0.0001

FS3 HPC.Fl_O 53.98 121.637 1362.67 202.62 0.0000 10.57 109.288 1324.66 49.7 0.3995 1.35810 0.0000893 53.98 0.005 0.0001

FS36 Bleed3.Fl_O 41.83 121.637 1362.67 202.62 0.0000 8.19 114.477 1341.01 49.3 0.3000 1.35810 0.0000893 41.83 0.004 0.0001

FS4 Burner.Fl_O 42.77 118.836 2712.15 174.67 0.0225 12.10 112.262 2677.37 74.6 0.2996 1.28879 0.0000893 41.83 0.004 0.0272

FS45 HPT.Fl_O 57.01 27.706 1778.19 2.85 0.0168 55.99 24.943 1732.85 265.4 0.4007 1.32487 0.0000893 56.06 0.005 0.0204

FS49 LPT.Fl_O 57.67 6.369 1271.25 -131.33 0.0166 208.32 5.492 1222.97 860.2 0.4722 1.35221 0.0000893 56.73 0.005 0.0202

FS5 TEGV.Fl_O 57.67 6.369 1271.31 -131.33 0.0166 208.32 5.492 1223.04 860.2 0.4722 1.35221 0.0000893 56.73 0.005 0.0202

FS8 Core_Nozz.Fl_O 57.67 6.369 1271.44 -131.33 0.0166 208.34 3.402 1077.50 613.4 1.0000 1.35220 0.0000893 56.73 0.005 0.0202

FS17 FanDuctLkg.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.677 524.99 2606.7 0.5226 1.39970 0.0000851 310.13 0.026 0.0001

FS171 Bleed15.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.516 520.71 2481.9 0.5626 1.39970 0.0000851 310.13 0.026 0.0001

FS172 FanDuct.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 5.516 520.71 2481.9 0.5626 1.39970 0.0000851 310.13 0.026 0.0001

FS173 Byp_Nozz.Fl_O 310.16 6.838 553.67 1.73 0.0000 688.65 3.612 461.30 2006.9 1.0000 1.39970 0.0000851 310.13 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1025.97 1.604 0.9117 3933.623 1.1585 0.9174 -7973.6 56.33 27.21

LPC 187.66 2.415 0.8569 3933.623 1.3341 0.8733 -3077.9 3.24 2.50

HPC 89.76 11.811 0.8612 10141.517 2.1371 0.8987 -14154.7 30.96 29.86

HPT 12.10 4.289 0.9102 215.917 1.3509 0.8900 14154.7 

LPT 55.99 4.350 0.9140 89.544 1.3958 0.8973 11051.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1192.08 1.590 0.9136 3896.116 0.0605 0.8607 1.0235 0.9980 0.9905

LPC 149.00 2.524 0.8226 1.039 0.0000 1.2595 0.9285 1.0417 0.0003 

HPC 81.63 11.301 0.8701 9871.151 13.0487 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.198 0.9102 1.298 4.1981 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.519 0.9208 1.007 3.5195 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–77
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3700.70 9002.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0877 1007.47 112.26 27.706

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6638 1007.47 112.26 6.369

TEGV 0.0000 0.4722 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.08 103.22 34.793

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1194.13 159.25 79.329

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.08 103.22 34.793

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1362.67 202.62 121.637

Splitter 5.4671 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 971.08 103.22 34.793

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11244.6 6611.3 14154.7 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 637.64 21.90 10.299

LP_Shaft 3775.9 15372.0 11051.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.4776 1362.67 202.62 118.836

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.6681 1362.67 202.62 66.709

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.67 202.62 121.637

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.67 202.62 121.637

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1362.67 202.62 121.637

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 553.67 1.73 6.838

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2712.14 0.9995 0.0230 0.93966 0.02246 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.232 0.9816 1.0000 0.9800 613.40 1.000 1556.9 3126.7

Byp_Nozz 2.396 0.9814 1.0000 0.9800 2006.86 1.000 1032.2 11470.4

NASA/TM—2013-218094 I–78
************************************************************************************************************************************ 

Date:07/05/13 Time:10:02:15 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 33/ 1/17 Run by: Philip C Jorgenson PC: 76 

Temperature Stator 1 inlet: 472.50 Stator 1 exit: 489.80 Stator 2 inlet: 510.61 Stator 2 exit: 519.07 

 Stator 3 inlet: 544.45 Stator 3 exit: 553.00 Stator 4 inlet: 577.00 Stator 4 exit: 584.89 

 Stator 5 inlet: 603.96 Stator 5 exit: 611.44 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.03 

Fan Bypass Relative Humidity 0.26 

LPC Inlet Relative Humidity 2.11 

LPC Exit Relative Humidity 0.03 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 437.12 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 3.79 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 462.00 

Additional Water at LPC Exit 0.0000043 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 363.05 5383.6 0.6046 3254.95 5.5075 789.49 27.846 1.415 76.800 2677.4 2516.8 1746.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.05 4.267 477.92 -16.44 0.0000 1200.33 2.854 425.97 3662.0 0.7800 1.40068 0.0000851 363.02 0.031 0.0001

FS1 Inlet.Fl_O 363.05 4.267 477.92 -16.44 0.0000 1200.33 3.353 446.06 4168.2 0.5970 1.40068 0.0000851 363.02 0.031 0.0001

FS12 Splitter.Fl_02 307.26 4.265 477.92 -16.44 0.0000 1016.39 3.353 446.13 3531.8 0.5963 1.40068 0.0000851 307.23 0.026 0.0001

FS2 Splitter.Fl_01 55.79 4.265 477.92 -16.44 0.0000 184.55 3.788 462.00 830.5 0.4147 1.40068 0.0000851 55.78 0.005 0.0001

FS14 Fan.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.615 523.30 2606.7 0.5226 1.39973 0.0000851 307.23 0.026 0.0001

FS23 LPC.Fl_O 55.79 10.262 636.11 21.55 0.0000 88.48 9.206 616.74 412.6 0.3972 1.39789 0.0000851 55.78 0.005 0.0001

FS24 VaporIN.Fl_O 55.79 10.262 636.18 21.54 0.0000 88.48 9.206 616.80 412.6 0.3972 1.39789 0.0000894 55.78 0.005 0.0001

FS25 Bleed2.Fl_O 55.79 10.262 636.18 21.54 0.0000 88.48 9.206 616.80 412.6 0.3972 1.39789 0.0000894 55.78 0.005 0.0001

FS3 HPC.Fl_O 53.08 118.809 1351.95 199.84 0.0000 10.60 106.670 1313.93 49.7 0.4008 1.35874 0.0000894 53.08 0.005 0.0001

FS36 Bleed3.Fl_O 41.14 118.809 1351.95 199.84 0.0000 8.22 111.773 1330.32 49.3 0.3008 1.35874 0.0000894 41.14 0.004 0.0001

FS4 Burner.Fl_O 42.04 116.073 2677.38 172.56 0.0220 12.09 109.650 2642.95 74.6 0.2994 1.29010 0.0000894 41.14 0.004 0.0266

FS45 HPT.Fl_O 56.04 27.046 1754.98 2.92 0.0164 56.01 24.346 1710.04 265.4 0.4007 1.32616 0.0000894 55.13 0.005 0.0200

FS49 LPT.Fl_O 56.69 6.216 1253.73 -129.39 0.0162 208.39 5.359 1205.96 860.2 0.4721 1.35355 0.0000894 55.78 0.005 0.0198

FS5 TEGV.Fl_O 56.69 6.216 1253.79 -129.39 0.0162 208.40 5.359 1206.02 860.2 0.4721 1.35355 0.0000894 55.78 0.005 0.0198

FS8 Core_Nozz.Fl_O 56.69 6.216 1253.93 -129.39 0.0162 208.41 3.319 1062.08 613.4 1.0000 1.35354 0.0000894 55.78 0.005 0.0198

FS17 FanDuctLkg.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.615 523.30 2606.7 0.5226 1.39973 0.0000851 307.23 0.026 0.0001

FS171 Bleed15.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.456 519.03 2481.9 0.5626 1.39973 0.0000851 307.23 0.026 0.0001

FS172 FanDuct.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 5.456 519.03 2481.9 0.5626 1.39973 0.0000851 307.23 0.026 0.0001

FS173 Byp_Nozz.Fl_O 307.26 6.764 551.89 1.30 0.0000 688.66 3.572 459.81 2006.9 1.0000 1.39973 0.0000851 307.23 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 1016.39 1.586 0.9105 3900.420 1.1548 0.9162 -7712.9 58.47 27.99

LPC 184.55 2.406 0.8608 3900.420 1.3310 0.8768 -2999.0 3.51 2.79

HPC 88.48 11.578 0.8614 10106.860 2.1251 0.8986 -13732.3 31.89 30.71

HPT 12.09 4.292 0.9097 216.324 1.3520 0.8895 13732.3 

LPT 56.01 4.351 0.9135 89.373 1.3969 0.8967 10712.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 1180.94 1.573 0.9124 3863.230 0.0599 0.8607 1.0235 0.9980 0.9905

LPC 146.85 2.490 0.8219 1.030 0.0000 1.2567 0.9440 1.0473 0.0003

HPC 80.48 11.079 0.8703 9837.418 12.9699 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.201 0.9097 1.300 4.2005 12.6299 0.9723 1.0000 0.0003

LPT 0.86 3.520 0.9203 1.005 3.5204 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 I–79
===INLETS==== eRam Afs Fram 

Inlet 1.0000 3661.98 8908.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 2.0531 1001.16 110.69 27.046

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.6527 1001.16 110.69 6.216

TEGV 0.0000 0.4721 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.24 101.78 34.142

FanDuct 0.0000 0.5626 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 1185.49 157.05 77.561 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.24 101.78 34.142

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1351.95 199.84 118.809

Splitter 5.5075 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 965.24 101.78 34.142

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 11193.3 6443.4 13732.3 WB17Y Bleed> 0.0000 1.0000 1.0000 0.0000 636.18 21.54 10.262

LP_Shaft 3744.1 15027.2 10712.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 6.3701 1351.95 199.84 116.073

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 5.5739 1351.95 199.84 65.149

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1351.95 199.84 118.809

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1351.95 199.84 118.809

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1351.95 199.84 118.809

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 551.89 1.30 6.764

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 2677.36 0.9995 0.0230 0.90415 0.02198 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 2.178 0.9815 1.0000 0.9800 613.40 1.000 1546.4 3009.9

Byp_Nozz 2.370 0.9815 1.0000 0.9800 2006.86 1.000 1030.5 11282.2

NASA/TM—2013-218094 I–80
Appendix J: Compressor code analysis for the altitude cruise conditions at 39000 feet 

 5μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.956 EfDer = 0.985 SH = 0.292440E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.868 3888.739 4.265 457.734 1.000 1.000 0.980

 W Kg/sec = 28.577 Wdry = 62.850 WH2O = 0.018 lbm/sec H2O = 0.106g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 203.570 4139.589 1.381 0.248 53.358 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 167437.078 49323.992 1.395 831.557 595.936 619.754 1.040 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 483.25 -0.17 483.25 0.47 0.83 745.23

 MEAN 17.06 0.00 -0.02 483.25 -0.17 483.25 0.47 0.74

 HUB 12.51 0.00 -0.02 483.25 -0.17 483.25 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.39 50.47 4.92 700.09 850.82 3.66 438.96 450.26 21.85

 MEAN 50.16 47.20 2.96 578.95 754.26 3.66 438.96 450.26 21.85

 HUB 41.31 38.62 2.69 424.53 643.35 3.66 438.96 450.26 21.85

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 725.34 355.07 632.49 1039.22 0.70 7.29 6.52 16.04

 MEAN 18.04 770.25 412.46 650.51 1033.75 0.75 7.43 6.80 12.53

 HUB 15.00 909.83 579.46 701.45 1019.86 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.09 720.48 345.02 0.69 7328.55 0.92 0.90

 MEAN 612.06 680.44 199.60 0.66 7442.02 0.92 0.90 0.90 1.21

 HUB 509.03 704.97 70.42 0.69 8693.92 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.61 1.32 4.07 497.72 1.09 455.42 477.79 14.31

 MEAN 5.64 1.32 3.91 498.34 1.09 450.64 479.08 17.36

 HUB 5.89 1.38 3.53 505.18 1.10 438.62 487.31 28.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.31 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.38 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.56 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 832.1764 411.6610 723.2239 1026.9709 0.8103 -0.1062 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6951 3.7149 444.7459 482.0695 22.8487 29.6486 35.4000 5.7514

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 676.2443 165.4300 655.6976 1048.5519 0.6449 0.2327 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6362 4.2749 463.6583 478.4119 554.9116 0.0414 0.3622

 

NASA/TM—2013-218094 J–1
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 677.9093 0.0000 677.9093 1048.2969 0.6467 0.2581 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.2261 463.4891 478.8769 0.0000 0.0600 0.0716 0.2067

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8253 5.5795 1.3083 500.4125 42.6805 237.2659 1.8393

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 265503.188 0.542 943.267 724249.813 0.494615E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.638 EfDer = 0.990 SH = 0.793530E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.868 3888.739 5.580 500.411 1.000 1.000 0.980

 W Kg/sec = 28.577 Wdry = 62.819 WH2O = 0.050 lbm/sec H2O = 0.329g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 162.689 3959.158 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146133.156 49314.289 1.239 590.487 476.414 468.502 0.983

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 593.93 -0.20 593.93 0.56 0.87 709.99

 MEAN 18.08 0.00 -0.02 593.93 -0.20 593.93 0.56 0.81

 HUB 15.21 0.00 -0.02 593.93 -0.20 593.93 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.59 46.36 3.23 697.38 916.17 4.52 472.10 479.52 14.88

 MEAN 45.94 42.30 3.64 613.50 854.04 4.52 472.10 479.52 14.88

 HUB 41.00 37.84 3.16 516.16 787.01 4.52 472.10 479.52 14.88

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 645.13 277.74 582.28 1086.47 0.59 2.33 2.04 9.02

 MEAN 18.01 664.85 302.33 592.13 1082.85 0.61 2.40 2.13 7.35

 HUB 15.22 725.92 404.25 602.95 1079.61 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 692.97 715.16 415.22 0.66 5675.72 0.92 0.91

 MEAN 611.18 667.83 308.85 0.62 5448.72 0.92 0.91 0.91 1.38

 HUB 516.60 613.32 112.36 0.57 6156.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.80 1.22 5.37 531.32 1.06 497.92 494.59 6.56

 MEAN 6.75 1.21 5.25 530.09 1.06 494.62 494.35 7.31

 HUB 6.91 1.24 5.12 533.95 1.07 491.66 496.95 8.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.50 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 27.05 27.55 23.50 4.05 0.92 0.33 1.63

 HUB 33.84 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 761.3764 303.1825 698.4085 1072.5337 0.7099 -0.2336 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8025 4.8801 485.2846 496.9738 10.1668 23.4659 30.6000 7.1341

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 656.1975 139.1185 641.2809 1085.6792 0.6044 0.0294 2.4513

 

NASA/TM—2013-218094 J–2
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7543 5.2933 497.2445 494.9695 491.5697 0.0407 0.2262

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 697.8997 0.0000 697.8997 1080.7042 0.6458 0.1055 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0830 492.7213 495.8897 0.0000 0.0600 0.0720 -0.1044

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8281 6.7051 1.2017 531.7853 31.3743 278.7588 2.1609

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195584.266 0.407 694.862 654897.250 0.975334E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.069 EfDer = 0.993 SH = 0.123737E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.868 3888.739 6.705 531.784 1.000 1.000 0.980

 W Kg/sec = 28.577 Wdry = 62.791 WH2O = 0.078 lbm/sec H2O = 0.597g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 139.559 3840.597 1.380 0.249 53.388 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 125550.727 49305.676 1.334 545.479 408.813 424.468 1.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 552.38 -0.19 552.38 0.50 0.80 672.64

 MEAN 17.74 0.00 -0.02 552.38 -0.19 552.38 0.50 0.75

 HUB 15.05 0.00 -0.02 552.38 -0.19 552.38 0.50 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.96 46.36 4.60 681.09 877.08 5.65 507.34 494.83 6.90

 MEAN 47.47 43.40 4.07 601.97 817.14 5.65 507.34 494.83 6.90

 HUB 42.77 38.84 3.93 510.73 752.44 5.65 507.34 494.83 6.90

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 615.21 281.46 547.05 1122.67 0.55 2.26 1.98 8.75

 MEAN 17.51 632.92 303.64 555.33 1119.30 0.57 2.34 2.07 6.78

 HUB 14.85 690.58 397.89 564.43 1116.23 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.27 672.30 390.80 0.60 5579.59 0.92 0.91 

 MEAN 594.10 626.70 290.46 0.56 5319.08 0.92 0.91 0.91 1.40

 HUB 503.94 574.31 106.05 0.51 5911.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.20 6.59 562.12 1.06 531.80 507.95 3.73

 MEAN 7.99 1.19 6.45 560.71 1.05 528.61 507.63 4.07

 HUB 8.14 1.21 6.31 563.93 1.06 525.72 509.57 4.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.23 35.54 31.50 4.04 0.93 0.35 1.40

 MEAN 28.67 27.61 23.50 4.11 0.92 0.35 1.62

 HUB 35.18 10.64 6.50 4.14 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 712.9929 305.6331 644.1641 1111.7325 0.6413 -0.2020 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0464 6.1230 521.5485 509.4278 5.0688 25.3827 31.5000 6.1173

 

NASA/TM—2013-218094 J–3
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 620.8176 135.4272 605.8663 1122.1804 0.5532 0.0458 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0080 6.5224 531.3940 508.1455 451.3937 0.0338 0.2603

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 637.3543 0.0000 637.3543 1120.3983 0.5689 0.1532 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4177 529.7348 508.6031 0.0000 0.0600 0.0574 -0.0191

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8494 7.9698 1.1886 562.2511 30.4676 263.7624 2.0447

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 190284.203 0.421 676.032 618774.375 0.156226E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.40068E-02

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.701 EfDer = 0.996 SH = 0.198772E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.868 3888.739 7.970 562.249 1.000 1.000 0.980

 W Kg/sec = 28.577 Wdry = 62.743 WH2O = 0.125 lbm/sec H2O = 1.104g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 120.728 3735.095 1.379 0.250 53.413 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109016.195 49291.098 1.451 513.330 353.825 395.845 1.119

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 509.67 -0.18 509.67 0.45 0.73 627.76

 MEAN 16.97 0.00 -0.02 509.67 -0.18 509.67 0.45 0.68

 HUB 14.32 0.00 -0.02 509.67 -0.18 509.67 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.06 46.36 5.70 653.60 828.96 6.95 541.49 508.27 4.13

 MEAN 48.50 43.80 4.70 575.91 769.18 6.95 541.49 508.27 4.13

 HUB 43.65 37.84 5.81 485.96 704.33 6.95 541.49 508.27 4.13

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 578.94 278.04 507.80 1155.89 0.50 2.16 1.89 8.34

 MEAN 16.57 593.05 293.21 515.50 1152.36 0.51 2.24 1.97 6.35

 HUB 13.89 643.46 373.72 523.81 1149.08 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.70 624.01 362.67 0.54 5252.70 0.92 0.91

 MEAN 562.45 581.57 269.24 0.50 4862.56 0.92 0.91 0.91 1.43

 HUB 471.37 532.83 97.64 0.46 5193.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.39 1.18 7.93 590.73 1.05 563.95 519.32 2.50

 MEAN 9.28 1.16 7.77 588.61 1.05 560.51 518.74 2.71

 HUB 9.38 1.18 7.60 590.41 1.05 557.32 519.91 2.92

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.70 35.53 31.50 4.03 0.93 0.37 1.40

 MEAN 29.63 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.51 10.56 6.50 4.06 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 645.6531 294.8561 574.3935 1148.2881 0.5623 -0.1345 2.1803

 

NASA/TM—2013-218094 J–4
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.3342 7.5540 556.6183 519.7947 3.0070 27.1730 32.4000 5.2270

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 568.9445 127.5976 554.4517 1155.9286 0.4922 0.0867 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.3063 7.9039 564.0523 518.9547 432.2457 0.0276 0.2907

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 564.2897 0.0000 564.2897 1156.3093 0.4880 0.1953 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9016 564.4531 518.9792 0.0000 0.0600 0.0458 0.0852

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8663 9.2775 1.1641 589.8752 27.6669 263.6942 2.0441

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 173245.766 0.422 615.499 606057.188 0.223939E-02

 

Melt Ratio at Stator LE, Throat, TE

0.38079E+00 0.45818E+00 0.67145E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.332 EfDer = 0.998 SH = 0.250580E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 62.868 3888.739 9.277 589.862 1.000 1.000 0.980

 W Kg/sec = 28.577 Wdry = 62.711 WH2O = 0.158 lbm/sec H2O = 1.584g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.229 3646.589 1.378 0.250 53.430 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 95808.156 49281.012 1.636 509.668 311.454 384.739 1.235

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 451.14 -0.16 451.14 0.39 0.66 582.97

 MEAN 15.91 0.00 -0.02 451.14 -0.16 451.14 0.39 0.60

 HUB 13.07 0.00 -0.02 451.14 -0.16 451.14 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.04 47.36 6.68 621.70 768.27 8.38 573.63 518.57 2.36

 MEAN 50.13 44.80 5.33 540.02 703.79 8.38 573.63 518.57 2.36

 HUB 44.52 38.84 5.68 443.54 632.77 8.38 573.63 518.57 2.36

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 534.69 283.40 453.41 1186.67 0.45 2.05 1.78 7.43

 MEAN 15.50 541.93 284.33 461.35 1182.38 0.46 2.13 1.86 5.75

 HUB 12.59 580.03 340.28 469.73 1178.30 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.81 558.09 325.40 0.47 5087.08 0.92 0.91

 MEAN 525.92 520.77 241.59 0.44 4408.96 0.92 0.91 0.91 1.48

 HUB 427.25 477.71 86.97 0.41 4286.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.80 1.16 9.42 617.38 1.05 594.58 528.54 1.58

 MEAN 10.59 1.14 9.19 613.71 1.04 590.29 527.41 1.73

 HUB 10.55 1.14 8.96 613.05 1.04 586.22 527.51 1.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.01 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.65 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.92 10.49 6.50 3.99 0.92 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.495 73.000

 

NASA/TM—2013-218094 J–5
 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 608.0307 289.5475 534.6621 1177.2474 0.5165 -0.2142 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.6182 8.8757 585.2483 528.3457 1.9601 28.4379 33.0000 4.5621

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 541.2700 123.5995 526.9691 1183.3787 0.4574 -0.0041 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.5769 9.1830 591.3664 527.7906 410.5396 0.0483 0.3117

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 523.2385 0.0000 523.2385 1184.8750 0.4416 0.2297 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2761 592.9023 528.0200 0.0000 0.0600 0.0437 0.0597

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8716 10.5837 1.1408 614.7094 24.8492 267.5266 2.0738

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 155926.719 0.421 553.969 610531.000 0.301064E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3429 Tt4 = 614.7094 T1 = 457.7343

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 980544.13 3483.6287 203.5695 2.4817 0.8276 2.9563 1.3429 37.3740

NASA/TM—2013-218094 J–6
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.229 EfDer = 0.994 SH = 0.321684E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.672 3730.491 4.265 457.734 1.000 1.000 0.980

 W Kg/sec = 26.669 Wdry = 58.653 WH2O = 0.019 lbm/sec H2O = 0.118g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 189.982 3971.133 1.381 0.248 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 153501.828 46031.219 1.495 831.557 556.171 619.754 1.114

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 443.03 -0.15 443.03 0.43 0.79 714.90

 MEAN 17.06 0.00 -0.02 443.03 -0.15 443.03 0.43 0.69

 HUB 12.51 0.00 -0.02 443.03 -0.15 443.03 0.43 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.59 50.47 6.12 671.60 804.69 3.76 441.95 450.18 21.10

 MEAN 51.43 47.20 4.23 555.39 710.56 3.76 441.95 450.18 21.10

 HUB 42.60 38.62 3.98 407.26 601.88 3.76 441.95 450.18 21.10

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 677.19 358.27 574.65 1043.92 0.65 7.29 6.52 16.04

 MEAN 18.04 716.63 406.06 590.48 1038.49 0.69 7.43 6.80 12.53

 HUB 15.00 834.62 550.74 627.12 1027.23 0.81 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 671.60 654.53 313.33 0.63 7394.24 0.92 0.91

 MEAN 587.16 617.63 181.10 0.59 7326.25 0.92 0.91 0.91 1.27

 HUB 488.32 630.22 62.42 0.61 8263.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.58 1.31 4.22 496.44 1.08 459.57 476.78 13.68

 MEAN 5.56 1.30 4.06 496.08 1.08 454.80 477.33 16.53

 HUB 5.75 1.35 3.74 500.98 1.09 444.98 483.05 24.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.94 28.60 24.20 4.40 0.93 0.31 1.80

 MEAN 34.52 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.29 -5.68 -9.30 3.62 0.92 0.12 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 764.7976 405.2682 648.5931 1033.9380 0.7397 -0.0878 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6137 3.9188 450.8260 479.4797 20.0359 31.9989 35.4000 3.4011

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 611.5717 149.6091 592.9899 1053.1727 0.5807 0.2736 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5777 4.4508 467.7783 476.7594 554.9116 0.0321 0.3935

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 608.7161 0.0000 608.7161 1053.4418 0.5778 0.3051 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4358 468.0670 477.2218 0.0000 0.0600 0.0512 0.2644

NASA/TM—2013-218094 J–7
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8582 5.5468 1.3006 497.8311 40.0997 228.3272 1.7700

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 249511.688 0.553 827.284 663973.000 0.566654E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.156 EfDer = 0.997 SH = 0.917804E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.672 3730.491 5.547 497.830 1.000 1.000 0.980

 W Kg/sec = 26.669 Wdry = 58.618 WH2O = 0.054 lbm/sec H2O = 0.390g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 152.332 3807.879 1.380 0.249 53.378 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 132934.984 46020.441 1.324 590.487 446.119 468.502 1.050 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 540.29 -0.19 540.29 0.51 0.81 682.86

 MEAN 18.08 0.00 -0.02 540.29 -0.19 540.29 0.51 0.75

 HUB 15.21 0.00 -0.02 540.29 -0.19 540.29 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.08 46.36 4.72 669.00 860.07 4.66 474.41 478.24 16.03

 MEAN 47.46 42.30 5.16 588.53 799.06 4.66 474.41 478.24 16.03

 HUB 42.52 37.84 4.68 495.16 732.99 4.66 474.41 478.24 16.03

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 604.49 286.05 532.52 1087.66 0.56 2.33 2.04 9.02

 MEAN 18.01 621.75 304.52 542.07 1083.77 0.57 2.40 2.13 7.35

 HUB 15.22 678.18 393.49 552.35 1080.21 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 664.77 653.45 378.71 0.60 5845.05 0.92 0.91

 MEAN 586.31 610.94 281.79 0.56 5487.78 0.92 0.91 0.91 1.41

 HUB 495.58 561.70 102.09 0.52 5992.99 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.22 5.49 528.36 1.06 499.05 493.60 7.42

 MEAN 6.68 1.20 5.36 526.49 1.06 495.48 493.04 8.32

 HUB 6.79 1.22 5.22 529.13 1.06 492.24 495.07 9.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.24 35.42 31.50 3.92 0.93 0.36 1.40

 MEAN 29.33 27.47 23.50 3.97 0.92 0.35 1.63

 HUB 35.47 10.47 6.50 3.97 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 700.6050 305.3759 630.5497 1076.2041 0.6510 -0.2017 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7297 5.0798 488.6353 495.1284 10.6138 25.8410 30.6000 4.7590

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 593.7252 125.8740 580.2287 1088.3552 0.5455 0.0925 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7008 5.4874 499.7279 493.3820 491.5697 0.0309 0.2654

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 624.1708 0.0000 624.1708 1085.0934 0.5752 0.1626 0.5911

NASA/TM—2013-218094 J–8
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3480 496.7600 494.0768 0.0000 0.0600 0.0506 -0.0082

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8621 6.6735 1.2031 527.9922 30.1627 262.6159 2.0358

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188110.422 0.426 623.701 597635.750 0.111916E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.501 EfDer = 0.998 SH = 0.141422E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.672 3730.491 6.673 527.991 1.000 1.000 0.980

 W Kg/sec = 26.669 Wdry = 58.589 WH2O = 0.083 lbm/sec H2O = 0.698g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 130.392 3697.519 1.380 0.249 53.394 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 114531.000 46011.449 1.428 545.479 382.003 424.468 1.111

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 503.90 -0.17 503.90 0.46 0.75 647.58

 MEAN 17.74 0.00 -0.02 503.90 -0.17 503.90 0.46 0.70

 HUB 15.05 0.00 -0.02 503.90 -0.17 503.90 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.37 46.36 6.01 653.37 825.25 5.79 507.66 493.58 7.97

 MEAN 48.90 43.40 5.50 577.47 766.54 5.79 507.66 493.58 7.97

 HUB 44.21 38.84 5.37 489.95 702.95 5.79 507.66 493.58 7.97

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 577.96 287.69 501.27 1121.76 0.52 2.26 1.98 8.75

 MEAN 17.51 593.26 304.40 509.21 1118.20 0.53 2.34 2.07 6.78

 HUB 14.85 646.34 386.83 517.79 1114.90 0.58 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 644.91 615.53 357.21 0.55 5702.68 0.92 0.91

 MEAN 569.92 574.28 265.52 0.51 5332.11 0.92 0.91 0.91 1.44

 HUB 483.44 526.73 96.60 0.47 5747.11 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.01 1.20 6.70 557.72 1.06 530.97 506.82 4.43

 MEAN 7.92 1.19 6.55 555.79 1.05 527.61 506.27 4.86

 HUB 8.02 1.20 6.41 557.95 1.06 524.50 507.79 5.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.85 35.47 31.50 3.97 0.93 0.38 1.40

 MEAN 30.87 27.54 23.50 4.04 0.92 0.37 1.62

 HUB 36.76 10.57 6.50 4.07 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 660.9047 306.3995 585.5889 1112.3943 0.5941 -0.1801 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9669 6.2945 522.2003 507.8059 5.7689 27.6201 31.5000 3.8799

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 564.4445 123.1298 550.8509 1122.4244 0.5029 0.1031 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9432 6.6991 531.6604 506.5762 451.3937 0.0266 0.2940

 

NASA/TM—2013-218094 J–9
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 576.7849 0.0000 576.7849 1121.2098 0.5144 0.2001 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6291 530.5375 506.9825 0.0000 0.0600 0.0421 0.0541

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8732 7.9210 1.1869 557.1514 29.1625 249.6301 1.9351

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182236.594 0.438 604.226 568860.563 0.175359E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.19850E-03 0.27949E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.998 EfDer = 0.999 SH = 0.218433E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.672 3730.491 7.921 557.149 1.000 1.000 0.980

 W Kg/sec = 26.669 Wdry = 58.544 WH2O = 0.128 lbm/sec H2O = 1.236g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 112.848 3599.461 1.378 0.250 53.419 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99900.172 45997.477 1.552 513.330 330.774 395.845 1.197

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 467.05 -0.16 467.05 0.41 0.69 604.96

 MEAN 16.97 0.00 -0.02 467.05 -0.16 467.05 0.41 0.64

 HUB 14.32 0.00 -0.02 467.05 -0.16 467.05 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.32 46.36 6.96 627.00 781.96 7.06 539.73 506.86 4.88

 MEAN 49.80 43.80 6.00 552.48 723.56 7.06 539.73 506.86 4.88

 HUB 44.96 37.84 7.12 466.18 660.01 7.06 539.73 506.86 4.88

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 545.59 281.63 467.28 1152.87 0.47 2.16 1.89 8.34

 MEAN 16.57 557.31 292.41 474.43 1149.28 0.48 2.24 1.97 6.35

 HUB 13.89 603.40 362.85 482.11 1145.91 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 614.63 573.79 333.00 0.50 5320.33 0.92 0.91

 MEAN 539.56 534.95 247.15 0.47 4849.10 0.92 0.91 0.91 1.47

 HUB 452.18 490.32 89.33 0.43 5042.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.31 1.18 8.00 584.80 1.05 561.03 517.92 3.01

 MEAN 9.18 1.16 7.84 582.35 1.05 557.55 517.19 3.28

 HUB 9.23 1.17 7.67 583.36 1.05 554.28 518.06 3.54

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.08 35.48 31.50 3.98 0.93 0.39 1.40

 MEAN 31.65 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 36.97 10.50 6.50 4.00 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 603.0541 294.0549 526.5036 1146.0436 0.5262 -0.1229 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2283 7.6623 554.4721 518.1260 3.5612 29.1836 32.4000 3.2164

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 521.0874 116.8647 507.8137 1153.6063 0.4517 0.1335 2.2705

 

NASA/TM—2013-218094 J–10
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2105 8.0229 561.8190 517.2712 432.2457 0.0226 0.3189

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 516.7417 0.0000 516.7417 1153.9226 0.4478 0.2290 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0209 562.1555 517.3063 0.0000 0.0600 0.0401 0.1320

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8780 9.1859 1.1597 583.4614 26.3564 251.0231 1.9459

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 165134.828 0.437 547.523 560799.125 0.244114E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.42101E+00 0.50271E+00 0.72732E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.422 EfDer = 1.000 SH = 0.271121E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.672 3730.491 9.186 583.448 1.000 1.000 0.980

 W Kg/sec = 26.669 Wdry = 58.513 WH2O = 0.159 lbm/sec H2O = 1.733g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 99.581 3517.370 1.377 0.251 53.436 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 88410.000 45987.895 1.745 509.668 291.999 384.739 1.318

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 416.31 -0.14 416.31 0.36 0.63 562.31

 MEAN 15.91 0.00 -0.02 416.31 -0.14 416.31 0.36 0.57

 HUB 13.07 0.00 -0.02 416.31 -0.14 416.31 0.36 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.09 47.36 7.73 596.40 727.45 8.42 569.63 517.00 2.88

 MEAN 51.22 44.80 6.42 518.04 664.70 8.42 569.63 517.00 2.88

 HUB 45.63 38.84 6.79 425.49 595.38 8.42 569.63 517.00 2.88

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 506.61 283.07 420.14 1181.41 0.43 2.05 1.78 7.43

 MEAN 15.50 511.53 281.26 427.27 1177.26 0.43 2.13 1.86 5.75

 HUB 12.59 545.65 329.70 434.78 1173.27 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 584.03 516.82 300.96 0.44 5080.87 0.92 0.91

 MEAN 504.52 482.08 223.26 0.41 4361.07 0.92 0.91 0.91 1.51

 HUB 409.86 442.11 80.16 0.38 4152.83 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.65 1.16 9.40 609.80 1.05 589.35 526.89 1.98

 MEAN 10.43 1.14 9.18 606.07 1.04 585.21 525.70 2.16

 HUB 10.37 1.13 8.96 604.98 1.04 581.26 525.64 2.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.97 35.62 31.50 4.12 0.93 0.43 1.40

 MEAN 33.36 27.59 23.50 4.09 0.93 0.40 1.64

 HUB 37.17 10.45 6.50 3.95 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 570.2795 286.4127 493.1394 1172.9910 0.4862 -0.2017 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4570 8.9177 581.0491 526.5702 2.4098 30.1478 33.0000 2.8522

 

NASA/TM—2013-218094 J–11
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 498.4995 113.8328 485.3286 1179.1355 0.4228 0.0458 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4296 9.2406 587.1623 525.9971 410.5396 0.0410 0.3352

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 482.7251 0.0000 482.7251 1180.3386 0.4090 0.2572 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.3136 588.4004 526.2427 0.0000 0.0600 0.0394 0.1019

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 10.4317 1.1356 606.9485 23.5023 256.9289 1.9917

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 147571.266 0.433 489.289 568535.250 0.326972E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3260 Tt4 = 606.9485 T1 = 457.7338

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 932564.81 3092.0244 189.9818 2.4461 0.8546 4.2285 1.3260 37.3740

NASA/TM—2013-218094 J–12
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.681 EfDer = 0.996 SH = 0.331267E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.329 3685.723 4.265 457.734 1.000 1.000 0.980

 W Kg/sec = 26.059 Wdry = 57.310 WH2O = 0.019 lbm/sec H2O = 0.123g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 185.632 3923.478 1.381 0.248 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149218.063 44977.160 1.530 831.557 543.441 619.754 1.140

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 430.67 -0.15 430.67 0.42 0.77 706.33

 MEAN 17.06 0.00 -0.02 430.67 -0.15 430.67 0.42 0.68

 HUB 12.51 0.00 -0.02 430.67 -0.15 430.67 0.42 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.02 50.47 6.55 663.54 791.18 3.78 442.82 450.17 20.93

 MEAN 51.88 47.20 4.68 548.72 697.66 3.78 442.82 450.17 20.93

 HUB 43.07 38.62 4.45 402.37 589.49 3.78 442.82 450.17 20.93

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 663.34 359.75 557.31 1045.27 0.63 7.29 6.52 16.04

 MEAN 18.04 701.07 404.56 572.56 1039.82 0.67 7.43 6.80 12.53

 HUB 15.00 813.54 542.71 606.06 1029.13 0.79 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 663.54 634.73 303.79 0.61 7424.78 0.92 0.91

 MEAN 580.11 598.87 175.55 0.58 7299.27 0.92 0.91 0.91 1.29

 HUB 482.46 609.05 60.25 0.59 8142.53 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.57 1.31 4.26 496.13 1.08 460.76 476.55 13.54

 MEAN 5.54 1.30 4.10 495.48 1.08 455.97 476.88 16.35

 HUB 5.71 1.34 3.80 499.84 1.09 446.64 482.01 23.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.84 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 35.24 17.05 12.70 4.35 0.92 0.28 2.22

 HUB 41.84 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 745.9208 403.7791 627.1844 1035.7756 0.7202 -0.0831 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5918 3.9740 452.4366 478.8516 19.4637 32.7733 35.4000 2.6267

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 592.6028 144.9688 574.5974 1054.4623 0.5620 0.2870 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5606 4.4993 468.9312 476.3253 554.9116 0.0301 0.4037

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 589.1432 0.0000 589.1432 1054.7864 0.5585 0.3189 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4898 469.2677 476.7964 0.0000 0.0600 0.0467 0.2809

NASA/TM—2013-218094 J–13
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8656 5.5348 1.2978 497.1466 39.4153 225.2947 1.7465

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 245271.656 0.557 794.607 645443.438 0.590288E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.657 EfDer = 0.999 SH = 0.958107E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.329 3685.723 5.535 497.146 1.000 1.000 0.980

 W Kg/sec = 26.059 Wdry = 57.274 WH2O = 0.055 lbm/sec H2O = 0.410g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 149.065 3764.771 1.380 0.249 53.379 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 129053.852 44966.090 1.353 590.487 436.562 468.502 1.073

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 524.51 -0.18 524.51 0.49 0.80 675.13

 MEAN 18.08 0.00 -0.02 524.51 -0.18 524.51 0.49 0.74

 HUB 15.21 0.00 -0.02 524.51 -0.18 524.51 0.49 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.57 46.36 5.21 660.97 843.94 4.69 475.08 477.91 16.39

 MEAN 47.96 42.30 5.66 581.47 783.22 4.69 475.08 477.91 16.39

 HUB 43.02 37.84 5.18 489.21 717.37 4.69 475.08 477.91 16.39

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 592.89 288.88 517.75 1088.04 0.54 2.33 2.04 9.02

 MEAN 18.01 609.31 305.51 527.18 1084.08 0.56 2.40 2.13 7.35

 HUB 15.22 664.26 390.59 537.29 1080.44 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.79 635.16 367.91 0.58 5902.68 0.92 0.91

 MEAN 579.27 594.02 273.76 0.55 5505.54 0.92 0.91 0.91 1.43

 HUB 489.63 546.34 99.04 0.51 5948.73 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.74 1.22 5.53 527.60 1.06 499.41 493.35 7.68

 MEAN 6.66 1.20 5.39 525.55 1.06 495.77 492.69 8.63

 HUB 6.75 1.22 5.25 527.84 1.06 492.45 494.54 9.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.16 35.40 31.50 3.90 0.93 0.37 1.40

 MEAN 30.09 27.44 23.50 3.94 0.92 0.36 1.63

 HUB 36.02 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 683.6736 306.3704 611.1848 1077.1730 0.6347 -0.1933 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7059 5.1302 489.5229 494.6527 10.7796 26.6234 30.6000 3.9766

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 575.7977 122.0732 562.7087 1089.0945 0.5287 0.1116 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6812 5.5365 500.4160 492.9595 491.5697 0.0286 0.2774

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 603.9087 0.0000 603.9087 1086.1779 0.5560 0.1788 0.5911

NASA/TM—2013-218094 J–14
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4119 497.7621 493.6128 0.0000 0.0600 0.0457 0.0180

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8693 6.6583 1.2030 526.9953 29.8504 257.6257 1.9971

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186188.094 0.432 603.194 580324.750 0.116611E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.962 EfDer = 0.999 SH = 0.147182E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.329 3685.723 6.658 526.994 1.000 1.000 0.980

 W Kg/sec = 26.059 Wdry = 57.244 WH2O = 0.084 lbm/sec H2O = 0.730g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 127.576 3656.600 1.379 0.250 53.396 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111327.992 44956.996 1.459 545.479 373.767 424.468 1.136

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 489.81 -0.17 489.81 0.45 0.74 640.41

 MEAN 17.74 0.00 -0.02 489.81 -0.17 489.81 0.45 0.69

 HUB 15.05 0.00 -0.02 489.81 -0.17 489.81 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.82 46.36 6.46 645.53 810.46 5.82 507.79 493.24 8.30

 MEAN 49.36 43.40 5.96 570.54 752.08 5.82 507.79 493.24 8.30

 HUB 44.67 38.84 5.83 484.07 688.76 5.82 507.79 493.24 8.30

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 567.45 289.73 487.90 1121.55 0.51 2.26 1.98 8.75

 MEAN 17.51 581.94 304.83 495.72 1117.94 0.52 2.34 2.07 6.78

 HUB 14.85 633.60 383.80 504.13 1114.59 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 637.17 598.97 347.44 0.53 5742.92 0.92 0.91

 MEAN 563.08 558.95 258.26 0.50 5339.43 0.92 0.91 0.91 1.46

 HUB 477.64 512.79 93.84 0.46 5701.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.99 1.20 6.72 556.57 1.06 530.79 506.52 4.65

 MEAN 7.89 1.18 6.57 554.49 1.05 527.38 505.90 5.11

 HUB 7.98 1.20 6.43 556.36 1.06 524.22 507.29 5.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.70 35.45 31.50 3.95 0.93 0.39 1.40

 MEAN 31.59 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 37.28 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 646.3152 306.8255 568.8422 1112.5804 0.5809 -0.1741 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9366 6.3339 522.3848 507.3680 5.9893 28.3418 31.5000 3.1582

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 548.3519 119.6193 535.1458 1122.5073 0.4885 0.1204 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9161 6.7392 531.7500 506.1460 451.3937 0.0249 0.3043

 

NASA/TM—2013-218094 J–15
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 559.9796 0.0000 559.9796 1121.3934 0.4994 0.2124 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6743 530.7222 506.5391 0.0000 0.0600 0.0400 0.0732

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8769 7.8953 1.1858 555.8030 28.8115 245.3456 1.9019

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180076.406 0.444 583.394 553516.000 0.181692E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.12727E-02 0.35577E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.404 EfDer = 1.000 SH = 0.225122E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.329 3685.723 7.895 555.800 1.000 1.000 0.980

 W Kg/sec = 26.059 Wdry = 57.200 WH2O = 0.129 lbm/sec H2O = 1.278g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.491 3560.576 1.378 0.250 53.421 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 97289.266 44943.172 1.585 513.330 323.877 395.845 1.222

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 454.84 -0.16 454.84 0.40 0.68 598.43

 MEAN 16.97 0.00 -0.02 454.84 -0.16 454.84 0.40 0.63

 HUB 14.32 0.00 -0.02 454.84 -0.16 454.84 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.72 46.36 7.36 619.48 768.65 7.07 539.28 506.47 5.12

 MEAN 50.20 43.80 6.40 545.85 710.63 7.07 539.28 506.47 5.12

 HUB 45.37 37.84 7.53 460.59 647.43 7.07 539.28 506.47 5.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 536.25 282.76 455.64 1152.07 0.47 2.16 1.89 8.34

 MEAN 16.57 547.22 292.28 462.62 1148.48 0.48 2.24 1.97 6.35

 HUB 13.89 592.00 359.81 470.11 1145.08 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 607.26 559.38 324.50 0.49 5341.53 0.92 0.91

 MEAN 533.08 521.54 240.80 0.45 4846.84 0.92 0.91 0.91 1.48

 HUB 446.76 478.08 86.95 0.42 4999.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.27 1.17 8.01 583.23 1.05 560.27 517.53 3.18

 MEAN 9.14 1.16 7.84 580.69 1.04 556.78 516.75 3.46

 HUB 9.18 1.16 7.67 581.47 1.05 553.49 517.53 3.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.82 35.46 31.50 3.96 0.93 0.40 1.40

 MEAN 32.28 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.43 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 591.1202 293.9220 512.8674 1145.4469 0.5161 -0.1196 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1837 7.6783 553.9044 517.6575 3.7377 29.8168 32.4000 2.5832

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 507.5142 113.8206 494.5862 1152.9872 0.4402 0.1475 2.2705

 

NASA/TM—2013-218094 J–16
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1681 8.0407 561.2266 516.7943 432.2457 0.0215 0.3279

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 503.2680 0.0000 503.2680 1153.2847 0.4364 0.2394 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0387 561.5445 516.8325 0.0000 0.0600 0.0389 0.1460

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8803 9.1445 1.1582 581.7498 25.9946 247.2629 1.9168

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 162899.547 0.442 527.746 546665.313 0.251045E-02

 

Melt Ratio at Stator LE, Throat, TE

0.43423E+00 0.51730E+00 0.74559E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.767 EfDer = 1.000 SH = 0.278245E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.329 3685.723 9.145 581.736 1.000 1.000 0.980

 W Kg/sec = 26.059 Wdry = 57.169 WH2O = 0.160 lbm/sec H2O = 1.781g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.598 3480.268 1.377 0.251 53.439 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 86276.836 44933.730 1.781 509.668 286.195 384.739 1.344

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 406.26 -0.14 406.26 0.35 0.62 556.38

 MEAN 15.91 0.00 -0.02 406.26 -0.14 406.26 0.35 0.56

 HUB 13.07 0.00 -0.02 406.26 -0.14 406.26 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.42 47.36 8.06 589.24 715.84 8.41 568.58 516.55 3.05

 MEAN 51.57 44.80 6.77 511.83 653.57 8.41 568.58 516.55 3.05

 HUB 45.99 38.84 7.15 420.38 584.71 8.41 568.58 516.55 3.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 498.67 283.13 410.50 1180.01 0.42 2.05 1.78 7.43

 MEAN 15.50 502.89 280.49 417.39 1175.90 0.43 2.13 1.86 5.75

 HUB 12.59 535.82 326.74 424.66 1171.94 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 577.02 504.86 293.89 0.43 5081.93 0.92 0.91

 MEAN 498.47 470.88 217.97 0.40 4349.21 0.92 0.91 0.91 1.53

 HUB 404.94 431.81 78.20 0.37 4115.52 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.59 1.16 9.38 607.77 1.04 587.96 526.42 2.11

 MEAN 10.37 1.13 9.16 604.02 1.04 583.87 525.22 2.31

 HUB 10.30 1.13 8.94 602.82 1.04 579.94 525.11 2.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.59 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.90 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.58 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 559.6099 285.6375 481.2218 1171.8561 0.4775 -0.1980 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3937 8.9126 579.9352 526.0668 2.5561 30.6920 33.0000 2.3080

 

NASA/TM—2013-218094 J–17
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 486.2952 111.0459 473.4467 1178.0009 0.4128 0.0608 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3695 9.2385 586.0439 525.4850 410.5396 0.0393 0.3428

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 471.1067 0.0000 471.1067 1179.1298 0.3995 0.2659 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.3064 587.2068 525.7370 0.0000 0.0600 0.0384 0.1148

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 10.3706 1.1341 604.8686 23.1342 253.7067 1.9667

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 145293.875 0.436 470.709 555150.188 0.336129E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3214 Tt4 = 604.8686 T1 = 457.7336 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 919729.56 2979.6504 185.6321 2.4317 0.8602 4.6809 1.3214 37.3740

NASA/TM—2013-218094 J–18
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.020 EfDer = 0.997 SH = 0.338190E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.365 3655.387 4.265 457.733 1.000 1.000 0.980

 W Kg/sec = 25.621 Wdry = 56.346 WH2O = 0.019 lbm/sec H2O = 0.126g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 182.513 3891.185 1.381 0.248 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146192.234 44221.211 1.556 831.557 534.311 619.754 1.160

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 421.93 -0.15 421.93 0.41 0.76 700.51

 MEAN 17.06 0.00 -0.02 421.93 -0.15 421.93 0.41 0.67

 HUB 12.51 0.00 -0.02 421.93 -0.15 421.93 0.41 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.34 50.47 6.87 658.08 781.85 3.80 443.42 450.16 20.83

 MEAN 52.22 47.20 5.02 544.21 688.73 3.80 443.42 450.16 20.83

 HUB 43.41 38.62 4.79 399.06 580.85 3.80 443.42 450.16 20.83

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 653.84 360.97 545.16 1046.19 0.62 7.29 6.52 16.04

 MEAN 18.04 690.37 403.70 560.03 1040.74 0.66 7.43 6.80 12.53

 HUB 15.00 799.13 537.28 591.56 1030.40 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 658.08 620.86 297.11 0.59 7449.88 0.92 0.91

 MEAN 575.34 585.74 171.64 0.56 7283.59 0.92 0.91 0.91 1.30

 HUB 478.49 594.47 58.79 0.58 8060.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.29 495.94 1.08 461.57 476.40 13.45

 MEAN 5.53 1.30 4.13 495.09 1.08 456.77 476.59 16.24

 HUB 5.68 1.33 3.83 499.07 1.09 447.74 481.32 23.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.51 28.59 24.20 4.39 0.93 0.33 1.80

 MEAN 35.79 17.04 12.70 4.34 0.92 0.29 2.22

 HUB 42.25 -5.68 -9.30 3.62 0.92 0.14 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 733.0459 402.9140 612.3859 1037.0099 0.7069 -0.0800 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5773 4.0112 453.5201 478.4485 19.1150 33.3426 35.4000 2.0574

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 579.3846 141.7352 561.7808 1055.3529 0.5490 0.2967 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5489 4.5323 469.7284 476.0406 554.9116 0.0288 0.4113

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 575.6277 0.0000 575.6277 1055.7001 0.5453 0.3287 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5259 470.0846 476.5185 0.0000 0.0600 0.0439 0.2925

NASA/TM—2013-218094 J–19
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8701 5.5261 1.2958 496.6977 38.9666 223.0624 1.7292

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 242491.484 0.560 772.398 632355.125 0.607458E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.026 EfDer = 0.999 SH = 0.987513E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.365 3655.387 5.526 496.697 1.000 1.000 0.980

 W Kg/sec = 25.621 Wdry = 56.310 WH2O = 0.056 lbm/sec H2O = 0.424g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 146.723 3735.472 1.380 0.249 53.380 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126342.203 44209.930 1.374 590.487 429.712 468.502 1.090

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 513.49 -0.18 513.49 0.48 0.78 669.87

 MEAN 18.08 0.00 -0.02 513.49 -0.18 513.49 0.48 0.73

 HUB 15.21 0.00 -0.02 513.49 -0.18 513.49 0.48 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.94 46.36 5.58 655.53 832.84 4.72 475.55 477.68 16.63

 MEAN 48.33 42.30 6.03 576.68 772.30 4.72 475.55 477.68 16.63

 HUB 43.39 37.84 5.55 485.19 706.58 4.72 475.55 477.68 16.63

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 584.94 291.06 507.39 1088.34 0.54 2.33 2.04 9.02

 MEAN 18.01 600.71 306.37 516.72 1084.33 0.55 2.40 2.13 7.35

 HUB 15.22 654.58 388.67 526.71 1080.62 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 651.38 622.32 360.33 0.57 5947.00 0.92 0.91

 MEAN 574.50 582.14 268.13 0.54 5520.93 0.92 0.91 0.91 1.44

 HUB 485.60 535.55 96.94 0.50 5919.38 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.74 1.22 5.55 527.12 1.06 499.68 493.19 7.85

 MEAN 6.64 1.20 5.41 524.94 1.06 496.00 492.47 8.84

 HUB 6.73 1.22 5.27 526.98 1.06 492.62 494.20 9.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.84 35.38 31.50 3.88 0.93 0.38 1.40

 MEAN 30.66 27.43 23.50 3.93 0.93 0.37 1.63

 HUB 36.42 10.43 6.50 3.93 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 672.0918 307.2313 597.7595 1077.8456 0.6236 -0.1876 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6894 5.1639 490.1398 494.3465 10.8986 27.2019 30.6000 3.3981

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 563.3353 119.4311 550.5296 1089.6263 0.5170 0.1252 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6672 5.5695 500.9112 492.6851 491.5697 0.0271 0.2861

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 589.9905 0.0000 589.9905 1086.9229 0.5428 0.1903 0.5911

NASA/TM—2013-218094 J–20
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4541 498.4514 493.3135 0.0000 0.0600 0.0427 0.0361

 

 STAGE EXIT CONDITIONS, STAGE 2 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8736 6.6471 1.2029 526.3497 29.6537 254.0446 1.9693

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184979.359 0.436 589.207 568139.813 0.120054E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.303 EfDer = 1.000 SH = 0.151423E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.365 3655.387 6.647 526.349 1.000 1.000 0.980

 W Kg/sec = 25.621 Wdry = 56.280 WH2O = 0.085 lbm/sec H2O = 0.754g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 125.567 3628.727 1.379 0.250 53.397 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109090.266 44200.762 1.483 545.479 367.891 424.468 1.154

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 479.96 -0.17 479.96 0.44 0.73 635.53

 MEAN 17.74 0.00 -0.02 479.96 -0.17 479.96 0.44 0.68

 HUB 15.05 0.00 -0.02 479.96 -0.17 479.96 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.15 46.36 6.79 640.22 800.28 5.84 507.91 493.02 8.54

 MEAN 49.70 43.40 6.30 565.84 742.11 5.84 507.91 493.02 8.54

 HUB 45.02 38.84 6.18 480.08 678.97 5.84 507.91 493.02 8.54

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 560.24 291.34 478.53 1121.46 0.50 2.26 1.98 8.75

 MEAN 17.51 574.14 305.29 486.25 1117.82 0.51 2.34 2.07 6.78

 HUB 14.85 624.77 381.78 494.55 1114.42 0.56 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 631.92 587.36 340.59 0.52 5774.67 0.92 0.91

 MEAN 558.45 548.20 253.15 0.49 5347.54 0.92 0.91 0.91 1.47

 HUB 473.70 503.02 91.92 0.45 5671.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.97 1.20 6.74 555.84 1.06 530.71 506.34 4.81

 MEAN 7.87 1.18 6.59 553.66 1.05 527.27 505.66 5.29

 HUB 7.95 1.20 6.44 555.31 1.06 524.07 506.97 5.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.33 35.44 31.50 3.94 0.93 0.40 1.40

 MEAN 32.12 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.67 10.53 6.50 4.03 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 636.3046 307.2950 557.1833 1112.7450 0.5718 -0.1699 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9152 6.3599 522.5469 507.0866 6.1431 28.8774 31.5000 2.6226

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 537.1346 117.1723 524.1987 1122.6124 0.4785 0.1329 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8966 6.7659 531.8577 505.8672 451.3937 0.0239 0.3120

 

NASA/TM—2013-218094 J–21
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 548.3262 0.0000 548.3262 1121.5607 0.4889 0.2212 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7039 530.8885 506.2513 0.0000 0.0600 0.0390 0.0866

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8788 7.8763 1.1849 554.9330 28.5874 242.2579 1.8780

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 178700.547 0.448 569.208 542633.625 0.186375E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.22074E-02 0.41645E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.706 EfDer = 1.000 SH = 0.230087E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.365 3655.387 7.876 554.930 1.000 1.000 0.980

 W Kg/sec = 25.621 Wdry = 56.236 WH2O = 0.130 lbm/sec H2O = 1.309g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 108.810 3534.039 1.378 0.250 53.423 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 95460.469 44187.043 1.609 513.330 318.959 395.845 1.241

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 446.29 -0.15 446.29 0.39 0.67 593.97

 MEAN 16.97 0.00 -0.02 446.29 -0.15 446.29 0.39 0.62

 HUB 14.32 0.00 -0.02 446.29 -0.15 446.29 0.39 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.01 46.36 7.65 614.38 759.49 7.08 539.03 506.22 5.28

 MEAN 50.51 43.80 6.71 541.35 701.72 7.08 539.03 506.22 5.28

 HUB 45.68 37.84 7.84 456.80 638.73 7.08 539.03 506.22 5.28

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 529.83 283.73 447.45 1151.59 0.46 2.16 1.89 8.34

 MEAN 16.57 540.24 292.33 454.32 1147.99 0.47 2.24 1.97 6.35

 HUB 13.89 584.09 357.79 461.68 1144.57 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 602.26 549.24 318.52 0.48 5359.87 0.92 0.91 

 MEAN 528.69 512.13 236.36 0.45 4847.64 0.92 0.91 0.91 1.49

 HUB 443.08 469.49 85.29 0.41 4971.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.25 1.17 8.01 582.22 1.05 559.81 517.28 3.29

 MEAN 9.11 1.16 7.84 579.61 1.04 556.31 516.47 3.58

 HUB 9.14 1.16 7.67 580.24 1.05 553.01 517.19 3.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.38 35.45 31.50 3.95 0.93 0.41 1.40

 MEAN 32.76 27.49 23.50 3.99 0.93 0.40 1.62

 HUB 37.77 10.47 6.50 3.97 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 582.8724 293.9735 503.3088 1145.1012 0.5090 -0.1173 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1522 7.6884 553.5776 517.3536 3.8600 30.2884 32.4000 2.1116

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 497.9973 111.6862 485.3118 1152.6327 0.4321 0.1579 2.2705

 

NASA/TM—2013-218094 J–22
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1379 8.0521 560.8893 516.4832 432.2457 0.0208 0.3346

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 493.8250 0.0000 493.8250 1152.9169 0.4283 0.2470 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0500 561.1942 516.5233 0.0000 0.0600 0.0381 0.1563

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8817 9.1150 1.1573 580.6454 25.7614 244.5324 1.8956

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161461.891 0.445 514.298 536565.500 0.256180E-02

 

Melt Ratio at Stator LE, Throat, TE

0.44509E+00 0.52924E+00 0.76045E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.026 EfDer = 1.000 SH = 0.283524E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.365 3655.387 9.115 580.631 1.000 1.000 0.980

 W Kg/sec = 25.621 Wdry = 56.206 WH2O = 0.160 lbm/sec H2O = 1.816g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 96.177 3454.905 1.377 0.251 53.440 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 84773.141 44177.707 1.807 509.668 282.039 384.739 1.364

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 399.18 -0.14 399.18 0.34 0.61 552.33

 MEAN 15.91 0.00 -0.02 399.18 -0.14 399.18 0.34 0.56

 HUB 13.07 0.00 -0.02 399.18 -0.14 399.18 0.34 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.67 47.36 8.31 584.39 707.83 8.41 567.94 516.26 3.16

 MEAN 51.83 44.80 7.03 507.61 645.88 8.41 567.94 516.26 3.16

 HUB 46.25 38.84 7.41 416.92 577.31 8.41 567.94 516.26 3.16

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 493.21 283.38 403.67 1179.14 0.42 2.05 1.78 7.43

 MEAN 15.50 496.89 280.11 410.41 1175.04 0.42 2.13 1.86 5.75

 HUB 12.59 528.97 324.80 417.52 1171.10 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 572.27 496.40 288.89 0.42 5086.44 0.92 0.91

 MEAN 494.36 462.97 214.25 0.39 4343.26 0.92 0.91 0.91 1.53

 HUB 401.61 424.52 76.82 0.36 4090.99 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.54 1.16 9.37 606.47 1.04 587.09 526.13 2.21

 MEAN 10.33 1.13 9.15 602.70 1.04 583.03 524.91 2.41

 HUB 10.25 1.12 8.93 601.41 1.04 579.12 524.76 2.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.07 35.59 31.50 4.09 0.93 0.44 1.40

 MEAN 34.31 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.88 10.42 6.50 3.92 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 552.1951 285.2490 472.8133 1171.1597 0.4715 -0.1953 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3496 8.9086 579.2543 525.7427 2.6594 31.1026 33.0000 1.8974

 

NASA/TM—2013-218094 J–23
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 477.6880 109.0805 465.0669 1177.3104 0.4057 0.0718 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3273 9.2365 585.3660 525.1536 410.5396 0.0382 0.3486

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 462.8999 0.0000 462.8999 1178.3892 0.3928 0.2724 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.3010 586.4783 525.4110 0.0000 0.0600 0.0378 0.1245

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8814 10.3278 1.1331 603.5269 22.8970 251.3175 1.9482

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 143830.109 0.439 458.136 545511.750 0.343105E-02

 

Melt Ratio at Stator LE, Throat, TE

 0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3185 Tt4 = 603.5269 T1 = 457.7335

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 911463.38 2903.2476 182.5126 2.4217 0.8634 5.0203 1.3185 37.3740

NASA/TM—2013-218094 J–24
5μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 3.082 EfDer = 0.986 SH = 0.658166E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.298 3973.534 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 27.863 Wdry = 61.257 WH2O = 0.040 lbm/sec H2O = 0.228g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 202.817 4139.589 1.381 0.249 53.370 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 170325.938 48084.855 1.400 831.557 593.874 619.754 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 491.59 -0.17 491.59 0.47 0.83 745.23

 MEAN 17.06 0.00 -0.02 491.59 -0.17 491.59 0.47 0.74

 HUB 12.51 0.00 -0.02 491.59 -0.17 491.59 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.51 50.47 5.04 715.36 868.12 3.67 458.51 464.09 18.67

 MEAN 50.28 47.20 3.08 591.57 769.29 3.67 458.51 464.09 18.67

 HUB 41.44 38.62 2.82 433.79 655.73 3.67 458.51 464.09 18.67

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 738.48 365.13 641.89 1062.46 0.70 7.29 6.52 16.04

 MEAN 18.04 784.13 422.73 660.43 1056.78 0.74 7.43 6.80 12.53

 HUB 15.00 925.29 591.49 711.54 1042.74 0.89 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.36 731.22 350.23 0.69 7536.18 0.92 0.90

 MEAN 625.41 690.83 202.68 0.65 7627.28 0.92 0.90 0.90 1.22

 HUB 520.13 715.11 71.36 0.69 8874.47 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.62 1.32 4.09 519.89 1.09 476.09 489.75 12.42

 MEAN 5.64 1.32 3.93 520.39 1.09 471.02 491.30 14.93

 HUB 5.89 1.38 3.55 527.34 1.10 458.59 500.34 23.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.63 28.62 24.20 4.42 0.93 0.27 1.80

 MEAN 32.62 17.06 12.70 4.36 0.91 0.23 2.22

 HUB 39.74 -5.73 -9.30 3.57 0.91 0.07 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 846.1885 421.9100 733.5032 1050.0707 0.8058 -0.1042 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7005 3.7356 465.0706 494.7288 19.1810 29.9074 35.4000 5.4926

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 685.5095 167.6965 664.6812 1072.1124 0.6394 0.2388 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6439 4.3009 484.8307 489.7952 554.9116 0.0404 0.3669

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 686.5549 0.0000 686.5549 1071.9382 0.6405 0.2650 1.3089

NASA/TM—2013-218094 J–25
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.2564 484.7294 490.4254 0.0000 0.0600 0.0692 0.2149

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8290 5.5903 1.3109 522.5373 44.6241 236.2108 1.8311

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 278031.813 0.543 963.101 682869.750 0.107727E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.847 EfDer = 0.992 SH = 0.165259E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.298 3973.534 5.590 522.536 1.000 1.000 0.980

 W Kg/sec = 27.863 Wdry = 61.196 WH2O = 0.101 lbm/sec H2O = 0.658g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 161.782 3958.917 1.379 0.250 53.402 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 148237.344 48066.043 1.246 590.487 474.005 468.502 0.988

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 602.46 -0.21 602.46 0.56 0.86 709.94

 MEAN 18.08 0.00 -0.02 602.46 -0.21 602.46 0.56 0.80

 HUB 15.21 0.00 -0.02 602.46 -0.21 602.46 0.56 0.74

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.80 46.36 3.44 712.58 933.29 4.54 493.49 491.27 12.67

 MEAN 46.15 42.30 3.85 626.87 869.59 4.54 493.49 491.27 12.67

 HUB 41.21 37.84 3.37 527.42 800.84 4.54 493.49 491.27 12.67

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 656.12 287.56 589.75 1110.86 0.59 2.33 2.04 9.02

 MEAN 18.01 676.15 311.56 600.09 1107.02 0.61 2.40 2.13 7.35

 HUB 15.22 738.36 414.03 611.36 1103.59 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.08 724.32 420.52 0.65 5876.21 0.92 0.91

 MEAN 624.51 676.79 312.95 0.61 5614.93 0.92 0.91 0.91 1.38

 HUB 527.87 621.87 113.84 0.56 6305.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.83 1.22 5.41 555.15 1.06 520.70 504.82 5.83

 MEAN 6.77 1.21 5.28 553.70 1.06 517.11 504.69 6.47

 HUB 6.93 1.24 5.15 557.53 1.07 513.90 507.36 7.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.99 35.49 31.50 3.99 0.93 0.33 1.40

 MEAN 27.44 27.54 23.50 4.04 0.92 0.33 1.63

 HUB 34.11 10.55 6.50 4.05 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 772.5948 312.4346 706.6027 1096.8654 0.7044 -0.2288 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.8272 4.9232 507.7173 507.7538 8.6889 23.8533 30.6000 6.7467

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 663.3660 140.6383 648.2864 1110.3417 0.5974 0.0409 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7818 5.3446 520.2644 505.1204 491.5697 0.0391 0.2335

 

NASA/TM—2013-218094 J–26
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 704.2371 0.0000 704.2371 1105.5408 0.6370 0.1162 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1444 515.8025 506.2628 0.0000 0.0600 0.0684 -0.0873

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8341 6.7360 1.2049 555.4608 32.9250 276.0848 2.1402

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 205842.891 0.411 713.039 617138.438 0.197303E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.344 EfDer = 0.994 SH = 0.242212E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.298 3973.534 6.736 555.460 1.000 1.000 0.980

 W Kg/sec = 27.863 Wdry = 61.149 WH2O = 0.148 lbm/sec H2O = 1.125g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 138.431 3839.798 1.378 0.250 53.427 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 127059.273 48051.441 1.344 545.479 405.804 424.468 1.046

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 559.01 -0.19 559.01 0.50 0.80 672.50

 MEAN 17.74 0.00 -0.02 559.01 -0.19 559.01 0.50 0.74

 HUB 15.05 0.00 -0.02 559.01 -0.19 559.01 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.23 46.36 4.87 695.94 892.80 5.70 530.52 504.88 5.94

 MEAN 47.74 43.40 4.34 615.09 831.30 5.70 530.52 504.88 5.94

 HUB 43.04 38.84 4.20 521.87 764.88 5.70 530.52 504.88 5.94

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 625.20 292.09 552.77 1148.01 0.54 2.26 1.98 8.75

 MEAN 17.51 643.05 313.47 561.47 1144.43 0.56 2.34 2.07 6.78

 HUB 14.85 701.60 407.73 570.97 1141.17 0.61 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 679.30 394.83 0.59 5790.19 0.92 0.91

 MEAN 607.05 633.59 293.58 0.55 5491.21 0.92 0.91 0.91 1.41

 HUB 514.93 580.94 107.21 0.51 6057.64 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.12 1.20 6.65 587.51 1.06 556.31 516.99 3.24

 MEAN 8.04 1.19 6.51 585.85 1.05 552.85 516.72 3.53

 HUB 8.18 1.22 6.36 588.99 1.06 549.70 518.67 3.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.85 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.17 27.60 23.50 4.10 0.92 0.35 1.62

 HUB 35.53 10.63 6.50 4.13 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 722.9099 315.5276 650.4160 1136.9980 0.6358 -0.1976 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0978 6.1918 545.7632 518.6771 4.2564 25.8788 31.5000 5.6212

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 626.1937 136.5999 611.1129 1147.7892 0.5456 0.0592 2.3726

 

NASA/TM—2013-218094 J–27
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0622 6.6037 556.1670 517.0048 451.3937 0.0322 0.2687

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 642.1859 0.0000 642.1859 1146.0715 0.5603 0.1648 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5060 554.5398 517.3615 0.0000 0.0600 0.0540 -0.0017

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8558 8.0272 1.1917 587.4222 31.9900 260.6328 2.0204

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 200566.109 0.425 694.760 583129.313 0.277592E-02

 

Melt Ratio at Stator LE, Throat, TE

0.19317E+00 0.25134E+00 0.42964E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.041 EfDer = 0.997 SH = 0.313532E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.298 3973.534 8.027 587.413 1.000 1.000 0.980

 W Kg/sec = 27.863 Wdry = 61.106 WH2O = 0.192 lbm/sec H2O = 1.682g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 119.458 3733.876 1.377 0.251 53.450 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110066.711 48037.883 1.465 513.330 350.365 395.845 1.130

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 514.58 -0.18 514.58 0.44 0.73 627.55

 MEAN 16.97 0.00 -0.02 514.58 -0.18 514.58 0.44 0.68

 HUB 14.32 0.00 -0.02 514.58 -0.18 514.58 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.39 46.36 6.03 667.85 843.24 7.02 566.33 516.45 3.06

 MEAN 48.84 43.80 5.04 588.47 781.86 7.02 566.33 516.45 3.06

 HUB 43.99 37.84 6.15 496.56 715.22 7.02 566.33 516.45 3.06

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 587.98 289.09 512.00 1182.06 0.50 2.16 1.89 8.34

 MEAN 16.57 601.97 303.20 520.04 1178.33 0.51 2.24 1.97 6.35

 HUB 13.89 652.93 383.17 528.68 1174.85 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.68 629.13 365.59 0.53 5461.34 0.92 0.91

 MEAN 574.71 586.65 271.51 0.50 5028.24 0.92 0.91 0.91 1.44

 HUB 481.64 537.77 98.47 0.46 5324.80 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.49 1.18 8.03 617.55 1.05 590.02 526.86 1.86

 MEAN 9.36 1.17 7.86 615.16 1.05 586.31 526.28 2.01

 HUB 9.45 1.18 7.68 616.79 1.05 582.85 527.38 2.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.45 35.53 31.50 4.03 0.93 0.38 1.40

 MEAN 30.24 27.57 23.50 4.07 0.92 0.37 1.62

 HUB 35.93 10.55 6.50 4.05 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 654.3503 304.9074 578.9696 1174.3334 0.5572 -0.1312 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.4173 7.6509 582.4193 527.3039 2.1963 27.7730 32.4000 4.6270

 

NASA/TM—2013-218094 J–28
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 572.7943 128.4610 558.2034 1182.3246 0.4845 0.1013 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.3918 8.0173 590.3746 526.3921 432.2457 0.0262 0.2999

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 568.0605 0.0000 568.0605 1182.7161 0.4803 0.2066 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.0159 590.8081 526.6425 0.0000 0.0600 0.0439 0.1004

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8695 9.3639 1.1665 616.4741 29.0870 260.0436 2.0158

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 182812.063 0.427 633.260 571097.063 0.354373E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.690 EfDer = 0.999 SH = 0.461357E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.298 3973.534 9.364 616.472 1.000 1.000 0.980

 W Kg/sec = 27.863 Wdry = 61.015 WH2O = 0.283 lbm/sec H2O = 2.818g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 104.907 3644.834 1.375 0.252 53.498 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96667.180 48009.672 1.655 509.668 307.972 384.739 1.249

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 455.15 -0.16 455.15 0.38 0.66 582.69

 MEAN 15.91 0.00 -0.02 455.15 -0.16 455.15 0.38 0.60

 HUB 13.07 0.00 -0.02 455.15 -0.16 455.15 0.38 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.39 47.36 7.03 635.26 781.61 8.48 600.06 527.09 2.16

 MEAN 50.49 44.80 5.69 551.79 715.41 8.48 600.06 527.09 2.16

 HUB 44.89 38.84 6.05 453.21 642.42 8.48 600.06 527.09 2.16

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 543.49 294.22 456.97 1213.35 0.45 2.05 1.78 7.43

 MEAN 15.50 550.22 293.90 465.15 1208.89 0.46 2.13 1.86 5.75

 HUB 12.59 588.38 348.90 473.77 1204.64 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 562.42 327.86 0.46 5281.11 0.92 0.91

 MEAN 537.39 525.03 243.49 0.43 4557.19 0.92 0.91 0.91 1.49

 HUB 436.57 481.81 87.67 0.40 4394.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.93 1.17 9.54 645.48 1.05 622.08 536.99 1.55

 MEAN 10.70 1.14 9.31 641.51 1.04 617.53 535.92 1.69

 HUB 10.65 1.14 9.07 640.61 1.04 613.19 536.08 1.83

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.78 35.66 31.50 4.16 0.93 0.41 1.40

 MEAN 32.29 27.63 23.50 4.13 0.92 0.39 1.64

 HUB 36.37 10.48 6.50 3.98 0.92 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 616.2851 299.2861 538.7347 1203.8163 0.5119 -0.2102 2.0437

 

NASA/TM—2013-218094 J–29
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.7319 9.0018 612.4994 537.0165 1.8831 29.0537 33.0000 3.9463

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 544.6537 124.3721 530.2634 1210.2542 0.4500 0.0143 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.6942 9.3290 619.0821 536.2677 410.5396 0.0460 0.3210

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 526.7328 0.0000 526.7328 1211.6909 0.4347 0.2409 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4186 620.6104 536.5475 0.0000 0.0600 0.0419 0.0760

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8736 10.7001 1.1427 642.5328 26.0614 263.4045 2.0419

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 164802.906 0.426 570.876 575759.125 0.567688E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3444 Tt4 = 642.5328 T1 = 477.9153

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1032055.75 3575.0349 202.8167 2.5091 0.8320 3.0820 1.3444 37.3740

NASA/TM—2013-218094 J–30
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.264 EfDer = 0.994 SH = 0.714125E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.524 3826.412 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 26.147 Wdry = 57.483 WH2O = 0.041 lbm/sec H2O = 0.252g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 190.329 3986.318 1.381 0.249 53.371 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 157251.328 45123.285 1.492 831.557 557.332 619.754 1.112

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 453.85 -0.16 453.85 0.43 0.79 717.64

 MEAN 17.06 0.00 -0.02 453.85 -0.16 453.85 0.43 0.70

 HUB 12.51 0.00 -0.02 453.85 -0.16 453.85 0.43 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH 

 TIP 56.63 50.47 6.16 688.87 825.07 3.75 461.38 463.98 18.11

 MEAN 51.46 47.20 4.26 569.67 728.48 3.75 461.38 463.98 18.11

 HUB 42.64 38.62 4.02 417.73 616.94 3.75 461.38 463.98 18.11

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 693.68 368.28 587.84 1066.83 0.65 7.29 6.52 16.04

 MEAN 18.04 734.15 416.89 604.30 1061.19 0.69 7.43 6.80 12.53

 HUB 15.00 855.22 564.80 642.18 1049.57 0.81 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 688.87 669.58 320.59 0.63 7600.88 0.92 0.91

 MEAN 602.25 632.09 185.37 0.60 7521.65 0.92 0.91 0.91 1.27

 HUB 500.88 645.36 63.92 0.61 8473.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.59 1.31 4.22 518.67 1.09 480.04 488.79 11.93

 MEAN 5.58 1.31 4.06 518.24 1.08 474.97 489.65 14.28

 HUB 5.76 1.35 3.74 523.35 1.10 464.63 496.14 20.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.07 28.61 24.20 4.41 0.93 0.31 1.80

 MEAN 34.60 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.33 -5.68 -9.30 3.62 0.92 0.12 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 783.5024 416.0772 663.8944 1056.5221 0.7416 -0.0876 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6263 3.9214 470.8380 492.1416 17.1178 32.0763 35.4000 3.3237

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 625.2844 152.9636 606.2859 1076.3750 0.5809 0.2762 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5903 4.4606 488.7259 488.3144 554.9116 0.0321 0.3955

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 622.3589 0.0000 622.3589 1076.6556 0.5780 0.3075 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4457 489.0290 488.9396 0.0000 0.0600 0.0510 0.2671

NASA/TM—2013-218094 J–31
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8582 5.5594 1.3036 520.0862 42.1736 227.9504 1.7671

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 262866.625 0.554 854.505 630451.000 0.120455E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.241 EfDer = 0.998 SH = 0.186289E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.524 3826.412 5.559 520.085 1.000 1.000 0.980

 W Kg/sec = 26.147 Wdry = 57.417 WH2O = 0.107 lbm/sec H2O = 0.759g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 152.306 3821.309 1.379 0.250 53.409 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 135953.203 45102.879 1.323 590.487 446.299 468.502 1.050

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 552.53 -0.19 552.53 0.51 0.81 685.26

 MEAN 18.08 0.00 -0.02 552.53 -0.19 552.53 0.51 0.76

 HUB 15.21 0.00 -0.02 552.53 -0.19 552.53 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.17 46.36 4.81 686.20 881.15 4.67 495.67 490.26 13.46

 MEAN 47.54 42.30 5.24 603.66 818.50 4.67 495.67 490.26 13.46

 HUB 42.60 37.84 4.76 507.89 750.63 4.67 495.67 490.26 13.46

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 618.63 295.18 543.67 1111.87 0.56 2.33 2.04 9.02

 MEAN 18.01 636.28 313.55 553.66 1107.81 0.57 2.40 2.13 7.35

 HUB 15.22 694.08 404.02 564.37 1104.10 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 681.86 667.16 386.68 0.60 6031.47 0.92 0.91

 MEAN 601.38 624.01 287.83 0.56 5650.53 0.92 0.91 0.91 1.42

 HUB 508.32 573.93 104.30 0.52 6153.28 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.22 5.52 552.30 1.06 521.69 504.10 6.47

 MEAN 6.71 1.21 5.38 550.26 1.06 517.89 503.70 7.22

 HUB 6.82 1.23 5.24 552.95 1.06 514.42 505.86 7.97

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.50 35.42 31.50 3.92 0.93 0.36 1.40

 MEAN 29.52 27.47 23.50 3.97 0.92 0.36 1.63

 HUB 35.60 10.47 6.50 3.97 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 716.6194 314.4338 643.9524 1100.1393 0.6514 -0.2003 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7584 5.1009 510.7903 506.1612 9.0263 26.0257 30.6000 4.5743

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 605.8253 128.4393 592.0538 1112.6825 0.5445 0.0977 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7298 5.5163 522.5034 503.8249 491.5697 0.0305 0.2688

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 636.7656 0.0000 636.7656 1109.3843 0.5740 0.1669 0.5911

NASA/TM—2013-218094 J–32
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3776 519.4379 504.7159 0.0000 0.0600 0.0498 -0.0020

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8633 6.7030 1.2057 551.8376 31.7530 261.4886 2.0270

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 198652.969 0.427 645.764 567504.188 0.221471E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.640 EfDer = 0.999 SH = 0.271416E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.524 3826.412 6.703 551.837 1.000 1.000 0.980

 W Kg/sec = 26.147 Wdry = 57.368 WH2O = 0.156 lbm/sec H2O = 1.286g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 130.120 3709.746 1.378 0.250 53.436 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 116901.203 45087.711 1.430 545.479 381.511 424.468 1.113 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 514.31 -0.18 514.31 0.46 0.75 649.72

 MEAN 17.74 0.00 -0.02 514.31 -0.18 514.31 0.46 0.70

 HUB 15.05 0.00 -0.02 514.31 -0.18 514.31 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.50 46.36 6.14 670.17 844.92 5.81 530.74 503.98 6.74

 MEAN 49.04 43.40 5.64 592.32 784.58 5.81 530.74 503.98 6.74

 HUB 44.35 38.84 5.51 502.55 719.20 5.81 530.74 503.98 6.74

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 591.13 297.43 510.85 1146.98 0.52 2.26 1.98 8.75

 MEAN 17.51 606.67 313.88 519.15 1143.26 0.53 2.34 2.07 6.78

 HUB 14.85 660.92 397.38 528.11 1139.81 0.58 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.49 627.30 364.06 0.55 5895.67 0.92 0.91

 MEAN 584.57 585.49 270.69 0.51 5498.16 0.92 0.91 0.91 1.45

 HUB 495.87 537.21 98.49 0.47 5903.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.20 6.75 583.23 1.06 555.36 516.17 3.77

 MEAN 7.97 1.19 6.59 581.11 1.05 551.76 515.70 4.12

 HUB 8.07 1.20 6.44 583.28 1.06 548.44 517.29 4.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.21 35.48 31.50 3.98 0.93 0.38 1.40

 MEAN 31.16 27.54 23.50 4.04 0.92 0.38 1.62

 HUB 36.96 10.56 6.50 4.06 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 675.3282 315.9428 596.8655 1137.3955 0.5937 -0.1783 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0175 6.3380 546.1914 517.3909 4.7785 27.8939 31.5000 3.6061

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 574.8554 125.4008 561.0110 1147.7662 0.5008 0.1098 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9944 6.7522 556.1969 515.7699 451.3937 0.0261 0.2987

 

NASA/TM—2013-218094 J–33
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 587.2360 0.0000 587.2360 1146.5314 0.5122 0.2059 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6839 555.0359 516.0781 0.0000 0.0600 0.0412 0.0623

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8756 7.9727 1.1894 582.5072 30.7036 248.1028 1.9233

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 192670.188 0.440 626.316 539995.500 0.306900E-02

 

Melt Ratio at Stator LE, Throat, TE

0.23321E+00 0.30155E+00 0.50495E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.197 EfDer = 1.000 SH = 0.342235E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.524 3826.412 7.973 582.496 1.000 1.000 0.980

 W Kg/sec = 26.147 Wdry = 57.327 WH2O = 0.197 lbm/sec H2O = 1.864g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 112.396 3610.765 1.377 0.251 53.459 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 101749.234 45075.063 1.557 513.330 329.708 395.845 1.201

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 475.70 -0.16 475.70 0.41 0.69 606.86

 MEAN 16.97 0.00 -0.02 475.70 -0.16 475.70 0.41 0.64

 HUB 14.32 0.00 -0.02 475.70 -0.16 475.70 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.52 46.36 7.16 643.12 800.07 7.11 564.50 515.38 3.57

 MEAN 50.00 43.80 6.20 566.68 740.00 7.11 564.50 515.38 3.57

 HUB 45.16 37.84 7.32 478.17 674.60 7.11 564.50 515.38 3.57

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 557.68 291.73 475.29 1178.99 0.47 2.16 1.89 8.34

 MEAN 16.57 569.42 301.97 482.76 1175.24 0.48 2.24 1.97 6.35

 HUB 13.89 616.36 372.91 490.76 1171.71 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.44 583.62 338.70 0.50 5511.10 0.92 0.91

 MEAN 553.43 544.32 251.46 0.46 5007.54 0.92 0.91 0.91 1.48

 HUB 463.81 499.10 90.90 0.43 5182.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.39 1.18 8.08 611.75 1.05 587.01 525.76 2.21

 MEAN 9.26 1.16 7.90 609.08 1.05 583.29 525.06 2.40

 HUB 9.31 1.17 7.73 610.01 1.05 579.79 525.91 2.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.54 35.47 31.50 3.97 0.93 0.40 1.40

 MEAN 32.03 27.51 23.50 4.01 0.93 0.39 1.62

 HUB 37.23 10.49 6.50 3.99 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 615.6907 303.6649 535.5956 1171.9895 0.5253 -0.1212 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.3051 7.7322 580.1357 526.0196 2.5888 29.5518 32.4000 2.8482

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 529.6134 118.7768 516.1225 1179.8707 0.4489 0.1425 2.2705

 

NASA/TM—2013-218094 J–34
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2879 8.1056 587.9731 525.1302 432.2457 0.0222 0.3247

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 525.2487 0.0000 525.2487 1180.1982 0.4451 0.2359 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1033 588.3463 525.4238 0.0000 0.0600 0.0394 0.1409

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8778 9.2635 1.1619 610.2676 27.7833 249.0408 1.9305

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 174760.359 0.440 568.096 532081.375 0.391479E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.642 EfDer = 1.000 SH = 0.505604E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.524 3826.412 9.264 610.266 1.000 1.000 0.980

 W Kg/sec = 26.147 Wdry = 57.233 WH2O = 0.291 lbm/sec H2O = 3.113g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 99.012 3527.684 1.374 0.252 53.512 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89978.656 45045.777 1.753 509.668 290.743 384.739 1.323

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 423.66 -0.15 423.66 0.36 0.63 563.96

 MEAN 15.91 0.00 -0.02 423.66 -0.15 423.66 0.36 0.57

 HUB 13.07 0.00 -0.02 423.66 -0.15 423.66 0.36 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.30 47.36 7.94 611.74 744.24 8.50 596.07 526.03 2.62

 MEAN 51.44 44.80 6.64 531.36 679.70 8.50 596.07 526.03 2.62

 HUB 45.86 38.84 7.02 436.43 608.35 8.50 596.07 526.03 2.62

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 518.02 293.14 427.09 1208.16 0.43 2.05 1.78 7.43

 MEAN 15.50 522.65 290.49 434.48 1203.86 0.43 2.13 1.86 5.75

 HUB 12.59 557.18 338.90 442.27 1199.73 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 599.05 525.35 305.91 0.43 5261.59 0.92 0.91

 MEAN 517.49 490.21 227.00 0.41 4504.30 0.92 0.91 0.91 1.52

 HUB 420.40 449.72 81.50 0.37 4268.64 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.76 1.16 9.50 638.06 1.05 616.83 535.79 1.91

 MEAN 10.54 1.14 9.28 634.06 1.04 612.45 534.69 2.08

 HUB 10.47 1.13 9.05 632.82 1.04 608.26 534.72 2.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.46 35.61 31.50 4.11 0.93 0.43 1.40

 MEAN 33.77 27.59 23.50 4.09 0.93 0.41 1.64

 HUB 37.46 10.44 6.50 3.94 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 582.1994 295.8217 501.4436 1199.5399 0.4854 -0.1995 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5614 9.0148 608.2124 535.7182 2.2876 30.5381 33.0000 2.4619

 

NASA/TM—2013-218094 J–35
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 506.4637 115.6514 493.0824 1205.9325 0.4200 0.0566 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.5349 9.3512 614.7300 534.9374 410.5396 0.0402 0.3413

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 490.5074 0.0000 490.5074 1207.1168 0.4063 0.2643 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4236 615.9953 535.2488 0.0000 0.0600 0.0387 0.1118

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8790 10.5369 1.1375 634.9806 24.7157 254.3984 1.9721

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 156495.703 0.436 508.723 539600.125 0.618368E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3286 Tt4 = 634.9806 T1 = 477.9148

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 985445.81 3203.4050 190.3293 2.4708 0.8548 4.2635 1.3286 37.3740

NASA/TM—2013-218094 J–36
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.725 EfDer = 0.996 SH = 0.734100E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.189 3780.265 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 25.540 Wdry = 56.148 WH2O = 0.041 lbm/sec H2O = 0.260g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 185.913 3938.243 1.381 0.249 53.372 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 152800.797 44076.039 1.527 831.557 544.409 619.754 1.138

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 441.01 -0.15 441.01 0.42 0.77 708.98

 MEAN 17.06 0.00 -0.02 441.01 -0.15 441.01 0.42 0.68

 HUB 12.51 0.00 -0.02 441.01 -0.15 441.01 0.42 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.06 50.47 6.59 680.56 811.09 3.78 462.30 463.95 17.96

 MEAN 51.93 47.20 4.73 562.80 715.12 3.78 462.30 463.95 17.96

 HUB 43.11 38.62 4.49 412.69 604.09 3.78 462.30 463.95 17.97

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 679.37 369.88 569.85 1068.22 0.64 7.29 6.52 16.04

 MEAN 18.04 718.05 415.39 585.70 1062.58 0.68 7.43 6.80 12.53

 HUB 15.00 833.35 556.51 620.30 1051.55 0.79 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 680.56 649.04 310.69 0.61 7633.71 0.92 0.91

 MEAN 594.99 612.62 179.60 0.58 7494.63 0.92 0.91 0.91 1.29

 HUB 494.84 623.36 61.67 0.59 8349.48 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.58 1.31 4.27 518.35 1.08 481.29 488.53 11.80

 MEAN 5.56 1.30 4.11 517.61 1.08 476.22 489.18 14.12

 HUB 5.72 1.34 3.80 522.14 1.09 466.39 495.00 20.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.99 28.60 24.20 4.40 0.93 0.33 1.80

 MEAN 35.35 17.05 12.70 4.35 0.92 0.28 2.22

 HUB 41.90 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 763.9448 414.5860 641.6620 1058.4299 0.7218 -0.0828 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6042 3.9776 472.5507 491.4481 16.6317 32.8670 35.4000 2.5330

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 605.6283 148.1552 587.2271 1077.7102 0.5620 0.2898 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5730 4.5099 489.9490 487.8853 554.9116 0.0300 0.4059

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 602.0840 0.0000 602.0840 1078.0471 0.5585 0.3215 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5006 490.3018 488.5205 0.0000 0.0600 0.0465 0.2838

NASA/TM—2013-218094 J–37
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8656 5.5472 1.3008 519.3649 41.4524 224.8604 1.7431

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 258404.609 0.558 820.511 612608.000 0.125019E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.751 EfDer = 0.999 SH = 0.193851E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.189 3780.265 5.547 519.364 1.000 1.000 0.980

 W Kg/sec = 25.540 Wdry = 56.080 WH2O = 0.109 lbm/sec H2O = 0.795g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 148.995 3777.844 1.379 0.250 53.411 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 131932.844 44055.141 1.352 590.487 436.617 468.502 1.073

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 536.19 -0.18 536.19 0.49 0.80 677.47

 MEAN 18.08 0.00 -0.02 536.19 -0.18 536.19 0.49 0.74

 HUB 15.21 0.00 -0.02 536.19 -0.18 536.19 0.49 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.67 46.36 5.31 677.92 864.49 4.70 496.38 489.96 13.73

 MEAN 48.05 42.30 5.75 596.38 802.12 4.70 496.38 489.96 13.73

 HUB 43.11 37.84 5.27 501.76 734.48 4.70 496.38 489.96 13.73

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 606.72 298.10 528.43 1112.25 0.55 2.33 2.04 9.02

 MEAN 18.01 623.46 314.59 538.27 1108.12 0.56 2.40 2.13 7.35

 HUB 15.22 679.70 401.01 548.80 1104.32 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 673.64 648.28 375.54 0.58 6090.98 0.92 0.91

 MEAN 594.13 606.53 279.54 0.55 5669.09 0.92 0.91 0.91 1.43

 HUB 502.19 558.05 101.19 0.51 6107.34 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.22 5.55 551.50 1.06 522.06 503.91 6.68

 MEAN 6.69 1.21 5.41 549.27 1.06 518.19 503.42 7.47

 HUB 6.78 1.22 5.27 551.58 1.06 514.64 505.40 8.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.43 35.40 31.50 3.90 0.93 0.37 1.40

 MEAN 30.30 27.44 23.50 3.94 0.92 0.36 1.63

 HUB 36.16 10.45 6.50 3.95 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 699.1879 315.4728 623.9717 1101.1228 0.6350 -0.1920 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7340 5.1517 511.7176 505.7137 9.1606 26.8206 30.6000 3.7794

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 587.3621 124.5249 574.0103 1113.4248 0.5275 0.1168 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7097 5.5656 523.2161 503.4477 491.5697 0.0282 0.2809

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 615.9294 0.0000 615.9294 1110.4766 0.5547 0.1833 0.5911

NASA/TM—2013-218094 J–38
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4417 520.4763 504.2848 0.0000 0.0600 0.0450 0.0243

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8702 6.6872 1.2055 550.7825 31.4191 256.4640 1.9881

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 196613.172 0.433 624.305 550849.875 0.230235E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.108 EfDer = 0.999 SH = 0.282032E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.189 3780.265 6.687 550.781 1.000 1.000 0.980

 W Kg/sec = 25.540 Wdry = 56.031 WH2O = 0.158 lbm/sec H2O = 1.344g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 127.279 3668.515 1.378 0.251 53.440 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 113602.445 44039.785 1.462 545.479 373.205 424.468 1.137

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 499.80 -0.17 499.80 0.45 0.74 642.50

 MEAN 17.74 0.00 -0.02 499.80 -0.17 499.80 0.45 0.69

 HUB 15.05 0.00 -0.02 499.80 -0.17 499.80 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.96 46.36 6.60 662.09 829.69 5.85 530.87 503.71 7.02

 MEAN 49.51 43.40 6.11 585.18 769.70 5.85 530.87 503.71 7.02

 HUB 44.82 38.84 5.98 496.48 704.61 5.85 530.87 503.71 7.02

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 580.38 299.49 497.14 1146.74 0.51 2.26 1.98 8.75

 MEAN 17.51 595.07 314.29 505.30 1142.97 0.52 2.34 2.07 6.78

 HUB 14.85 647.82 394.21 514.07 1139.46 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 653.51 610.32 354.03 0.53 5936.29 0.92 0.91

 MEAN 577.52 569.76 263.24 0.50 5505.11 0.92 0.91 0.91 1.46

 HUB 489.89 522.90 95.68 0.46 5856.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.04 1.20 6.77 582.00 1.06 555.15 515.93 3.95

 MEAN 7.94 1.19 6.62 579.73 1.05 551.50 515.41 4.32

 HUB 8.02 1.20 6.46 581.58 1.06 548.13 516.87 4.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.07 35.46 31.50 3.96 0.93 0.39 1.40

 MEAN 31.88 27.52 23.50 4.02 0.93 0.39 1.62

 HUB 37.48 10.54 6.50 4.04 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 660.3975 316.3479 579.6971 1137.5498 0.5805 -0.1723 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9858 6.3766 546.3566 517.0122 4.9572 28.6218 31.5000 2.8782

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 558.3961 121.8103 544.9481 1147.8076 0.4865 0.1270 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9656 6.7911 556.2557 515.3991 451.3937 0.0245 0.3090

 

NASA/TM—2013-218094 J–39
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 570.0964 0.0000 570.0964 1146.6692 0.4972 0.2180 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7273 555.1876 515.6920 0.0000 0.0600 0.0394 0.0810

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8788 7.9450 1.1881 581.0703 30.3237 243.8353 1.8902

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 190347.688 0.446 604.410 525270.375 0.317594E-02

 

Melt Ratio at Stator LE, Throat, TE

0.24884E+00 0.32075E+00 0.53289E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.603 EfDer = 1.000 SH = 0.352825E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.189 3780.265 7.945 581.059 1.000 1.000 0.980

 W Kg/sec = 25.540 Wdry = 55.991 WH2O = 0.198 lbm/sec H2O = 1.927g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.035 3571.626 1.377 0.251 53.463 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99080.922 44027.430 1.590 513.330 322.805 395.845 1.226

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 463.22 -0.16 463.22 0.40 0.68 600.28

 MEAN 16.97 0.00 -0.02 463.22 -0.16 463.22 0.40 0.63

 HUB 14.32 0.00 -0.02 463.22 -0.16 463.22 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.91 46.36 7.55 635.37 786.43 7.12 564.00 515.06 3.74

 MEAN 50.40 43.80 6.60 559.85 726.76 7.12 564.00 515.06 3.74

 HUB 45.57 37.84 7.73 472.40 661.73 7.12 564.00 515.06 3.74

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 548.18 292.77 463.45 1178.12 0.47 2.16 1.89 8.34

 MEAN 16.57 559.14 301.74 470.73 1174.36 0.48 2.24 1.97 6.35

 HUB 13.89 604.72 369.74 478.52 1170.82 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.83 568.97 330.06 0.48 5530.65 0.92 0.91

 MEAN 546.76 530.68 245.01 0.45 5003.79 0.92 0.91 0.91 1.49

 HUB 458.22 486.63 88.48 0.42 5137.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.35 1.18 8.08 610.06 1.05 586.16 525.43 2.34

 MEAN 9.21 1.16 7.91 607.29 1.05 582.43 524.69 2.53

 HUB 9.25 1.16 7.73 608.00 1.05 578.92 525.46 2.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.28 35.46 31.50 3.96 0.93 0.41 1.40

 MEAN 32.66 27.50 23.50 4.00 0.93 0.40 1.62

 HUB 37.69 10.48 6.50 3.98 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 603.5528 303.4418 521.7270 1171.3245 0.5153 -0.1180 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2573 7.7456 579.4935 525.6389 2.7311 30.1827 32.4000 2.2173

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 515.8373 115.6872 502.6973 1179.1746 0.4375 0.1566 2.2705

 

NASA/TM—2013-218094 J–40
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2421 8.1202 587.2985 524.7449 432.2457 0.0211 0.3336

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 511.5976 0.0000 511.5976 1179.4818 0.4337 0.2461 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1175 587.6520 525.0504 0.0000 0.0600 0.0383 0.1546

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8795 9.2187 1.1603 608.4409 27.3898 245.3415 1.9019

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 172341.219 0.444 547.235 518549.531 0.405421E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.983 EfDer = 1.000 SH = 0.522591E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.189 3780.265 9.219 608.439 1.000 1.000 0.980

 W Kg/sec = 25.540 Wdry = 55.895 WH2O = 0.294 lbm/sec H2O = 3.221g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.040 3490.368 1.374 0.253 53.518 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 87813.445 43997.691 1.788 509.668 284.979 384.739 1.350

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 413.46 -0.14 413.46 0.35 0.62 558.00

 MEAN 15.91 0.00 -0.02 413.46 -0.14 413.46 0.35 0.56

 HUB 13.07 0.00 -0.02 413.46 -0.14 413.46 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.63 47.36 8.27 604.36 732.38 8.49 594.92 525.71 2.79

 MEAN 51.78 44.80 6.98 524.95 668.34 8.49 594.92 525.71 2.79

 HUB 46.21 38.84 7.37 431.17 597.48 8.49 594.92 525.71 2.79

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 509.96 293.05 417.35 1206.64 0.42 2.05 1.78 7.43

 MEAN 15.50 513.87 289.60 424.50 1202.39 0.43 2.13 1.86 5.75

 HUB 12.59 547.18 335.81 432.02 1198.29 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 591.82 513.27 298.77 0.43 5259.94 0.92 0.91

 MEAN 511.25 478.88 221.65 0.40 4490.33 0.92 0.91 0.91 1.53

 HUB 415.33 439.28 79.53 0.37 4229.65 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.69 1.16 9.48 635.88 1.05 615.32 535.43 2.05

 MEAN 10.47 1.14 9.25 631.87 1.04 610.98 534.32 2.22

 HUB 10.39 1.13 9.03 630.51 1.04 606.83 534.31 2.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.08 35.60 31.50 4.10 0.93 0.44 1.40

 MEAN 34.30 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.86 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 571.3842 294.9077 489.3970 1198.2998 0.4768 -0.1960 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4930 9.0051 606.9794 535.3283 2.4330 31.0729 33.0000 1.9271

 

NASA/TM—2013-218094 J–41
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 494.1711 112.8444 481.1146 1204.6804 0.4102 0.0711 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4693 9.3435 613.4796 534.5333 410.5396 0.0387 0.3487

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 478.7984 0.0000 478.7984 1205.7914 0.3971 0.2727 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4108 614.6689 534.8580 0.0000 0.0600 0.0379 0.1243

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8801 10.4704 1.1358 632.7491 24.3109 251.2858 1.9480

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154011.172 0.440 489.031 526808.750 0.638238E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3240 Tt4 = 632.7491 T1 = 477.9146

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 971717.94 3085.4929 185.9135 2.4552 0.8600 4.7254 1.3240 37.3740

NASA/TM—2013-218094 J–42
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.075 EfDer = 0.997 SH = 0.748651E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.226 3748.905 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 25.103 Wdry = 55.184 WH2O = 0.041 lbm/sec H2O = 0.266g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 182.726 3905.573 1.381 0.249 53.373 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149637.422 43320.004 1.554 831.557 535.079 619.754 1.158

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 431.88 -0.15 431.88 0.41 0.76 703.10

 MEAN 17.06 0.00 -0.02 431.88 -0.15 431.88 0.41 0.67

 HUB 12.51 0.00 -0.02 431.88 -0.15 431.88 0.41 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.39 50.47 6.92 674.92 801.39 3.80 462.94 463.94 17.88

 MEAN 52.27 47.20 5.07 558.13 705.83 3.80 462.94 463.94 17.88

 HUB 43.47 38.62 4.85 409.27 595.10 3.80 462.94 463.94 17.88

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 669.50 371.21 557.17 1069.19 0.63 7.29 6.52 16.04

 MEAN 18.04 706.90 414.53 572.60 1063.54 0.66 7.43 6.80 12.53

 HUB 15.00 818.30 550.85 605.13 1052.88 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 674.92 634.57 303.71 0.59 7661.19 0.92 0.91

 MEAN 590.06 598.90 175.53 0.56 7478.96 0.92 0.91 0.91 1.31

 HUB 490.73 608.11 60.12 0.58 8264.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.58 1.31 4.30 518.16 1.08 482.17 488.38 11.71

 MEAN 5.54 1.30 4.14 517.20 1.08 477.08 488.87 14.01

 HUB 5.69 1.33 3.84 521.33 1.09 467.57 494.25 19.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.67 28.59 24.20 4.39 0.93 0.34 1.80

 MEAN 35.90 17.04 12.70 4.34 0.92 0.29 2.22

 HUB 42.31 -5.67 -9.30 3.63 0.92 0.14 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 750.5278 413.7220 626.1997 1059.7203 0.7082 -0.0796 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5895 4.0159 473.7108 491.0035 16.3314 33.4522 35.4000 1.9478

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 591.8445 144.7832 573.8621 1078.6395 0.5487 0.2998 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5611 4.5437 490.8013 487.6033 554.9116 0.0288 0.4136

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 587.9965 0.0000 587.9965 1078.9996 0.5449 0.3315 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5375 491.1744 488.2470 0.0000 0.0600 0.0437 0.2956

NASA/TM—2013-218094 J–43
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8700 5.5385 1.2987 518.8909 40.9785 222.5710 1.7254

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 255473.281 0.561 797.293 599925.500 0.128349E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 6.130 EfDer = 1.000 SH = 0.199406E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.226 3748.905 5.538 518.890 1.000 1.000 0.980

 W Kg/sec = 25.103 Wdry = 55.115 WH2O = 0.110 lbm/sec H2O = 0.822g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 146.605 3748.215 1.379 0.250 53.413 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 129105.852 43298.762 1.374 590.487 429.628 468.502 1.090

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 524.70 -0.18 524.70 0.48 0.79 672.16

 MEAN 18.08 0.00 -0.02 524.70 -0.18 524.70 0.48 0.73

 HUB 15.21 0.00 -0.02 524.70 -0.18 524.70 0.48 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.04 46.36 5.68 672.30 852.96 4.73 496.88 489.77 13.92

 MEAN 48.43 42.30 6.13 591.44 790.78 4.73 496.88 489.77 13.92

 HUB 43.49 37.84 5.65 497.60 723.26 4.73 496.88 489.77 13.92

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 598.50 300.38 517.66 1112.56 0.54 2.33 2.04 9.02

 MEAN 18.01 614.56 315.51 527.39 1108.37 0.55 2.40 2.13 7.35

 HUB 15.22 669.68 399.07 537.79 1104.51 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 668.05 634.94 367.66 0.57 6137.56 0.92 0.91

 MEAN 589.20 594.18 273.69 0.54 5685.60 0.92 0.91 0.91 1.44

 HUB 498.03 546.82 98.96 0.50 6077.72 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.77 1.22 5.57 550.99 1.06 522.36 503.79 6.83

 MEAN 6.67 1.20 5.43 548.63 1.06 518.44 503.24 7.64

 HUB 6.75 1.22 5.29 550.68 1.06 514.83 505.10 8.48

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.13 35.38 31.50 3.88 0.93 0.38 1.40

 MEAN 30.89 27.43 23.50 3.93 0.93 0.37 1.63

 HUB 36.58 10.43 6.50 3.93 0.93 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 687.1881 316.3961 610.0172 1101.8162 0.6237 -0.1862 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7173 5.1860 512.3722 505.4278 9.2560 27.4143 30.6000 3.1857

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 574.4280 121.7828 561.3702 1113.9706 0.5157 0.1308 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6955 5.5991 523.7400 503.2042 491.5697 0.0268 0.2898

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 601.5042 0.0000 601.5042 1111.2400 0.5413 0.1949 0.5911

NASA/TM—2013-218094 J–44
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4845 521.2030 504.0087 0.0000 0.0600 0.0420 0.0427

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8744 6.6757 1.2053 550.1008 31.2114 252.8166 1.9598

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195349.266 0.438 609.656 539051.500 0.236704E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.456 EfDer = 1.000 SH = 0.289898E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.226 3748.905 6.676 550.100 1.000 1.000 0.980

 W Kg/sec = 25.103 Wdry = 55.066 WH2O = 0.160 lbm/sec H2O = 1.386g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 125.235 3640.336 1.378 0.251 53.442 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 111279.727 43283.270 1.485 545.479 367.230 424.468 1.156

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 489.58 -0.17 489.58 0.44 0.73 637.56

 MEAN 17.74 0.00 -0.02 489.58 -0.17 489.58 0.44 0.68

 HUB 15.05 0.00 -0.02 489.58 -0.17 489.58 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.30 46.36 6.94 656.60 819.17 5.87 531.00 503.55 7.21

 MEAN 49.86 43.40 6.46 580.32 759.38 5.87 531.00 503.55 7.21

 HUB 45.17 38.84 6.33 492.37 694.46 5.87 531.00 503.55 7.21

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 572.97 301.15 487.45 1146.63 0.50 2.26 1.98 8.75

 MEAN 17.51 587.03 314.77 495.50 1142.83 0.51 2.34 2.07 6.78

 HUB 14.85 638.71 392.16 504.15 1139.28 0.56 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 648.09 598.31 346.94 0.52 5969.14 0.92 0.91

 MEAN 572.73 558.63 257.96 0.49 5513.55 0.92 0.91 0.91 1.47

 HUB 485.82 512.77 93.66 0.45 5826.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.03 1.20 6.78 581.22 1.06 555.06 515.79 4.07

 MEAN 7.92 1.19 6.63 578.85 1.05 551.38 515.22 4.46

 HUB 7.99 1.20 6.48 580.48 1.06 547.96 516.60 4.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.71 35.44 31.50 3.94 0.93 0.40 1.40

 MEAN 32.43 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.88 10.52 6.50 4.02 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 650.0748 316.8368 567.6370 1137.7070 0.5714 -0.1681 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9637 6.4026 546.5202 516.7716 5.0807 29.1689 31.5000 2.3311

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 546.8149 119.2840 533.6458 1147.8998 0.4764 0.1397 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9454 6.8176 556.3586 515.1611 451.3937 0.0236 0.3168

 

NASA/TM—2013-218094 J–45
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 558.0729 0.0000 558.0729 1146.8232 0.4866 0.2268 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7567 555.3503 515.4432 0.0000 0.0600 0.0385 0.0946

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8806 7.9253 1.1872 580.1469 30.0836 240.7164 1.8660

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188884.813 0.450 589.481 514751.438 0.325504E-02

 

Melt Ratio at Stator LE, Throat, TE

0.26131E+00 0.33591E+00 0.55464E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.911 EfDer = 1.000 SH = 0.360647E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.226 3748.905 7.925 580.135 1.000 1.000 0.980

 W Kg/sec = 25.103 Wdry = 55.026 WH2O = 0.199 lbm/sec H2O = 1.974g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 108.331 3544.815 1.376 0.251 53.465 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 97190.461 43271.133 1.615 513.330 317.822 395.845 1.245

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 454.38 -0.16 454.38 0.39 0.67 595.78

 MEAN 16.97 0.00 -0.02 454.38 -0.16 454.38 0.39 0.62

 HUB 14.32 0.00 -0.02 454.38 -0.16 454.38 0.39 0.56

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.21 46.36 7.85 630.10 776.97 7.14 563.72 514.85 3.86

 MEAN 50.71 43.80 6.91 555.20 717.56 7.14 563.72 514.85 3.86

 HUB 45.88 37.84 8.04 468.48 652.75 7.14 563.72 514.85 3.86

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 541.61 293.77 455.01 1177.60 0.46 2.16 1.89 8.34

 MEAN 16.57 551.98 301.80 462.17 1173.84 0.47 2.24 1.97 6.35

 HUB 13.89 596.57 367.65 469.82 1170.28 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 617.67 558.52 323.89 0.47 5549.45 0.92 0.91

 MEAN 542.22 520.96 240.42 0.44 5004.70 0.92 0.91 0.91 1.50

 HUB 454.42 477.76 86.77 0.41 5108.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.33 1.18 8.08 608.98 1.05 585.66 525.23 2.43

 MEAN 9.18 1.16 7.91 606.15 1.04 581.93 524.47 2.63

 HUB 9.21 1.16 7.73 606.69 1.05 578.40 525.17 2.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.85 35.44 31.50 3.94 0.93 0.41 1.40

 MEAN 33.15 27.48 23.50 3.98 0.93 0.40 1.62

 HUB 38.04 10.46 6.50 3.96 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 595.0948 303.5004 511.8841 1170.9485 0.5082 -0.1157 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2244 7.7547 579.1344 525.4022 2.8320 30.6641 32.4000 1.7359

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 506.0493 113.4921 493.1587 1178.7871 0.4293 0.1672 2.2705

 

NASA/TM—2013-218094 J–46
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2104 8.1307 586.9275 524.5016 432.2457 0.0205 0.3405

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 501.8990 0.0000 501.8990 1179.0801 0.4257 0.2538 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1277 587.2672 524.8156 0.0000 0.0600 0.0376 0.1649

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 9.1876 1.1593 607.2696 27.1402 242.5886 1.8805

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 170813.531 0.448 533.083 508799.000 0.415926E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.246 EfDer = 1.000 SH = 0.535603E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.226 3748.905 9.188 607.268 1.000 1.000 0.980

 W Kg/sec = 25.103 Wdry = 54.930 WH2O = 0.296 lbm/sec H2O = 3.302g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 95.606 3464.749 1.374 0.253 53.522 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 86266.695 43241.000 1.815 509.668 280.791 384.739 1.370

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 406.18 -0.14 406.18 0.34 0.61 553.90

 MEAN 15.91 0.00 -0.02 406.18 -0.14 406.18 0.34 0.56

 HUB 13.07 0.00 -0.02 406.18 -0.14 406.18 0.34 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.88 47.36 8.52 599.35 724.13 8.48 594.23 525.52 2.91

 MEAN 52.05 44.80 7.25 520.60 660.42 8.48 594.23 525.52 2.91

 HUB 46.48 38.84 7.64 427.59 589.86 8.48 594.23 525.52 2.91

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 504.38 293.27 410.35 1205.71 0.42 2.05 1.78 7.43

 MEAN 15.50 507.74 289.19 417.33 1201.48 0.42 2.13 1.86 5.75

 HUB 12.59 540.15 333.78 424.68 1197.40 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 586.91 504.60 293.65 0.42 5263.80 0.92 0.91

 MEAN 507.01 470.75 217.82 0.39 4484.04 0.92 0.91 0.91 1.54

 HUB 411.89 431.81 78.11 0.36 4204.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.65 1.16 9.46 634.49 1.04 614.38 535.22 2.14

 MEAN 10.42 1.13 9.24 630.46 1.04 610.08 534.09 2.32

 HUB 10.34 1.13 9.02 629.01 1.04 605.95 534.05 2.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 35.55 35.59 31.50 4.09 0.93 0.45 1.40

 MEAN 34.72 27.56 23.50 4.06 0.93 0.42 1.64

 HUB 38.17 10.42 6.50 3.92 0.93 0.41 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 563.8032 294.4969 480.7761 1197.5493 0.4708 -0.1933 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4465 8.9992 606.2385 535.0914 2.5369 31.4893 33.0000 1.5107

 

NASA/TM—2013-218094 J–47
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 485.3670 110.8340 472.5431 1203.9316 0.4032 0.0821 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4246 9.3393 612.7375 534.2847 410.5396 0.0377 0.3546

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 470.4000 0.0000 470.4000 1204.9918 0.3904 0.2792 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4033 613.8747 534.6203 0.0000 0.0600 0.0374 0.1339

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8807 10.4250 1.1347 631.3190 24.0521 248.9135 1.9296

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 152431.828 0.443 475.717 517516.594 0.653686E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.3210 Tt4 = 631.3190 T1 = 477.9145

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 962952.69 3005.2300 182.7255 2.4446 0.8631 5.0749 1.3210 37.3740

NASA/TM—2013-218094 J–48
10μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.856 EfDer = 0.984 SH = 0.116753E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.048 3888.739 4.265 457.735 1.000 1.000 0.980

 W Kg/sec = 28.658 Wdry = 63.041 WH2O = 0.007 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.152 4139.589 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 168033.281 49468.547 1.392 831.557 597.590 619.754 1.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 484.97 -0.17 484.97 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 484.97 -0.17 484.97 0.48 0.74

 HUB 12.51 0.00 -0.02 484.97 -0.17 484.97 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.30 50.47 4.83 700.09 851.80 3.66 438.82 448.93 8.78

 MEAN 50.06 47.20 2.86 578.95 755.36 3.66 438.82 448.93 8.78

 HUB 41.21 38.62 2.59 424.53 644.64 3.66 438.82 448.93 8.78

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 727.47 353.23 635.96 1038.69 0.70 7.29 6.52 16.04

 MEAN 18.04 772.56 411.47 653.87 1033.30 0.75 7.43 6.80 12.53

 HUB 15.00 913.32 579.93 705.58 1019.30 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.09 724.40 346.86 0.70 7290.67 0.92 0.90

 MEAN 612.06 683.95 200.59 0.66 7424.13 0.92 0.90 0.90 1.21

 HUB 509.03 709.13 70.90 0.70 8701.05 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 497.53 1.09 454.97 475.06 5.42

 MEAN 5.63 1.32 3.90 498.26 1.09 450.26 475.85 6.56

 HUB 5.89 1.38 3.52 505.23 1.10 438.14 481.56 10.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.05 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.18 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.42 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 835.5209 410.6706 727.6296 1026.3264 0.8141 -0.1080 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6906 3.6978 444.1965 477.7482 8.6993 29.4402 35.4000 5.9598

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 680.6235 166.5013 659.9437 1047.9094 0.6495 0.2278 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6296 4.2537 463.0866 476.1745 554.9116 0.0423 0.3585

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 682.8517 0.0000 682.8517 1047.6053 0.6518 0.2525 1.3089

NASA/TM—2013-218094 J–49
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.2010 462.8475 476.1836 0.0000 0.0600 0.0737 0.1998

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8221 5.5704 1.3062 500.3397 42.6070 238.0831 1.8456

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 264915.938 0.541 943.873 726828.875 0.171088E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.469 EfDer = 0.989 SH = 0.245431E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.048 3888.739 5.570 500.339 1.000 1.000 0.980

 W Kg/sec = 28.658 Wdry = 63.033 WH2O = 0.015 lbm/sec H2O = 0.101g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.409 3959.446 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 146996.813 49466.051 1.234 590.487 478.373 468.502 0.979

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 597.45 -0.21 597.45 0.56 0.87 710.04

 MEAN 18.08 0.00 -0.02 597.45 -0.21 597.45 0.56 0.81

 HUB 15.21 0.00 -0.02 597.45 -0.21 597.45 0.56 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.42 46.36 3.06 697.38 918.46 4.50 471.65 476.23 4.68

 MEAN 45.77 42.30 3.47 613.50 856.49 4.50 471.65 476.23 4.68

 HUB 40.84 37.84 3.00 516.16 789.68 4.50 471.65 476.23 4.68

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 647.63 274.73 586.47 1085.82 0.60 2.33 2.04 9.02

 MEAN 18.01 667.42 300.21 596.09 1082.31 0.62 2.40 2.13 7.35

 HUB 15.22 728.65 403.49 606.73 1079.18 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 692.97 720.33 418.24 0.66 5614.17 0.92 0.90

 MEAN 611.18 672.32 310.96 0.62 5410.57 0.92 0.90 0.90 1.37

 HUB 516.60 617.18 113.11 0.57 6145.45 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.77 1.22 5.34 530.97 1.06 497.25 491.55 2.02

 MEAN 6.73 1.21 5.22 529.86 1.06 494.05 491.13 2.24

 HUB 6.90 1.24 5.10 533.86 1.07 491.19 493.27 2.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.10 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.73 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.62 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 765.7443 301.0570 704.0802 1071.7021 0.7145 -0.2376 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7819 4.8444 484.4391 492.5258 3.1291 23.1510 30.6000 7.4490

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 661.9744 140.3433 646.9265 1084.8011 0.6102 0.0199 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7313 5.2506 496.3435 491.7730 491.5697 0.0421 0.2201

 

NASA/TM—2013-218094 J–50
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 705.1792 0.0000 705.1792 1079.5847 0.6532 0.0965 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0315 491.6000 491.9714 0.0000 0.0600 0.0752 -0.1189

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8229 6.6790 1.1990 531.5606 31.2231 280.9856 2.1782

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 194285.203 0.405 692.222 657878.813 0.284968E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.845 EfDer = 0.992 SH = 0.349951E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.048 3888.739 6.679 531.560 1.000 1.000 0.980

 W Kg/sec = 28.658 Wdry = 63.026 WH2O = 0.022 lbm/sec H2O = 0.168g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.474 3841.408 1.381 0.249 53.360 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126536.156 49464.020 1.326 545.479 411.275 424.468 1.032

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 556.73 -0.19 556.73 0.51 0.80 672.78

 MEAN 17.74 0.00 -0.02 556.73 -0.19 556.73 0.51 0.75

 HUB 15.05 0.00 -0.02 556.73 -0.19 556.73 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.74 46.36 4.38 681.09 879.82 5.61 506.66 491.56 1.99

 MEAN 47.24 43.40 3.84 601.97 820.09 5.61 506.66 491.56 1.99

 HUB 42.54 38.84 3.70 510.73 755.64 5.61 506.66 491.56 1.99

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 618.03 277.83 552.06 1121.88 0.55 2.26 1.98 8.75

 MEAN 17.51 635.92 301.05 560.14 1118.62 0.57 2.34 2.07 6.78

 HUB 14.85 693.85 396.94 569.09 1115.67 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.27 678.49 394.44 0.60 5507.63 0.92 0.91

 MEAN 594.10 632.17 293.04 0.57 5273.83 0.92 0.91 0.91 1.40

 HUB 503.94 579.06 107.00 0.52 5897.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.01 1.20 6.53 561.59 1.06 530.90 504.65 1.05

 MEAN 7.95 1.19 6.40 560.31 1.05 527.83 504.20 1.14

 HUB 8.11 1.21 6.27 563.71 1.06 525.04 505.79 1.23

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.71 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.26 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.90 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 717.5737 303.0303 650.4495 1110.8074 0.6460 -0.2056 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0032 6.0655 520.5186 505.1755 1.4293 24.9798 31.5000 6.5202

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 627.4549 136.8750 612.3438 1121.1547 0.5597 0.0344 2.3726

 

NASA/TM—2013-218094 J–51
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9624 6.4540 530.2521 504.7160 451.3937 0.0352 0.2534

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 644.7041 0.0000 644.7041 1119.2692 0.5760 0.1436 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3437 528.4936 504.7712 0.0000 0.0600 0.0604 -0.0335

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8446 7.9214 1.1860 561.8704 30.3115 266.4225 2.0653

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188739.234 0.418 672.462 621682.938 0.421862E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.434 EfDer = 0.995 SH = 0.535832E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.048 3888.739 7.921 561.870 1.000 1.000 0.980

 W Kg/sec = 28.658 Wdry = 63.015 WH2O = 0.034 lbm/sec H2O = 0.296g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.772 3736.361 1.380 0.249 53.366 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110039.742 49460.410 1.440 513.330 356.576 395.845 1.110

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 514.47 -0.18 514.47 0.45 0.73 627.97

 MEAN 16.97 0.00 -0.02 514.47 -0.18 514.47 0.45 0.68

 HUB 14.32 0.00 -0.02 514.47 -0.18 514.47 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.80 46.36 5.44 653.60 831.93 6.89 540.63 504.65 1.14

 MEAN 48.23 43.80 4.43 575.91 772.37 6.89 540.63 504.65 1.14

 HUB 43.38 37.84 5.54 485.96 707.82 6.89 540.63 504.65 1.14

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 581.79 274.15 513.15 1155.09 0.50 2.16 1.89 8.34

 MEAN 16.57 596.20 290.41 520.69 1151.66 0.52 2.24 1.97 6.35

 HUB 13.89 647.00 372.69 528.88 1148.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.70 630.62 366.56 0.55 5179.36 0.92 0.91

 MEAN 562.45 587.47 272.04 0.51 4816.22 0.92 0.91 0.91 1.42

 HUB 471.37 538.01 98.68 0.47 5179.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.32 1.18 7.85 590.08 1.05 562.92 515.71 0.70

 MEAN 9.21 1.16 7.69 588.10 1.05 559.58 515.03 0.75

 HUB 9.32 1.18 7.53 590.08 1.05 556.48 515.92 0.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.11 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.15 27.58 23.50 4.08 0.92 0.35 1.62

 HUB 35.17 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 649.8551 292.0426 580.5366 1147.4423 0.5664 -0.1370 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2654 7.4739 555.5383 515.6780 0.8399 26.7050 32.4000 5.6950

 

NASA/TM—2013-218094 J–52
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 575.5536 129.0798 560.8925 1154.9623 0.4983 0.0755 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2355 7.8113 562.8420 515.3838 432.2457 0.0288 0.2834

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 570.9680 0.0000 570.9680 1155.3676 0.4942 0.1862 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.8075 563.2630 515.3502 0.0000 0.0600 0.0475 0.0731

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8620 9.2058 1.1621 589.4143 27.5516 266.6895 2.0674

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171726.563 0.418 611.847 608769.000 0.615786E-03

 

Melt Ratio at Stator LE, Throat, TE

0.67497E-01 0.86653E-01 0.14104E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.039 EfDer = 0.997 SH = 0.710325E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.048 3888.739 9.206 589.412 1.000 1.000 0.980

 W Kg/sec = 28.658 Wdry = 63.004 WH2O = 0.045 lbm/sec H2O = 0.446g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.320 3648.014 1.380 0.249 53.371 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96805.516 49457.023 1.622 509.668 314.314 384.739 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 455.85 -0.16 455.85 0.39 0.66 583.20

 MEAN 15.91 0.00 -0.02 455.85 -0.16 455.85 0.39 0.61

 HUB 13.07 0.00 -0.02 455.85 -0.16 455.85 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.76 47.36 6.40 621.70 771.04 8.30 572.75 515.25 0.68

 MEAN 49.84 44.80 5.04 540.02 706.81 8.30 572.75 515.25 0.68

 HUB 44.23 38.84 5.39 443.54 636.13 8.30 572.75 515.25 0.68

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 537.07 279.65 458.52 1186.01 0.45 2.05 1.78 7.43

 MEAN 15.50 544.81 281.59 466.40 1181.78 0.46 2.13 1.86 5.75

 HUB 12.59 583.50 339.27 474.72 1177.76 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.81 564.43 329.15 0.48 5019.88 0.92 0.91

 MEAN 525.92 526.52 244.33 0.45 4366.50 0.92 0.91 0.91 1.47

 HUB 427.25 482.81 87.98 0.41 4273.49 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.70 1.16 9.31 616.72 1.05 593.60 525.12 0.45

 MEAN 10.50 1.14 9.09 613.17 1.04 589.37 523.92 0.49

 HUB 10.47 1.14 8.87 612.66 1.04 585.36 523.85 0.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.38 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.12 27.65 23.50 4.15 0.92 0.38 1.64

 HUB 35.55 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 612.1856 286.7558 540.8718 1176.4740 0.5204 -0.2175 2.0437

 

NASA/TM—2013-218094 J–53
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5250 8.7722 584.1436 524.3993 0.5508 27.9313 33.0000 5.0687

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 548.2115 125.1846 533.7272 1182.4520 0.4636 -0.0198 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4803 9.0622 590.0903 524.1418 410.5396 0.0505 0.3042

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 529.7126 0.0000 529.7126 1184.0188 0.4474 0.2205 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1587 591.6819 524.1426 0.0000 0.0600 0.0453 0.0461

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8699 10.4880 1.1393 614.1690 24.7730 270.6994 2.0984

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154559.906 0.417 550.684 612962.938 0.770957E-03

 

Melt Ratio at Stator LE, Throat, TE

0.34604E+00 0.37703E+00 0.46726E+00

 trTOT = 1.3418 Tt4 = 614.1690 T1 = 457.7348

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 974226.88 3471.0891 204.1520 2.4592 0.8238 2.8561 1.3418 37.3740

NASA/TM—2013-218094 J–54
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.097 EfDer = 0.993 SH = 0.125272E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.884 3728.968 4.265 457.734 1.000 1.000 0.980

 W Kg/sec = 26.766 Wdry = 58.877 WH2O = 0.007 lbm/sec H2O = 0.046g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 190.669 3969.513 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154163.641 46201.258 1.490 831.557 558.127 619.754 1.110

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 444.94 -0.15 444.94 0.43 0.79 714.61

 MEAN 17.06 0.00 -0.02 444.94 -0.15 444.94 0.43 0.70

 HUB 12.51 0.00 -0.02 444.94 -0.15 444.94 0.43 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.47 50.47 6.00 671.33 805.52 3.75 441.81 448.88 8.27

 MEAN 51.30 47.20 4.10 555.16 711.58 3.75 441.81 448.88 8.27

 HUB 42.47 38.62 3.85 407.09 603.18 3.75 441.81 448.88 8.27

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 679.04 356.11 578.16 1043.41 0.65 7.29 6.52 16.04

 MEAN 18.04 718.72 404.78 593.90 1038.05 0.69 7.43 6.80 12.53

 HUB 15.00 837.65 550.96 630.96 1026.75 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 671.33 658.51 315.21 0.63 7349.80 0.92 0.91

 MEAN 586.92 621.20 182.14 0.60 7303.21 0.92 0.91 0.91 1.26

 HUB 488.12 634.08 62.84 0.62 8266.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.57 1.31 4.20 496.20 1.08 459.12 474.18 5.06

 MEAN 5.56 1.30 4.05 495.96 1.08 454.42 474.33 6.09

 HUB 5.75 1.35 3.73 501.00 1.09 444.57 478.35 9.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.63 28.60 24.20 4.40 0.93 0.31 1.80

 MEAN 34.28 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.13 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 767.6245 403.9923 652.7156 1033.3807 0.7428 -0.0892 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6079 3.9032 450.3361 475.7688 7.4177 31.7551 35.4000 3.6450

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 615.7371 150.6281 597.0288 1052.5787 0.5850 0.2684 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5708 4.4308 467.2348 474.6467 554.9116 0.0327 0.3895

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 613.0662 0.0000 613.0662 1052.8492 0.5823 0.2997 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4141 467.5022 474.6940 0.0000 0.0600 0.0525 0.2582

NASA/TM—2013-218094 J–55
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8563 5.5385 1.2987 497.7202 39.9882 229.3139 1.7776

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 248658.547 0.552 827.437 666835.688 0.190909E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.969 EfDer = 0.997 SH = 0.281400E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.884 3728.968 5.539 497.720 1.000 1.000 0.980

 W Kg/sec = 26.766 Wdry = 58.868 WH2O = 0.017 lbm/sec H2O = 0.119g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 153.094 3806.749 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 133750.016 46198.426 1.317 590.487 448.189 468.502 1.045

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 543.61 -0.19 543.61 0.51 0.81 682.65

 MEAN 18.08 0.00 -0.02 543.61 -0.19 543.61 0.51 0.76

 HUB 15.21 0.00 -0.02 543.61 -0.19 543.61 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.90 46.36 4.54 668.73 861.95 4.64 473.97 474.91 4.99

 MEAN 47.27 42.30 4.97 588.29 801.14 4.64 473.97 474.91 4.99

 HUB 42.33 37.84 4.49 494.95 735.31 4.64 473.97 474.91 4.99

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 606.46 283.01 536.38 1087.07 0.56 2.33 2.04 9.02

 MEAN 18.01 623.91 302.32 545.77 1083.27 0.58 2.40 2.13 7.35

 HUB 15.22 680.55 392.59 555.91 1079.80 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 664.50 658.20 381.49 0.61 5782.85 0.92 0.91

 MEAN 586.07 615.12 283.74 0.57 5448.23 0.92 0.91 0.91 1.41

 HUB 495.38 565.33 102.79 0.52 5979.18 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.47 527.97 1.06 498.41 490.39 2.27

 MEAN 6.66 1.20 5.33 526.22 1.06 494.93 489.66 2.54

 HUB 6.78 1.22 5.20 528.99 1.06 491.77 491.24 2.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.82 35.42 31.50 3.92 0.93 0.35 1.40

 MEAN 28.98 27.47 23.50 3.97 0.92 0.35 1.63

 HUB 35.23 10.48 6.50 3.98 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 704.0506 303.1729 635.4317 1075.5083 0.6546 -0.2048 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7105 5.0492 487.8953 490.8168 3.2488 25.5064 30.6000 5.0936

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 598.6795 126.9243 585.0704 1087.6028 0.5505 0.0837 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6801 5.4506 498.9244 490.1898 491.5697 0.0318 0.2598

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 629.8730 0.0000 629.8730 1084.2239 0.5809 0.1550 0.5911

NASA/TM—2013-218094 J–56
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3066 495.8476 490.3481 0.0000 0.0600 0.0526 -0.0198

 

 STAGE EXIT CONDITIONS, STAGE 2 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8593 6.6512 1.2009 527.7241 30.0061 264.7663 2.0525

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186737.656 0.423 621.389 600651.563 0.327003E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.277 EfDer = 0.998 SH = 0.400614E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.884 3728.968 6.651 527.724 1.000 1.000 0.980

 W Kg/sec = 26.766 Wdry = 58.861 WH2O = 0.024 lbm/sec H2O = 0.197g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 131.268 3696.948 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115386.438 46196.270 1.419 545.479 384.335 424.468 1.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 507.67 -0.17 507.67 0.46 0.75 647.48

 MEAN 17.74 0.00 -0.02 507.67 -0.17 507.67 0.46 0.70

 HUB 15.05 0.00 -0.02 507.67 -0.17 507.67 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.15 46.36 5.79 653.11 827.35 5.75 507.02 490.13 2.30

 MEAN 48.68 43.40 5.28 577.23 768.85 5.75 507.02 490.13 2.30

 HUB 43.98 38.84 5.14 489.75 705.52 5.75 507.02 490.13 2.30

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 580.01 284.34 505.53 1121.08 0.52 2.26 1.98 8.75

 MEAN 17.51 595.57 301.96 513.34 1117.61 0.53 2.34 2.07 6.78

 HUB 14.85 648.96 385.82 521.81 1114.40 0.58 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 644.64 620.79 360.31 0.55 5636.28 0.92 0.91

 MEAN 569.69 578.97 267.73 0.52 5289.30 0.92 0.91 0.91 1.43

 HUB 483.24 530.82 97.41 0.48 5732.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.97 1.20 6.65 557.19 1.06 530.17 503.30 1.25

 MEAN 7.88 1.18 6.51 555.37 1.05 526.88 502.61 1.37

 HUB 7.99 1.20 6.37 557.69 1.06 523.86 503.77 1.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.36 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.46 27.54 23.50 4.04 0.92 0.37 1.62

 HUB 36.48 10.57 6.50 4.07 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 664.3437 303.9366 590.7411 1111.6394 0.5976 -0.1829 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9301 6.2472 521.3084 503.4676 1.6342 27.2258 31.5000 4.2742

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 569.8171 124.3017 556.0941 1121.5869 0.5080 0.0930 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9051 6.6430 530.6754 503.0493 451.3937 0.0274 0.2877

 

NASA/TM—2013-218094 J–57
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 582.5035 0.0000 582.5035 1120.3245 0.5199 0.1920 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5702 529.5046 503.1224 0.0000 0.0600 0.0439 0.0423

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8709 7.8815 1.1850 556.7465 29.0242 252.0007 1.9535

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180753.953 0.435 601.478 571718.938 0.478954E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.748 EfDer = 0.999 SH = 0.600492E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.884 3728.968 7.882 556.746 1.000 1.000 0.980

 W Kg/sec = 26.766 Wdry = 58.849 WH2O = 0.035 lbm/sec H2O = 0.338g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 113.783 3599.300 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 100743.789 46192.645 1.541 513.330 333.197 395.845 1.188

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 471.01 -0.16 471.01 0.42 0.69 604.94

 MEAN 16.97 0.00 -0.02 471.01 -0.16 471.01 0.42 0.64

 HUB 14.32 0.00 -0.02 471.01 -0.16 471.01 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.08 46.36 6.72 626.75 784.13 7.00 538.94 503.09 1.37

 MEAN 49.55 43.80 5.75 552.25 725.95 7.00 538.94 503.09 1.37

 HUB 44.70 37.84 6.86 465.99 662.68 7.00 538.94 503.09 1.37

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 547.57 278.22 471.62 1152.22 0.48 2.16 1.89 8.34

 MEAN 16.57 559.63 289.92 478.68 1148.71 0.49 2.24 1.97 6.35

 HUB 13.89 606.12 361.83 486.27 1145.40 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 614.38 579.16 336.16 0.50 5255.90 0.92 0.91 

 MEAN 539.34 539.76 249.42 0.47 4807.86 0.92 0.91 0.91 1.46

 HUB 452.00 494.56 90.17 0.43 5028.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.25 1.17 7.94 584.19 1.05 560.13 514.13 0.85

 MEAN 9.13 1.16 7.77 581.85 1.05 556.72 513.29 0.93

 HUB 9.19 1.17 7.61 583.00 1.05 553.52 513.88 1.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.54 35.48 31.50 3.98 0.93 0.39 1.40

 MEAN 31.20 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 36.65 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 606.1483 291.5507 531.4263 1145.3728 0.5292 -0.1250 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1726 7.5982 553.5427 513.8777 1.0121 28.7500 32.4000 3.6500

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 526.3022 118.0342 512.8956 1152.8500 0.4565 0.1239 2.2705

 

NASA/TM—2013-218094 J–58
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1538 7.9494 560.7949 513.5922 432.2457 0.0233 0.3122

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 522.0076 0.0000 522.0076 1153.1934 0.4527 0.2211 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9463 561.1544 513.5707 0.0000 0.0600 0.0412 0.1216

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8753 9.1286 1.1582 583.0089 26.2703 253.5561 1.9656

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 163769.172 0.434 544.959 563442.625 0.684354E-03

 

Melt Ratio at Stator LE, Throat, TE

0.70622E-01 0.90963E-01 0.14848E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.154 EfDer = 1.000 SH = 0.782482E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.884 3728.968 9.129 583.006 1.000 1.000 0.980

 W Kg/sec = 26.766 Wdry = 58.838 WH2O = 0.046 lbm/sec H2O = 0.497g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 100.529 3517.299 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89221.414 46189.336 1.731 509.668 294.434 384.739 1.307

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 420.13 -0.14 420.13 0.36 0.63 562.30

 MEAN 15.91 0.00 -0.02 420.13 -0.14 420.13 0.36 0.57

 HUB 13.07 0.00 -0.02 420.13 -0.14 420.13 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.83 47.36 7.47 596.16 729.45 8.35 568.86 513.51 0.84

 MEAN 50.95 44.80 6.15 517.83 666.94 8.35 568.86 513.51 0.84

 HUB 45.36 38.84 6.52 425.32 597.94 8.35 568.86 513.51 0.84

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 508.23 279.80 424.28 1180.90 0.43 2.05 1.78 7.43

 MEAN 15.50 513.64 278.83 431.36 1176.79 0.44 2.13 1.86 5.75

 HUB 12.59 548.31 328.73 438.84 1172.86 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 583.79 521.95 304.00 0.44 5022.19 0.92 0.91

 MEAN 504.31 486.74 225.48 0.41 4323.49 0.92 0.91 0.91 1.50

 HUB 409.70 446.24 80.96 0.38 4140.63 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.57 1.16 9.32 609.20 1.04 588.50 523.23 0.57

 MEAN 10.36 1.13 9.10 605.56 1.04 584.41 521.97 0.62

 HUB 10.30 1.13 8.89 604.60 1.04 580.50 521.73 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.40 35.62 31.50 4.12 0.93 0.42 1.40

 MEAN 32.88 27.60 23.50 4.10 0.93 0.40 1.64

 HUB 36.84 10.45 6.50 3.95 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 573.3199 283.9420 498.0689 1172.4082 0.4890 -0.2044 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3829 8.8359 580.1112 522.4056 0.6814 29.6868 33.0000 3.3132

 

NASA/TM—2013-218094 J–59
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 503.9109 115.0685 490.5970 1178.4454 0.4276 0.0326 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3538 9.1460 586.1000 522.1639 410.5396 0.0423 0.3283

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 487.8139 0.0000 487.8139 1179.6971 0.4135 0.2491 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2213 587.3719 522.1595 0.0000 0.0600 0.0404 0.0903

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 10.3563 1.1345 606.4391 23.4490 259.6520 2.0128

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 146322.188 0.429 486.902 570958.000 0.846233E-03

 

Melt Ratio at Stator LE, Throat, TE

 0.35378E+00 0.38575E+00 0.47759E+00

 trTOT = 1.3249 Tt4 = 606.4391 T1 = 457.7343

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 926241.50 3082.1660 190.6689 2.4284 0.8528 4.0969 1.3249 37.3740

NASA/TM—2013-218094 J–60
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.536 EfDer = 0.995 SH = 0.128085E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.558 3683.918 4.265 457.734 1.000 1.000 0.980

 W Kg/sec = 26.163 Wdry = 57.551 WH2O = 0.007 lbm/sec H2O = 0.047g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 186.375 3921.556 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149922.141 45160.738 1.524 831.557 545.559 619.754 1.136

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 432.70 -0.15 432.70 0.42 0.77 705.98

 MEAN 17.06 0.00 -0.02 432.70 -0.15 432.70 0.42 0.68

 HUB 12.51 0.00 -0.02 432.70 -0.15 432.70 0.42 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.88 50.47 6.41 663.22 792.01 3.78 442.68 448.87 8.14

 MEAN 51.74 47.20 4.54 548.45 698.71 3.78 442.68 448.87 8.14

 HUB 42.92 38.62 4.30 402.17 590.84 3.78 442.68 448.87 8.14

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 665.15 357.48 560.92 1044.75 0.64 7.29 6.52 16.04

 MEAN 18.04 703.18 403.22 576.09 1039.39 0.68 7.43 6.80 12.53

 HUB 15.00 816.57 542.89 609.96 1028.66 0.79 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 663.22 638.83 305.74 0.61 7377.95 0.92 0.91 

 MEAN 579.83 602.56 176.61 0.58 7274.95 0.92 0.91 0.91 1.28

 HUB 482.22 612.97 60.67 0.60 8145.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.24 495.88 1.08 460.30 473.97 4.97

 MEAN 5.54 1.30 4.09 495.35 1.08 455.59 473.93 5.99

 HUB 5.71 1.34 3.78 499.85 1.09 446.23 477.53 8.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.51 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 34.99 17.04 12.70 4.34 0.92 0.27 2.22

 HUB 41.67 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 748.7233 402.4327 631.3750 1035.2263 0.7232 -0.0845 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5858 3.9584 451.9495 475.2713 7.1542 32.5131 35.4000 2.8869

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 596.8275 146.0022 578.6937 1053.8716 0.5663 0.2815 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5537 4.4792 468.3866 474.2408 554.9116 0.0306 0.3995

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 593.4939 0.0000 593.4939 1054.2040 0.5630 0.3135 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4685 468.7087 474.2998 0.0000 0.0600 0.0478 0.2746

NASA/TM—2013-218094 J–61
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8640 5.5267 1.2959 497.0273 39.2956 226.3473 1.7546

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244358.516 0.556 794.817 648488.938 0.197566E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.460 EfDer = 0.998 SH = 0.293299E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.558 3683.918 5.527 497.027 1.000 1.000 0.980

 W Kg/sec = 26.163 Wdry = 57.541 WH2O = 0.017 lbm/sec H2O = 0.125g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 149.861 3763.379 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 129882.336 45157.813 1.346 590.487 438.728 468.502 1.068

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 527.89 -0.18 527.89 0.50 0.80 674.88

 MEAN 18.08 0.00 -0.02 527.89 -0.18 527.89 0.50 0.74

 HUB 15.21 0.00 -0.02 527.89 -0.18 527.89 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.38 46.36 5.02 660.65 845.79 4.68 474.63 474.55 5.10

 MEAN 47.76 42.30 5.46 581.18 785.28 4.68 474.63 474.55 5.10

 HUB 42.82 37.84 4.98 488.97 719.68 4.68 474.63 474.55 5.10

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 594.78 285.78 521.63 1087.46 0.55 2.33 2.04 9.02

 MEAN 18.01 611.40 303.23 530.91 1083.58 0.56 2.40 2.13 7.35

 HUB 15.22 666.60 389.61 540.88 1080.03 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.47 639.93 370.69 0.59 5839.27 0.92 0.91

 MEAN 578.99 598.25 275.75 0.55 5464.52 0.92 0.91 0.91 1.42

 HUB 489.39 550.01 99.79 0.51 5933.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.22 5.50 527.20 1.06 498.77 490.09 2.35

 MEAN 6.64 1.20 5.36 525.26 1.06 495.22 489.26 2.63

 HUB 6.74 1.22 5.23 527.69 1.06 491.98 490.67 2.92

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.72 35.40 31.50 3.90 0.93 0.36 1.40

 MEAN 29.73 27.45 23.50 3.95 0.92 0.36 1.63

 HUB 35.77 10.45 6.50 3.95 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 686.9897 304.0855 616.0250 1076.4956 0.6382 -0.1963 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6869 5.1004 488.7943 490.3606 3.2986 26.2721 30.6000 4.3279

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 580.6994 123.1124 567.4990 1088.3564 0.5336 0.1026 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6610 5.5005 499.6201 489.7592 491.5697 0.0294 0.2716

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 609.4518 0.0000 609.4518 1085.3401 0.5615 0.1712 0.5911

NASA/TM—2013-218094 J–62
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3720 496.8730 489.9113 0.0000 0.0600 0.0474 0.0066

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8671 6.6368 1.2009 526.7145 29.6894 259.8093 2.0140

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184774.281 0.429 601.009 583461.625 0.340905E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.732 EfDer = 0.999 SH = 0.417335E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.558 3683.918 6.637 526.714 1.000 1.000 0.980

 W Kg/sec = 26.163 Wdry = 57.534 WH2O = 0.024 lbm/sec H2O = 0.206g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 128.467 3655.783 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 112178.781 45155.613 1.450 545.479 376.139 424.468 1.128

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 493.56 -0.17 493.56 0.45 0.74 640.27

 MEAN 17.74 0.00 -0.02 493.56 -0.17 493.56 0.45 0.69

 HUB 15.05 0.00 -0.02 493.56 -0.17 493.56 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.59 46.36 6.23 645.22 812.48 5.79 507.15 489.73 2.40

 MEAN 49.13 43.40 5.73 570.26 754.32 5.79 507.15 489.73 2.40

 HUB 44.44 38.84 5.60 483.83 691.27 5.79 507.15 489.73 2.40

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 569.37 286.38 492.11 1120.89 0.51 2.26 1.98 8.75

 MEAN 17.51 584.15 302.37 499.80 1117.37 0.52 2.34 2.07 6.78

 HUB 14.85 636.15 382.76 508.11 1114.09 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 636.86 604.16 350.48 0.54 5676.54 0.92 0.91

 MEAN 562.80 563.58 260.43 0.50 5296.56 0.92 0.91 0.91 1.45

 HUB 477.40 516.85 94.64 0.46 5686.56 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.95 1.20 6.68 556.03 1.06 529.99 502.92 1.32

 MEAN 7.85 1.18 6.53 554.06 1.05 526.66 502.16 1.45

 HUB 7.95 1.20 6.39 556.08 1.06 523.58 503.21 1.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.20 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 31.17 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 36.99 10.55 6.50 4.05 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 649.5989 304.3589 573.8854 1111.8485 0.5843 -0.1769 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9010 6.2883 521.5074 502.9914 1.7003 27.9392 31.5000 3.5608

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 553.5869 120.7612 540.2547 1121.6958 0.4935 0.1104 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8794 6.6852 530.7825 502.5801 451.3937 0.0256 0.2981

 

NASA/TM—2013-218094 J–63
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 565.4351 0.0000 565.4351 1120.5487 0.5046 0.2050 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6189 529.7208 502.6551 0.0000 0.0600 0.0409 0.0624

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8756 7.8583 1.1840 555.3881 28.6753 247.6976 1.9201

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 178591.047 0.440 580.897 556477.500 0.497911E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.154 EfDer = 1.000 SH = 0.622149E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.558 3683.918 7.858 555.388 1.000 1.000 0.980

 W Kg/sec = 26.163 Wdry = 57.522 WH2O = 0.036 lbm/sec H2O = 0.352g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 111.413 3560.163 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98105.328 45151.980 1.573 513.330 326.262 395.845 1.213 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 458.67 -0.16 458.67 0.41 0.68 598.36

 MEAN 16.97 0.00 -0.02 458.67 -0.16 458.67 0.41 0.63

 HUB 14.32 0.00 -0.02 458.67 -0.16 458.67 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.48 46.36 7.12 619.18 770.68 7.03 538.51 502.64 1.44

 MEAN 49.95 43.80 6.15 545.58 712.89 7.03 538.51 502.64 1.44

 HUB 45.12 37.84 7.28 460.36 649.97 7.03 538.51 502.64 1.44

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 538.05 279.41 459.82 1151.45 0.47 2.16 1.89 8.34

 MEAN 16.57 549.38 289.81 466.72 1147.92 0.48 2.24 1.97 6.35

 HUB 13.89 594.58 358.78 474.13 1144.59 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 606.96 564.55 327.54 0.49 5278.38 0.92 0.91

 MEAN 532.82 526.20 243.01 0.46 4805.91 0.92 0.91 0.91 1.47

 HUB 446.54 482.18 87.76 0.42 4985.71 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.21 1.17 7.95 582.62 1.05 559.39 513.67 0.90

 MEAN 9.09 1.16 7.78 580.18 1.04 555.96 512.79 0.98

 HUB 9.13 1.16 7.62 581.11 1.05 552.74 513.30 1.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.29 35.46 31.50 3.96 0.93 0.40 1.40

 MEAN 31.84 27.51 23.50 4.01 0.93 0.39 1.62

 HUB 37.12 10.49 6.50 3.99 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 593.9987 291.4373 517.5894 1144.8077 0.5189 -0.1216 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1316 7.6183 552.9990 513.3571 1.0677 29.3824 32.4000 3.0176

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 512.4995 114.9386 499.4445 1152.2672 0.4448 0.1381 2.2705

 

NASA/TM—2013-218094 J–64
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1152 7.9718 560.2313 513.0713 432.2457 0.0221 0.3212

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 508.2992 0.0000 508.2992 1152.5929 0.4410 0.2315 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9687 560.5732 513.0530 0.0000 0.0600 0.0397 0.1359

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8780 9.0911 1.1569 581.2936 25.9136 249.7271 1.9359

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161555.406 0.439 525.486 549399.750 0.707524E-03

 

Melt Ratio at Stator LE, Throat, TE

0.71418E-01 0.92098E-01 0.15053E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.501 EfDer = 1.000 SH = 0.807158E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.558 3683.918 9.091 581.291 1.000 1.000 0.980

 W Kg/sec = 26.163 Wdry = 57.512 WH2O = 0.046 lbm/sec H2O = 0.514g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 98.525 3479.928 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 87058.313 45148.699 1.766 509.668 288.569 384.739 1.333

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 409.95 -0.14 409.95 0.35 0.62 556.33

 MEAN 15.91 0.00 -0.02 409.95 -0.14 409.95 0.35 0.57

 HUB 13.07 0.00 -0.02 409.95 -0.14 409.95 0.35 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.17 47.36 7.81 588.96 717.70 8.35 567.82 513.00 0.90

 MEAN 51.30 44.80 6.50 511.58 655.68 8.35 567.82 513.00 0.90

 HUB 45.72 38.84 6.88 420.18 587.13 8.35 567.82 513.00 0.90

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.16 279.93 414.48 1179.53 0.42 2.05 1.78 7.43

 MEAN 15.50 504.85 278.12 421.34 1175.46 0.43 2.13 1.86 5.75

 HUB 12.59 538.33 325.78 428.57 1171.54 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 576.74 509.79 296.81 0.43 5024.57 0.92 0.91

 MEAN 498.22 475.36 220.10 0.40 4312.40 0.92 0.91 0.91 1.52

 HUB 404.75 435.79 78.97 0.37 4103.36 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.51 1.16 9.30 607.18 1.04 587.13 522.68 0.61

 MEAN 10.30 1.13 9.09 603.51 1.04 583.08 521.40 0.66

 HUB 10.24 1.13 8.88 602.43 1.04 579.20 521.11 0.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.03 35.61 31.50 4.11 0.93 0.43 1.40

 MEAN 33.43 27.58 23.50 4.08 0.93 0.40 1.64

 HUB 37.24 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 562.4462 283.2169 485.9361 1171.3081 0.4802 -0.2007 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3246 8.8361 579.0233 521.8227 0.7241 30.2348 33.0000 2.7652

 

NASA/TM—2013-218094 J–65
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 491.4440 112.2217 478.4595 1177.3546 0.4174 0.0480 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2989 9.1500 585.0165 521.5825 410.5396 0.0404 0.3359

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 475.9580 0.0000 475.9580 1178.5280 0.4039 0.2579 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2200 586.2094 521.5773 0.0000 0.0600 0.0392 0.1035

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8809 10.3004 1.1330 604.3599 23.0852 256.3647 1.9873

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 144060.125 0.433 468.579 557678.188 0.872112E-03

 

Melt Ratio at Stator LE, Throat, TE

0.35606E+00 0.38833E+00 0.48076E+00

 trTOT = 1.3203 Tt4 = 604.3599 T1 = 457.7341

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 913339.38 2970.7881 186.3750 2.4153 0.8589 4.5362 1.3203 37.3740

NASA/TM—2013-218094 J–66
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.868 EfDer = 0.997 SH = 0.130098E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.602 3653.292 4.265 457.734 1.000 1.000 0.980

 W Kg/sec = 25.728 Wdry = 56.595 WH2O = 0.007 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 183.279 3888.954 1.381 0.248 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 146910.563 44410.617 1.550 831.557 536.498 619.754 1.155

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 424.01 -0.15 424.01 0.41 0.76 700.11

 MEAN 17.06 0.00 -0.02 424.01 -0.15 424.01 0.41 0.67

 HUB 12.51 0.00 -0.02 424.01 -0.15 424.01 0.41 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.20 50.47 6.73 657.70 782.65 3.80 443.28 448.86 8.06

 MEAN 52.07 47.20 4.87 543.89 689.75 3.80 443.28 448.86 8.06

 HUB 43.26 38.62 4.64 398.83 582.21 3.80 443.28 448.86 8.06

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 655.58 358.66 548.77 1045.69 0.63 7.29 6.52 16.04

 MEAN 18.04 692.41 402.28 563.57 1040.31 0.67 7.43 6.80 12.53

 HUB 15.00 802.07 537.39 595.43 1029.94 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 657.70 624.97 299.05 0.60 7402.14 0.92 0.91

 MEAN 575.01 589.44 172.72 0.57 7258.08 0.92 0.91 0.91 1.30

 HUB 478.21 598.36 59.17 0.58 8062.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.27 495.69 1.08 461.13 473.84 4.91

 MEAN 5.53 1.30 4.12 494.95 1.08 456.39 473.67 5.92

 HUB 5.68 1.33 3.82 499.08 1.09 447.34 476.99 8.54

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.17 28.59 24.20 4.39 0.93 0.33 1.80

 MEAN 35.52 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 42.07 -5.68 -9.30 3.62 0.92 0.14 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 735.7476 401.5017 616.5394 1036.4760 0.7099 -0.0813 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5712 3.9960 453.0434 474.9468 6.9890 33.0729 35.4000 2.3271

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 583.5778 142.7609 565.8466 1054.7712 0.5533 0.2912 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5420 4.5126 469.1888 473.9722 554.9116 0.0293 0.4069

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 579.9116 0.0000 579.9116 1055.1304 0.5496 0.3232 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5052 469.5346 474.0390 0.0000 0.0600 0.0449 0.2863

NASA/TM—2013-218094 J–67
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8688 5.5182 1.2939 496.5714 38.8398 224.1489 1.7376

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 241529.313 0.558 772.566 635462.438 0.202404E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.824 EfDer = 0.999 SH = 0.301958E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.602 3653.292 5.518 496.571 1.000 1.000 0.980

 W Kg/sec = 25.728 Wdry = 56.585 WH2O = 0.017 lbm/sec H2O = 0.129g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 147.531 3733.805 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 127165.727 44407.625 1.367 590.487 431.908 468.502 1.085 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 516.85 -0.18 516.85 0.49 0.79 669.57

 MEAN 18.08 0.00 -0.02 516.85 -0.18 516.85 0.49 0.73

 HUB 15.21 0.00 -0.02 516.85 -0.18 516.85 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.74 46.36 5.38 655.15 834.62 4.70 475.10 474.31 5.17

 MEAN 48.12 42.30 5.82 576.35 774.29 4.70 475.10 474.31 5.17

 HUB 43.18 37.84 5.34 484.91 708.83 4.70 475.10 474.31 5.17

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 586.72 287.93 511.21 1087.76 0.54 2.33 2.04 9.02

 MEAN 18.01 602.73 304.07 520.41 1083.83 0.56 2.40 2.13 7.35

 HUB 15.22 656.88 387.68 530.28 1080.21 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 651.01 627.03 363.08 0.58 5883.13 0.92 0.91

 MEAN 574.17 586.33 270.11 0.54 5479.41 0.92 0.91 0.91 1.43

 HUB 485.32 539.19 97.64 0.50 5904.37 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.52 526.72 1.06 499.05 489.90 2.40

 MEAN 6.62 1.20 5.38 524.65 1.06 495.45 489.00 2.70

 HUB 6.72 1.22 5.25 526.82 1.06 492.15 490.30 3.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.39 35.38 31.50 3.88 0.93 0.37 1.40

 MEAN 30.30 27.43 23.50 3.93 0.92 0.36 1.63

 HUB 36.17 10.43 6.50 3.93 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 675.2595 304.9183 602.4949 1077.1887 0.6269 -0.1905 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6708 5.1350 489.4259 490.0630 3.3334 26.8436 30.6000 3.7564

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 568.1255 120.4467 555.2110 1088.9066 0.5217 0.1163 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6476 5.5345 500.1282 489.4772 491.5697 0.0278 0.2803

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 595.3499 0.0000 595.3499 1086.1149 0.5481 0.1828 0.5911

NASA/TM—2013-218094 J–68
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4157 497.5855 489.6254 0.0000 0.0600 0.0442 0.0250

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8718 6.6263 1.2008 526.0610 29.4918 256.2146 1.9862

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183550.281 0.433 587.112 571298.625 0.351062E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.071 EfDer = 0.999 SH = 0.429605E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.602 3653.292 6.626 526.061 1.000 1.000 0.980

 W Kg/sec = 25.728 Wdry = 56.578 WH2O = 0.024 lbm/sec H2O = 0.213g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 126.456 3627.642 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 109924.320 44405.398 1.473 545.479 370.252 424.468 1.146

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 483.64 -0.17 483.64 0.44 0.73 635.34

 MEAN 17.74 0.00 -0.02 483.64 -0.17 483.64 0.44 0.68

 HUB 15.05 0.00 -0.02 483.64 -0.17 483.64 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.92 46.36 6.56 639.85 802.20 5.81 507.28 489.48 2.47

 MEAN 49.47 43.40 6.07 565.52 744.25 5.81 507.28 489.48 2.47

 HUB 44.78 38.84 5.94 479.81 681.39 5.81 507.28 489.48 2.47

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 562.03 288.00 482.63 1120.82 0.50 2.26 1.98 8.75

 MEAN 17.51 576.23 302.83 490.24 1117.25 0.52 2.34 2.07 6.78

 HUB 14.85 627.22 380.73 498.45 1113.93 0.56 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 631.56 592.43 343.56 0.53 5708.67 0.92 0.91

 MEAN 558.13 552.73 255.30 0.49 5304.40 0.92 0.91 0.91 1.46

 HUB 473.43 507.00 92.71 0.46 5656.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.69 555.29 1.06 529.92 502.68 1.36

 MEAN 7.83 1.18 6.55 553.22 1.05 526.56 501.88 1.50

 HUB 7.92 1.19 6.40 555.02 1.06 523.43 502.83 1.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.83 35.44 31.50 3.94 0.93 0.39 1.40

 MEAN 31.70 27.51 23.50 4.01 0.93 0.38 1.62

 HUB 37.37 10.54 6.50 4.04 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 639.4082 304.8135 562.0779 1112.0374 0.5750 -0.1726 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8807 6.3160 521.6870 502.6804 1.7460 28.4709 31.5000 3.0291

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 542.2081 118.2790 529.1500 1121.8253 0.4833 0.1230 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8612 6.7137 530.9083 502.2729 451.3937 0.0245 0.3057

 

NASA/TM—2013-218094 J–69
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 553.6009 0.0000 553.6009 1120.7443 0.4940 0.2138 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6505 529.9086 502.3473 0.0000 0.0600 0.0397 0.0760

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8778 7.8407 1.1833 554.5116 28.4523 244.5778 1.8960

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 177209.641 0.444 566.830 545608.688 0.511895E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.455 EfDer = 1.000 SH = 0.638257E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.602 3653.292 7.841 554.511 1.000 1.000 0.980

 W Kg/sec = 25.728 Wdry = 56.566 WH2O = 0.036 lbm/sec H2O = 0.361g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 109.722 3533.354 1.380 0.249 53.369 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96256.594 44401.758 1.598 513.330 321.313 395.845 1.232

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 450.03 -0.15 450.03 0.40 0.67 593.85

 MEAN 16.97 0.00 -0.02 450.03 -0.15 450.03 0.40 0.62

 HUB 14.32 0.00 -0.02 450.03 -0.15 450.03 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.77 46.36 7.41 614.03 761.41 7.04 538.26 502.34 1.49

 MEAN 50.26 43.80 6.46 541.04 703.86 7.04 538.26 502.34 1.49

 HUB 45.42 37.84 7.58 456.54 641.16 7.04 538.26 502.34 1.49

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 531.52 280.44 451.51 1150.99 0.46 2.16 1.89 8.34

 MEAN 16.57 542.30 289.90 458.31 1147.45 0.47 2.24 1.97 6.35

 HUB 13.89 586.56 356.75 465.59 1144.10 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 601.91 554.26 321.47 0.48 5297.67 0.92 0.91

 MEAN 528.39 516.65 238.49 0.45 4807.34 0.92 0.91 0.91 1.48

 HUB 442.83 473.48 86.08 0.41 4957.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.19 1.17 7.95 581.61 1.05 558.94 513.37 0.94

 MEAN 9.06 1.16 7.79 579.10 1.04 555.51 512.46 1.02

 HUB 9.10 1.16 7.62 579.87 1.05 552.27 512.90 1.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.84 35.45 31.50 3.95 0.93 0.40 1.40

 MEAN 32.31 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.46 10.47 6.50 3.97 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 585.6135 291.5269 507.8930 1144.4834 0.5117 -0.1192 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1019 7.6306 552.6876 513.0147 1.1067 29.8555 32.4000 2.5445

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 502.8220 112.7683 490.0135 1151.9388 0.4365 0.1487 2.2705

 

NASA/TM—2013-218094 J–70
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0870 7.9858 559.9144 512.7282 432.2457 0.0213 0.3279

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 498.6917 0.0000 498.6917 1152.2518 0.4328 0.2393 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9827 560.2440 512.7120 0.0000 0.0600 0.0388 0.1463

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8796 9.0637 1.1560 580.1875 25.6840 246.9404 1.9143

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 160131.672 0.442 512.204 539319.000 0.724789E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.72270E-01 0.93243E-01 0.15245E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.761 EfDer = 1.000 SH = 0.825575E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.602 3653.292 9.064 580.185 1.000 1.000 0.980

 W Kg/sec = 25.728 Wdry = 56.555 WH2O = 0.047 lbm/sec H2O = 0.526g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.089 3454.286 1.380 0.249 53.375 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85533.148 44398.488 1.792 509.668 284.367 384.739 1.353

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 402.77 -0.14 402.77 0.35 0.61 552.23

 MEAN 15.91 0.00 -0.02 402.77 -0.14 402.77 0.35 0.56

 HUB 13.07 0.00 -0.02 402.77 -0.14 402.77 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.42 47.36 8.06 584.06 709.58 8.35 567.18 512.67 0.93

 MEAN 51.56 44.80 6.76 507.32 647.87 8.35 567.18 512.67 0.93

 HUB 45.98 38.84 7.14 416.68 579.62 8.35 567.18 512.67 0.93

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.58 280.22 407.54 1178.67 0.42 2.05 1.78 7.43

 MEAN 15.50 498.76 277.78 414.24 1174.62 0.42 2.13 1.86 5.75

 HUB 12.59 531.38 323.82 421.31 1170.72 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 571.94 501.19 291.72 0.43 5029.76 0.92 0.91

 MEAN 494.08 467.31 216.30 0.40 4307.15 0.92 0.91 0.91 1.52

 HUB 401.38 428.39 77.56 0.37 4078.71 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.47 1.16 9.29 605.89 1.04 586.28 522.31 0.63

 MEAN 10.26 1.13 9.08 602.19 1.04 582.25 521.02 0.69

 HUB 10.19 1.12 8.87 601.03 1.04 578.39 520.70 0.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.51 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.84 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.55 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 554.8953 282.8748 477.3788 1170.6356 0.4740 -0.1979 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2832 8.8350 578.3593 521.4387 0.7541 30.6492 33.0000 2.3508

 

NASA/TM—2013-218094 J–71
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 482.6557 110.2148 469.9034 1176.6946 0.4102 0.0593 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2597 9.1517 584.3622 521.1989 410.5396 0.0391 0.3418

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 467.5861 0.0000 467.5861 1177.8152 0.3970 0.2646 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2182 585.5018 521.1933 0.0000 0.0600 0.0385 0.1134

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 10.2605 1.1320 603.0186 22.8501 253.9303 1.9685

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 142599.391 0.436 456.124 548068.625 0.891420E-03

 

Melt Ratio at Stator LE, Throat, TE

0.35847E+00 0.39100E+00 0.48397E+00

 trTOT = 1.3174 Tt4 = 603.0186 T1 = 457.7339

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 905020.31 2894.8354 183.2794 2.4059 0.8625 4.8684 1.3174 37.3740

NASA/TM—2013-218094 J–72
 10μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.887 EfDer = 0.985 SH = 0.251326E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.643 3973.534 4.265 477.916 1.000 1.000 0.980

 W Kg/sec = 28.020 Wdry = 61.628 WH2O = 0.015 lbm/sec H2O = 0.087g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 203.960 4139.589 1.381 0.248 53.356 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171507.766 48363.531 1.393 831.557 597.079 619.754 1.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 495.00 -0.17 495.00 0.47 0.83 745.23

 MEAN 17.06 0.00 -0.02 495.00 -0.17 495.00 0.47 0.74

 HUB 12.51 0.00 -0.02 495.00 -0.17 495.00 0.47 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.32 50.47 4.85 715.36 870.06 3.66 458.22 461.82 7.21

 MEAN 50.09 47.20 2.89 591.57 771.48 3.66 458.22 461.82 7.21

 HUB 41.24 38.62 2.62 433.79 658.29 3.66 458.22 461.82 7.21

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 742.65 361.53 648.71 1061.48 0.70 7.29 6.52 16.04

 MEAN 18.04 788.67 420.76 667.05 1055.95 0.75 7.43 6.80 12.53

 HUB 15.00 932.12 592.42 719.64 1041.69 0.89 7.49 7.25 9.22 

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.36 738.94 353.83 0.70 7461.79 0.92 0.90

 MEAN 625.41 697.74 204.65 0.66 7591.77 0.92 0.90 0.90 1.21

 HUB 520.13 723.26 72.28 0.69 8888.42 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.61 1.31 4.06 519.52 1.09 475.18 485.52 4.61

 MEAN 5.63 1.32 3.91 520.24 1.09 470.24 486.40 5.52

 HUB 5.89 1.38 3.52 527.47 1.10 457.62 492.35 8.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.13 28.61 24.20 4.41 0.93 0.27 1.80

 MEAN 32.24 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.46 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 852.6810 419.9444 742.0995 1048.8843 0.8129 -0.1075 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6918 3.7031 463.9675 488.4622 7.1779 29.5049 35.4000 5.8951

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 694.0648 169.7894 672.9766 1070.9309 0.6481 0.2293 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6315 4.2603 483.6920 486.2973 554.9116 0.0421 0.3596

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 696.1580 0.0000 696.1580 1070.6415 0.6502 0.2543 1.3089

NASA/TM—2013-218094 J–73
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.2088 483.4649 486.3371 0.0000 0.0600 0.0731 0.2020

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8231 5.5731 1.3068 522.4092 44.4953 237.8157 1.8435

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 276805.969 0.541 964.257 687608.063 0.363376E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.522 EfDer = 0.989 SH = 0.505407E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.643 3973.534 5.573 522.409 1.000 1.000 0.980

 W Kg/sec = 28.020 Wdry = 61.612 WH2O = 0.031 lbm/sec H2O = 0.200g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.174 3959.403 1.381 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 149924.984 48358.711 1.236 590.487 477.766 468.502 0.981

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 609.35 -0.21 609.35 0.56 0.87 710.03

 MEAN 18.08 0.00 -0.02 609.35 -0.21 609.35 0.56 0.81

 HUB 15.21 0.00 -0.02 609.35 -0.21 609.35 0.56 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.47 46.36 3.11 712.58 937.75 4.50 492.59 486.39 3.98

 MEAN 45.82 42.30 3.52 626.87 874.38 4.50 492.59 486.39 3.98

 HUB 40.89 37.84 3.05 527.42 806.04 4.50 492.59 486.39 3.98

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 660.93 281.69 597.90 1109.66 0.60 2.33 2.04 9.02

 MEAN 18.01 681.14 307.45 607.80 1106.04 0.62 2.40 2.13 7.35

 HUB 15.22 743.65 412.53 618.74 1102.80 0.67 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.08 734.36 426.38 0.66 5756.50 0.92 0.91

 MEAN 624.51 685.53 317.05 0.62 5540.98 0.92 0.91 0.91 1.37

 HUB 527.87 629.39 115.34 0.57 6283.08 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.22 5.35 554.47 1.06 519.39 500.23 1.81

 MEAN 6.73 1.21 5.23 553.27 1.06 516.01 499.89 1.99

 HUB 6.90 1.24 5.11 557.40 1.07 512.99 501.96 2.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.23 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.83 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.69 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 781.0240 308.3146 717.5936 1095.2996 0.7131 -0.2364 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7882 4.8556 506.0699 501.4444 2.7145 23.2508 30.6000 7.3492

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 674.5256 143.0042 659.1923 1108.6971 0.6084 0.0229 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7383 5.2639 518.5141 500.4244 491.5697 0.0416 0.2221

 

NASA/TM—2013-218094 J–74
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 718.1754 0.0000 718.1754 1103.4460 0.6508 0.0994 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0477 513.6384 500.7180 0.0000 0.0600 0.0742 -0.1143

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8246 6.6870 1.1999 555.0457 32.6383 280.2812 2.1727

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 203279.031 0.405 708.125 622546.625 0.576161E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.917 EfDer = 0.992 SH = 0.684619E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.643 3973.534 6.687 555.045 1.000 1.000 0.980

 W Kg/sec = 28.020 Wdry = 61.601 WH2O = 0.042 lbm/sec H2O = 0.315g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.177 3841.234 1.380 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 128970.945 48355.305 1.329 545.479 410.496 424.468 1.034

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 567.44 -0.20 567.44 0.51 0.80 672.75

 MEAN 17.74 0.00 -0.02 567.44 -0.20 567.44 0.51 0.75

 HUB 15.05 0.00 -0.02 567.44 -0.20 567.44 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.82 46.36 4.46 695.94 898.10 5.62 529.21 500.12 1.73

 MEAN 47.32 43.40 3.92 615.09 837.00 5.62 529.21 500.12 1.73

 HUB 42.62 38.84 3.78 521.87 771.06 5.62 529.21 500.12 1.73

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 630.56 285.10 562.43 1146.54 0.55 2.26 1.98 8.75

 MEAN 17.51 648.79 308.48 570.76 1143.18 0.57 2.34 2.07 6.78

 HUB 14.85 707.88 405.90 579.95 1140.12 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 691.23 401.83 0.60 5651.73 0.92 0.91

 MEAN 607.05 644.14 298.57 0.56 5403.93 0.92 0.91 0.91 1.40

 HUB 514.93 590.11 109.03 0.52 6030.54 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.02 1.20 6.55 586.49 1.06 554.59 512.24 0.95

 MEAN 7.96 1.19 6.41 585.12 1.05 551.34 511.84 1.02

 HUB 8.12 1.21 6.28 588.60 1.06 548.39 513.38 1.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.88 35.54 31.50 4.04 0.93 0.34 1.40

 MEAN 28.39 27.61 23.50 4.11 0.92 0.34 1.62

 HUB 34.99 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 731.6923 310.5068 662.5399 1135.2686 0.6445 -0.2045 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0167 6.0838 543.7951 512.8862 1.2540 25.1107 31.5000 6.3893

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 638.9168 139.3754 623.5296 1145.8760 0.5576 0.0381 2.3726

 

NASA/TM—2013-218094 J–75
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9767 6.4758 553.9929 512.2767 451.3937 0.0347 0.2557

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 656.2914 0.0000 656.2914 1143.9785 0.5737 0.1468 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3675 552.1917 512.3372 0.0000 0.0600 0.0594 -0.0288

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8463 7.9367 1.1869 586.7342 31.6924 265.5565 2.0586

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 197585.516 0.419 688.292 588391.875 0.786145E-03

 

Melt Ratio at Stator LE, Throat, TE

0.12819E-01 0.21457E-01 0.52098E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.524 EfDer = 0.995 SH = 0.911491E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.643 3973.534 7.937 586.733 1.000 1.000 0.980

 W Kg/sec = 28.020 Wdry = 61.587 WH2O = 0.056 lbm/sec H2O = 0.483g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.430 3736.065 1.380 0.249 53.378 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112085.313 48350.996 1.443 513.330 355.669 395.845 1.113 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 524.03 -0.18 524.03 0.45 0.73 627.92

 MEAN 16.97 0.00 -0.02 524.03 -0.18 524.03 0.45 0.68

 HUB 14.32 0.00 -0.02 524.03 -0.18 524.03 0.45 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.89 46.36 5.53 667.85 849.04 6.91 564.72 512.05 0.92

 MEAN 48.32 43.80 4.52 588.47 788.11 6.91 564.72 512.05 0.92

 HUB 43.47 37.84 5.63 496.56 722.05 6.91 564.72 512.05 0.92

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 593.47 281.47 522.47 1180.48 0.50 2.16 1.89 8.34

 MEAN 16.57 608.10 297.71 530.24 1176.94 0.52 2.24 1.97 6.35

 HUB 13.89 659.86 381.15 538.65 1173.65 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.68 642.07 373.20 0.54 5317.66 0.92 0.91

 MEAN 574.71 598.23 277.00 0.51 4937.27 0.92 0.91 0.91 1.42

 HUB 481.64 547.95 100.50 0.47 5296.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.34 1.18 7.88 616.29 1.05 588.06 522.44 0.57

 MEAN 9.23 1.16 7.72 614.17 1.05 584.54 521.80 0.61

 HUB 9.33 1.18 7.55 616.17 1.05 581.27 522.66 0.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.31 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.31 27.58 23.50 4.08 0.92 0.36 1.62

 HUB 35.28 10.57 6.50 4.07 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 662.5455 299.3839 591.0464 1172.6725 0.5650 -0.1362 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2876 7.4999 580.3729 522.4446 0.6703 26.8637 32.4000 5.5363

 

NASA/TM—2013-218094 J–76
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 585.7753 131.3723 570.8538 1180.4033 0.4963 0.0794 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2584 7.8418 588.0479 522.0901 432.2457 0.0284 0.2859

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 581.0762 0.0000 581.0762 1180.8068 0.4921 0.1893 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.8384 588.4838 522.0370 0.0000 0.0600 0.0469 0.0772

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8634 9.2290 1.1628 615.5295 28.8101 265.6786 2.0595

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 179829.063 0.420 626.437 576203.063 0.988822E-03

 

Melt Ratio at Stator LE, Throat, TE

0.21618E+00 0.24742E+00 0.33097E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.141 EfDer = 0.997 SH = 0.107853E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.643 3973.534 9.229 615.525 1.000 1.000 0.980

 W Kg/sec = 28.020 Wdry = 61.577 WH2O = 0.066 lbm/sec H2O = 0.650g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 106.959 3647.629 1.379 0.250 53.383 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98561.344 48347.813 1.627 509.668 313.341 384.739 1.228

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 464.12 -0.16 464.12 0.39 0.66 583.14

 MEAN 15.91 0.00 -0.02 464.12 -0.16 464.12 0.39 0.61

 HUB 13.07 0.00 -0.02 464.12 -0.16 464.12 0.39 0.54

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.86 47.36 6.50 635.26 786.87 8.32 598.28 521.85 0.52

 MEAN 49.94 44.80 5.14 551.79 721.15 8.32 598.28 521.85 0.52

 HUB 44.33 38.84 5.49 453.21 648.81 8.32 598.28 521.85 0.52

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 547.92 287.10 466.68 1212.04 0.45 2.05 1.78 7.43

 MEAN 15.50 555.66 288.72 474.76 1207.69 0.46 2.13 1.86 5.75

 HUB 12.59 594.96 347.00 483.29 1203.56 0.49 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 574.46 334.99 0.47 5153.42 0.92 0.91

 MEAN 537.39 535.94 248.67 0.44 4477.06 0.92 0.91 0.91 1.47

 HUB 436.57 491.52 89.57 0.41 4370.78 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.73 1.16 9.35 644.13 1.05 620.10 531.26 0.35

 MEAN 10.53 1.14 9.12 640.38 1.04 615.66 530.10 0.38

 HUB 10.49 1.14 8.90 639.79 1.04 611.45 530.03 0.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.60 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.31 27.64 23.50 4.14 0.92 0.38 1.64

 HUB 35.68 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 624.0308 294.0175 550.4254 1202.3212 0.5190 -0.2164 2.0437

 

NASA/TM—2013-218094 J–77
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5558 8.8066 610.2623 530.5735 0.4180 28.1095 33.0000 4.8905

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 557.6596 127.3420 542.9257 1208.4891 0.4615 -0.0145 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.5123 9.1025 616.5341 530.2875 410.5396 0.0497 0.3069

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 538.8945 0.0000 538.8945 1210.0583 0.4453 0.2238 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1981 618.1707 530.2773 0.0000 0.0600 0.0447 0.0510

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8712 10.5197 1.1399 641.4078 25.9052 269.5884 2.0898

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161872.688 0.418 563.886 580185.063 0.113559E-02

 

Melt Ratio at Stator LE, Throat, TE

0.59064E+00 0.62810E+00 0.73545E+00

 trTOT = 1.3421 Tt4 = 641.4078 T1 = 477.9159

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1019372.25 3550.9966 203.9595 2.4667 0.8252 2.8872 1.3421 37.3740

NASA/TM—2013-218094 J–78
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.008 EfDer = 0.992 SH = 0.267600E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.935 3823.779 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 26.334 Wdry = 57.919 WH2O = 0.016 lbm/sec H2O = 0.094g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 191.689 3983.575 1.381 0.248 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 158584.516 45453.500 1.482 831.557 561.164 619.754 1.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 457.70 -0.16 457.70 0.44 0.79 717.14

 MEAN 17.06 0.00 -0.02 457.70 -0.16 457.70 0.44 0.70

 HUB 12.51 0.00 -0.02 457.70 -0.16 457.70 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.39 50.47 5.92 688.40 826.80 3.74 461.07 461.75 6.87

 MEAN 51.21 47.20 4.01 569.28 730.58 3.74 461.07 461.75 6.87

 HUB 42.38 38.62 3.76 417.44 619.58 3.74 461.07 461.75 6.87

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 697.45 364.02 594.91 1065.86 0.65 7.29 6.52 16.04

 MEAN 18.04 738.41 414.38 611.18 1060.37 0.70 7.43 6.80 12.53

 HUB 15.00 861.37 565.27 649.94 1048.65 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 688.40 677.60 324.37 0.64 7513.05 0.92 0.91

 MEAN 601.84 639.29 187.46 0.60 7476.44 0.92 0.91 0.91 1.26

 HUB 500.53 653.16 64.74 0.62 8481.07 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.57 1.31 4.19 518.22 1.08 479.12 484.71 4.34

 MEAN 5.56 1.30 4.04 518.03 1.08 474.19 485.04 5.18

 HUB 5.76 1.35 3.72 523.42 1.10 463.77 489.33 7.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.46 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.14 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.01 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 789.2426 413.5740 672.2057 1055.4644 0.7478 -0.0903 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6154 3.8907 469.8237 486.5876 6.2537 31.6019 35.4000 3.7981

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 633.6667 155.0142 614.4136 1075.2515 0.5893 0.2659 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5770 4.4213 487.6180 484.9770 554.9116 0.0333 0.3877

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 631.1306 0.0000 631.1306 1075.5068 0.5868 0.2971 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4030 487.8806 485.0522 0.0000 0.0600 0.0537 0.2549

NASA/TM—2013-218094 J–79
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8544 5.5433 1.2999 519.8853 41.9720 229.8864 1.7821

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 261146.359 0.551 854.975 635796.063 0.397570E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.877 EfDer = 0.997 SH = 0.562735E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.935 3823.779 5.543 519.885 1.000 1.000 0.980

 W Kg/sec = 26.334 Wdry = 57.902 WH2O = 0.033 lbm/sec H2O = 0.228g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 153.808 3819.417 1.381 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 137596.953 45448.234 1.311 590.487 450.358 468.502 1.040

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 559.24 -0.19 559.24 0.52 0.82 684.93

 MEAN 18.08 0.00 -0.02 559.24 -0.19 559.24 0.52 0.76

 HUB 15.21 0.00 -0.02 559.24 -0.19 559.24 0.52 0.70

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.81 46.36 4.45 685.73 885.01 4.63 494.77 485.31 4.18

 MEAN 47.18 42.30 4.88 603.25 822.74 4.63 494.77 485.31 4.18

 HUB 42.24 37.84 4.40 507.54 755.34 4.63 494.77 485.31 4.18

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 622.62 289.12 551.42 1110.74 0.56 2.33 2.04 9.02

 MEAN 18.01 640.64 309.18 561.09 1106.86 0.58 2.40 2.13 7.35

 HUB 15.22 698.87 402.22 571.53 1103.33 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 681.39 676.71 392.27 0.61 5907.87 0.92 0.91

 MEAN 600.97 632.43 291.79 0.57 5571.72 0.92 0.91 0.91 1.40

 HUB 507.97 581.23 105.76 0.53 6125.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.74 1.22 5.46 551.54 1.06 520.42 499.29 1.98

 MEAN 6.67 1.20 5.33 549.74 1.06 516.79 498.68 2.20

 HUB 6.79 1.23 5.20 552.71 1.06 513.49 500.28 2.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.67 35.43 31.50 3.93 0.93 0.35 1.40

 MEAN 28.86 27.48 23.50 3.98 0.92 0.35 1.63

 HUB 35.14 10.48 6.50 3.98 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 723.5880 310.0432 653.7988 1098.7770 0.6585 -0.2065 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7210 5.0409 509.3012 499.9687 2.7838 25.3711 30.6000 5.2289

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 615.8015 130.5543 601.8031 1111.2142 0.5542 0.0804 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6896 5.4441 520.8893 499.1032 491.5697 0.0323 0.2578

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 648.2669 0.0000 648.2669 1107.6733 0.5853 0.1521 0.5911

NASA/TM—2013-218094 J–80
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2964 517.5992 499.3317 0.0000 0.0600 0.0537 -0.0248

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8576 6.6596 1.2014 551.3298 31.4465 265.6610 2.0594

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195895.484 0.422 641.348 573125.125 0.641799E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.203 EfDer = 0.998 SH = 0.761594E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.935 3823.779 6.660 551.329 1.000 1.000 0.980

 W Kg/sec = 26.334 Wdry = 57.890 WH2O = 0.044 lbm/sec H2O = 0.358g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 131.841 3708.900 1.380 0.249 53.373 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 118631.008 45444.688 1.413 545.479 386.105 424.468 1.099

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 521.95 -0.18 521.95 0.47 0.76 649.57

 MEAN 17.74 0.00 -0.02 521.95 -0.18 521.95 0.47 0.70

 HUB 15.05 0.00 -0.02 521.95 -0.18 521.95 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.08 46.36 5.72 669.71 849.22 5.75 529.48 498.98 1.95

 MEAN 48.60 43.40 5.20 591.91 789.30 5.75 529.48 498.98 1.95

 HUB 43.91 38.84 5.07 502.20 724.44 5.75 529.48 498.98 1.95

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 595.27 290.77 519.42 1145.67 0.52 2.26 1.98 8.75

 MEAN 17.51 611.32 309.01 527.47 1142.11 0.54 2.34 2.07 6.78

 HUB 14.85 666.22 395.40 536.19 1138.83 0.59 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 661.04 637.88 370.26 0.56 5763.77 0.92 0.91

 MEAN 584.17 594.93 275.16 0.52 5412.96 0.92 0.91 0.91 1.43

 HUB 495.53 545.46 100.12 0.48 5874.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.98 1.20 6.65 582.19 1.06 553.76 511.14 1.10

 MEAN 7.89 1.19 6.51 580.31 1.05 550.33 510.54 1.19

 HUB 8.01 1.20 6.37 582.78 1.06 547.17 511.72 1.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.24 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.36 27.55 23.50 4.05 0.92 0.37 1.62

 HUB 36.41 10.58 6.50 4.08 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 682.3142 311.0417 607.2938 1135.9113 0.6007 -0.1840 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9459 6.2454 544.4240 511.4592 1.4001 27.1205 31.5000 4.3795

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 585.6744 127.7609 571.5695 1146.1219 0.5110 0.0905 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9202 6.6429 554.2495 510.8961 451.3937 0.0278 0.2863

 

NASA/TM—2013-218094 J–81
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 598.8409 0.0000 598.8409 1144.7980 0.5231 0.1900 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5684 553.0011 510.9673 0.0000 0.0600 0.0446 0.0391

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8699 7.8958 1.1856 581.7531 30.4279 252.6442 1.9585

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189747.906 0.434 621.222 545341.063 0.868408E-03

 

Melt Ratio at Stator LE, Throat, TE

0.17606E-01 0.28398E-01 0.65042E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.695 EfDer = 0.999 SH = 0.995966E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.935 3823.779 7.896 581.751 1.000 1.000 0.980

 W Kg/sec = 26.334 Wdry = 57.877 WH2O = 0.058 lbm/sec H2O = 0.537g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.227 3610.618 1.380 0.249 53.381 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 103499.617 45440.496 1.534 513.330 334.588 395.845 1.183

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 483.89 -0.17 483.89 0.42 0.70 606.84

 MEAN 16.97 0.00 -0.02 483.89 -0.17 483.89 0.42 0.65

 HUB 14.32 0.00 -0.02 483.89 -0.17 483.89 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.03 46.36 6.67 642.68 804.61 7.01 562.99 510.77 1.07

 MEAN 49.49 43.80 5.69 566.29 745.00 7.01 562.99 510.77 1.07

 HUB 44.65 37.84 6.81 477.84 680.18 7.01 562.99 510.77 1.07

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 561.78 284.79 484.25 1177.63 0.48 2.16 1.89 8.34

 MEAN 16.57 574.24 296.89 491.53 1174.02 0.49 2.24 1.97 6.35

 HUB 13.89 622.01 370.86 499.37 1170.64 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 630.00 594.70 345.21 0.50 5380.06 0.92 0.91

 MEAN 553.05 554.28 256.16 0.47 4923.42 0.92 0.91 0.91 1.46

 HUB 463.49 507.88 92.63 0.43 5153.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.27 1.17 7.95 610.52 1.05 585.23 521.12 0.67

 MEAN 9.15 1.16 7.78 608.08 1.05 581.65 520.34 0.73

 HUB 9.21 1.17 7.62 609.31 1.05 578.31 520.95 0.78

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.46 35.48 31.50 3.98 0.93 0.39 1.40

 MEAN 31.13 27.53 23.50 4.03 0.92 0.38 1.62

 HUB 36.60 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 622.1276 298.5581 545.8074 1170.5662 0.5315 -0.1254 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1957 7.6060 578.2969 520.9285 0.7851 28.6788 32.4000 3.7212

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 540.4827 121.2145 526.7150 1178.2319 0.4587 0.1222 2.2705

 

NASA/TM—2013-218094 J–82
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1764 7.9588 585.8972 520.5834 432.2457 0.0235 0.3114

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 536.0584 0.0000 536.0584 1178.5774 0.4548 0.2201 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9559 586.2740 520.5419 0.0000 0.0600 0.0413 0.1202

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8750 9.1511 1.1590 609.2860 27.5486 254.0258 1.9692

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171993.766 0.433 563.096 537237.438 0.107627E-02

 

Melt Ratio at Stator LE, Throat, TE

0.23544E+00 0.26827E+00 0.35570E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.125 EfDer = 0.999 SH = 0.116871E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.935 3823.779 9.151 609.282 1.000 1.000 0.980

 W Kg/sec = 26.334 Wdry = 57.867 WH2O = 0.068 lbm/sec H2O = 0.712g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 100.864 3528.095 1.379 0.250 53.386 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91586.172 45437.406 1.725 509.668 295.500 384.739 1.302

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 431.27 -0.15 431.27 0.36 0.63 564.03

 MEAN 15.91 0.00 -0.02 431.27 -0.15 431.27 0.36 0.58

 HUB 13.07 0.00 -0.02 431.27 -0.15 431.27 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.80 47.36 7.44 611.32 748.25 8.36 594.39 520.39 0.62

 MEAN 50.92 44.80 6.12 531.00 684.19 8.36 594.39 520.39 0.62

 HUB 45.33 38.84 6.49 436.13 613.46 8.36 594.39 520.39 0.62

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 521.24 286.72 435.30 1207.07 0.43 2.05 1.78 7.43

 MEAN 15.50 526.84 285.74 442.62 1202.85 0.44 2.13 1.86 5.75

 HUB 12.59 562.48 337.02 450.33 1198.80 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 598.64 535.52 311.91 0.44 5146.50 0.92 0.91

 MEAN 517.14 499.45 231.40 0.42 4430.65 0.92 0.91 0.91 1.50

 HUB 420.11 457.94 83.10 0.38 4244.98 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.60 1.16 9.34 636.77 1.05 615.02 529.63 0.42

 MEAN 10.39 1.14 9.12 632.94 1.04 610.73 528.43 0.46

 HUB 10.34 1.13 8.91 631.95 1.04 606.63 528.22 0.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.37 35.62 31.50 4.12 0.93 0.42 1.40

 MEAN 32.85 27.60 23.50 4.10 0.93 0.40 1.64

 HUB 36.81 10.45 6.50 3.95 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 588.1789 290.9794 511.1609 1198.3173 0.4908 -0.2047 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4154 8.8537 606.2010 528.8679 0.5032 29.6508 33.0000 3.3492

 

NASA/TM—2013-218094 J–83
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 517.1089 118.0823 503.4464 1204.5104 0.4293 0.0315 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3857 9.1656 612.4815 528.5967 410.5396 0.0425 0.3280

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 500.5372 0.0000 500.5372 1205.7922 0.4151 0.2488 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2422 613.8197 528.5812 0.0000 0.0600 0.0404 0.0896

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 10.3884 1.1352 633.8625 24.6042 259.8961 2.0147

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 153772.516 0.429 503.441 544149.875 0.122817E-02

 

Melt Ratio at Stator LE, Throat, TE

0.61668E+00 0.65511E+00 0.76407E+00

 trTOT = 1.3263 Tt4 = 633.8625 T1 = 477.9154

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 972556.00 3184.0815 191.6885 2.4360 0.8514 4.0084 1.3263 37.3740

NASA/TM—2013-218094 J–84
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.443 EfDer = 0.995 SH = 0.273393E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.633 3776.794 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 25.742 Wdry = 56.617 WH2O = 0.015 lbm/sec H2O = 0.097g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 187.381 3934.627 1.381 0.248 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154217.516 44431.965 1.516 831.557 548.556 619.754 1.130

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.09 -0.15 445.09 0.43 0.78 708.33

 MEAN 17.06 0.00 -0.02 445.09 -0.15 445.09 0.43 0.69

 HUB 12.51 0.00 -0.02 445.09 -0.15 445.09 0.43 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.80 50.47 6.33 679.94 812.79 3.77 461.99 461.73 6.77

 MEAN 51.64 47.20 4.44 562.28 717.25 3.77 461.99 461.73 6.77

 HUB 42.82 38.62 4.20 412.31 606.83 3.77 461.99 461.73 6.77

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 683.05 365.33 577.14 1067.25 0.64 7.29 6.52 16.04

 MEAN 18.04 722.32 412.69 592.82 1061.75 0.68 7.43 6.80 12.53

 HUB 15.00 839.47 556.87 628.18 1050.65 0.80 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 679.94 657.32 314.61 0.62 7540.00 0.92 0.91

 MEAN 594.45 620.05 181.76 0.58 7445.83 0.92 0.91 0.91 1.28

 HUB 494.38 631.28 62.49 0.60 8354.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.24 517.87 1.08 480.36 484.49 4.27

 MEAN 5.54 1.30 4.08 517.37 1.08 475.43 484.64 5.09

 HUB 5.72 1.34 3.77 522.19 1.09 465.54 488.48 7.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.33 28.60 24.20 4.40 0.93 0.32 1.80

 MEAN 34.84 17.05 12.70 4.35 0.92 0.27 2.22

 HUB 41.56 -5.68 -9.30 3.62 0.92 0.12 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 769.6121 411.8847 650.1182 1057.3843 0.7278 -0.0855 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5926 3.9469 471.5392 486.0685 6.0361 32.3564 35.4000 3.0436

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 614.1564 150.2414 595.4961 1076.5815 0.5705 0.2790 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5594 4.4703 488.8297 484.5868 554.9116 0.0310 0.3976

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 610.8799 0.0000 610.8799 1076.9081 0.5673 0.3108 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4584 489.1566 484.6760 0.0000 0.0600 0.0488 0.2715

NASA/TM—2013-218094 J–85
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8623 5.5314 1.2971 519.1391 41.2260 226.9377 1.7592

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 256516.703 0.555 820.946 618288.000 0.410099E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.363 EfDer = 0.998 SH = 0.583472E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.633 3776.794 5.531 519.139 1.000 1.000 0.980

 W Kg/sec = 25.742 Wdry = 56.600 WH2O = 0.033 lbm/sec H2O = 0.238g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.569 3775.197 1.381 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 133608.828 44426.563 1.339 590.487 440.880 468.502 1.063

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 543.03 -0.19 543.03 0.50 0.80 677.00

 MEAN 18.08 0.00 -0.02 543.03 -0.19 543.03 0.50 0.74 

 HUB 15.21 0.00 -0.02 543.03 -0.19 543.03 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.29 46.36 4.93 677.30 868.26 4.67 495.46 484.98 4.25 

 MEAN 47.66 42.30 5.36 595.84 806.31 4.67 495.46 484.98 4.25

 HUB 42.72 37.84 4.88 501.30 739.17 4.67 495.46 484.98 4.25

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 610.54 291.85 536.26 1111.12 0.55 2.33 2.04 9.02

 MEAN 18.01 627.72 310.04 545.81 1107.16 0.57 2.40 2.13 7.35

 HUB 15.22 684.47 399.10 556.08 1103.54 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 673.02 657.92 381.16 0.59 5963.48 0.92 0.91

 MEAN 593.59 615.07 283.55 0.56 5587.12 0.92 0.91 0.91 1.42

 HUB 501.73 565.47 102.63 0.51 6078.38 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.49 550.70 1.06 520.77 499.01 2.04

 MEAN 6.65 1.20 5.36 548.71 1.06 517.07 498.32 2.28

 HUB 6.75 1.22 5.23 551.31 1.06 513.69 499.76 2.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.56 35.40 31.50 3.90 0.93 0.36 1.40

 MEAN 29.60 27.45 23.50 3.95 0.92 0.36 1.63

 HUB 35.67 10.46 6.50 3.96 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 705.9249 310.9064 633.7721 1099.7820 0.6419 -0.1980 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6967 5.0928 510.2377 499.5317 2.8175 26.1310 30.6000 4.4690

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 597.2708 126.6257 583.6937 1111.9688 0.5371 0.0993 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6700 5.4944 521.6028 498.7025 491.5697 0.0298 0.2696

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 627.1501 0.0000 627.1501 1108.8125 0.5656 0.1684 0.5911

NASA/TM—2013-218094 J–86
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3628 518.6701 498.9189 0.0000 0.0600 0.0484 0.0018

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8656 6.6449 1.2013 550.2366 31.0993 260.7137 2.0210

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193746.766 0.428 620.059 556704.125 0.665570E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.653 EfDer = 0.999 SH = 0.789502E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.633 3776.794 6.645 550.236 1.000 1.000 0.980

 W Kg/sec = 25.742 Wdry = 56.588 WH2O = 0.045 lbm/sec H2O = 0.373g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 129.036 3666.965 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115329.328 44422.965 1.443 545.479 377.897 424.468 1.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 507.42 -0.17 507.42 0.45 0.74 642.23

 MEAN 17.74 0.00 -0.02 507.42 -0.17 507.42 0.45 0.69

 HUB 15.05 0.00 -0.02 507.42 -0.17 507.42 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.52 46.36 6.16 661.48 833.83 5.78 529.58 498.62 2.03

 MEAN 49.05 43.40 5.65 584.64 774.26 5.78 529.58 498.62 2.03

 HUB 44.36 38.84 5.52 496.03 709.71 5.78 529.58 498.62 2.03

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 584.27 292.73 505.65 1145.43 0.51 2.26 1.98 8.75

 MEAN 17.51 599.53 309.33 513.57 1141.82 0.53 2.34 2.07 6.78

 HUB 14.85 652.98 392.13 522.12 1138.48 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.91 620.81 360.18 0.54 5802.58 0.92 0.91

 MEAN 576.99 579.13 267.67 0.51 5418.34 0.92 0.91 0.91 1.45

 HUB 489.44 531.11 97.31 0.47 5825.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.96 1.20 6.68 580.92 1.06 553.53 510.80 1.15

 MEAN 7.87 1.18 6.53 578.88 1.05 550.05 510.13 1.25

 HUB 7.96 1.20 6.39 581.04 1.06 546.84 511.20 1.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.07 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 31.06 27.53 23.50 4.03 0.92 0.37 1.62

 HUB 36.91 10.56 6.50 4.06 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 667.0779 311.3563 589.9578 1136.0880 0.5872 -0.1779 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9157 6.2866 544.5981 511.0149 1.4518 27.8233 31.5000 3.6767

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 569.0026 124.1241 555.2992 1146.1863 0.4964 0.1076 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8935 6.6848 554.3179 510.4614 451.3937 0.0259 0.2966

 

NASA/TM—2013-218094 J–87
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 581.2382 0.0000 581.2382 1144.9886 0.5076 0.2032 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6177 553.1912 510.5340 0.0000 0.0600 0.0412 0.0595

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8750 7.8722 1.1847 580.2751 30.0434 248.3842 1.9255

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 187366.859 0.440 599.641 530820.438 0.898449E-03

 

Melt Ratio at Stator LE, Throat, TE

0.19188E-01 0.30685E-01 0.69269E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.096 EfDer = 0.999 SH = 0.102736E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.633 3776.794 7.872 580.273 1.000 1.000 0.980

 W Kg/sec = 25.742 Wdry = 56.574 WH2O = 0.058 lbm/sec H2O = 0.556g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 111.853 3570.792 1.380 0.249 53.382 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 100785.273 44418.813 1.567 513.330 327.642 395.845 1.208

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 471.20 -0.16 471.20 0.41 0.68 600.14

 MEAN 16.97 0.00 -0.02 471.20 -0.16 471.20 0.41 0.63

 HUB 14.32 0.00 -0.02 471.20 -0.16 471.20 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.42 46.36 7.06 634.79 790.69 7.03 562.48 510.36 1.12

 MEAN 49.90 43.80 6.10 559.33 731.48 7.03 562.48 510.36 1.12

 HUB 45.06 37.84 7.22 471.97 667.04 7.03 562.48 510.36 1.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 551.95 285.90 472.13 1176.77 0.47 2.16 1.89 8.34

 MEAN 16.57 563.65 296.68 479.25 1173.16 0.48 2.24 1.97 6.35

 HUB 13.89 610.10 367.64 486.89 1169.75 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.26 579.70 336.36 0.49 5400.90 0.92 0.91

 MEAN 546.25 540.34 249.57 0.46 4919.88 0.92 0.91 0.91 1.47

 HUB 457.80 495.17 90.16 0.42 5108.84 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.24 1.17 7.96 608.79 1.05 584.39 520.69 0.71

 MEAN 9.11 1.16 7.79 606.25 1.04 580.80 519.87 0.77

 HUB 9.16 1.16 7.63 607.25 1.05 577.43 520.40 0.82

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.20 35.47 31.50 3.97 0.93 0.39 1.40

 MEAN 31.76 27.51 23.50 4.01 0.93 0.39 1.62

 HUB 37.06 10.49 6.50 3.99 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 609.5923 298.3479 531.5932 1169.9271 0.5211 -0.1221 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1535 7.6258 577.6688 520.4399 0.8257 29.3026 32.4000 3.0974

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 526.3141 118.0369 512.9072 1177.5692 0.4469 0.1363 2.2705

 

NASA/TM—2013-218094 J–88
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1366 7.9806 585.2425 520.0951 432.2457 0.0223 0.3202

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 521.9870 0.0000 521.9870 1177.8965 0.4432 0.2304 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9777 585.6007 520.0569 0.0000 0.0600 0.0399 0.1342

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8778 9.1124 1.1576 607.4185 27.1592 250.2344 1.9398

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 169577.000 0.438 542.707 523891.813 0.110898E-02

 

Melt Ratio at Stator LE, Throat, TE

0.24184E+00 0.27520E+00 0.36396E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.465 EfDer = 1.000 SH = 0.120273E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.633 3776.794 9.112 607.414 1.000 1.000 0.980

 W Kg/sec = 25.742 Wdry = 56.564 WH2O = 0.068 lbm/sec H2O = 0.734g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 98.863 3490.097 1.379 0.250 53.387 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89368.500 44415.742 1.760 509.668 289.645 384.739 1.328

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 420.83 -0.14 420.83 0.35 0.62 557.95

 MEAN 15.91 0.00 -0.02 420.83 -0.14 420.83 0.35 0.57

 HUB 13.07 0.00 -0.02 420.83 -0.14 420.83 0.35 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.13 47.36 7.77 603.80 736.11 8.36 593.24 519.92 0.66

 MEAN 51.26 44.80 6.46 524.47 672.55 8.36 593.24 519.92 0.66

 HUB 45.68 38.84 6.84 430.77 602.32 8.36 593.24 519.92 0.66

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 512.90 286.71 425.28 1205.57 0.43 2.05 1.78 7.43

 MEAN 15.50 517.78 284.90 432.35 1201.39 0.43 2.13 1.86 5.75

 HUB 12.59 552.20 333.89 439.82 1197.38 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 591.28 523.09 304.57 0.43 5146.18 0.92 0.91 

 MEAN 510.78 487.80 225.88 0.41 4417.64 0.92 0.91 0.91 1.51

 HUB 414.95 447.23 81.06 0.37 4205.58 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.54 1.16 9.32 634.56 1.04 613.50 529.10 0.45

 MEAN 10.33 1.13 9.11 630.71 1.04 609.26 527.89 0.49

 HUB 10.27 1.13 8.89 629.59 1.04 605.19 527.63 0.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.99 35.61 31.50 4.11 0.93 0.43 1.40

 MEAN 33.38 27.58 23.50 4.08 0.93 0.40 1.64

 HUB 37.20 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 576.9907 290.1284 498.7422 1197.1108 0.4820 -0.2011 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3550 8.8526 604.9812 528.3130 0.5338 30.1874 33.0000 2.8126

 

NASA/TM—2013-218094 J–89
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 504.3582 115.1706 491.0326 1203.3077 0.4191 0.0465 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3288 9.1680 611.2603 528.0437 410.5396 0.0406 0.3354

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 488.4156 0.0000 488.4156 1204.5092 0.4055 0.2573 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2392 612.5151 528.0272 0.0000 0.0600 0.0393 0.1025

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8810 10.3304 1.1337 631.5974 24.2070 256.6758 1.9897

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 151301.250 0.433 484.218 531565.875 0.126321E-02

 

Melt Ratio at Stator LE, Throat, TE

0.62560E+00 0.66437E+00 0.77399E+00

 trTOT = 1.3216 Tt4 = 631.5974 T1 = 477.9152

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 958508.56 3067.5718 187.3809 2.4224 0.8578 4.4429 1.3216 37.3740

NASA/TM—2013-218094 J–90
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.778 EfDer = 0.996 SH = 0.277628E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.686 3745.057 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 25.312 Wdry = 55.671 WH2O = 0.015 lbm/sec H2O = 0.099g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 184.250 3901.564 1.381 0.248 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 151092.641 43689.543 1.542 831.557 539.393 619.754 1.149

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 436.08 -0.15 436.08 0.42 0.77 702.38

 MEAN 17.06 0.00 -0.02 436.08 -0.15 436.08 0.42 0.68

 HUB 12.51 0.00 -0.02 436.08 -0.15 436.08 0.42 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.11 50.47 6.64 674.23 803.08 3.79 462.63 461.72 6.71

 MEAN 51.98 47.20 4.78 557.56 707.95 3.79 462.63 461.72 6.71

 HUB 43.16 38.62 4.54 408.85 597.87 3.79 462.63 461.72 6.71

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 673.07 366.57 564.49 1068.23 0.63 7.29 6.52 16.04

 MEAN 18.04 711.10 411.74 579.77 1062.72 0.67 7.43 6.80 12.53

 HUB 15.00 824.33 551.15 612.98 1052.00 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 674.23 642.88 307.65 0.60 7565.51 0.92 0.91

 MEAN 589.45 606.39 177.71 0.57 7428.73 0.92 0.91 0.91 1.29

 HUB 490.23 616.00 60.92 0.59 8269.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.27 517.67 1.08 481.25 484.36 4.22

 MEAN 5.53 1.30 4.11 516.95 1.08 476.30 484.39 5.03

 HUB 5.69 1.33 3.81 521.36 1.09 466.74 487.92 7.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.00 28.59 24.20 4.39 0.93 0.33 1.80

 MEAN 35.38 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 41.96 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 756.0515 410.9411 634.6190 1058.7043 0.7141 -0.0822 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5778 3.9857 472.7205 485.7346 5.8966 32.9247 35.4000 2.4753

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 600.3259 146.8580 582.0858 1077.5331 0.5571 0.2888 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5478 4.5049 489.6975 484.3321 554.9116 0.0296 0.4051

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 596.6708 0.0000 596.6708 1077.8917 0.5536 0.3209 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4966 490.0531 484.4307 0.0000 0.0600 0.0457 0.2834

NASA/TM—2013-218094 J–91
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8674 5.5232 1.2951 518.6562 40.7432 224.7102 1.7419

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 253520.906 0.558 797.802 605759.625 0.419242E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.734 EfDer = 0.999 SH = 0.598719E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.686 3745.057 5.523 518.656 1.000 1.000 0.980

 W Kg/sec = 25.312 Wdry = 55.653 WH2O = 0.033 lbm/sec H2O = 0.246g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 148.204 3745.215 1.381 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 130775.148 43684.035 1.361 590.487 433.960 468.502 1.080

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 531.52 -0.18 531.52 0.49 0.79 671.62

 MEAN 18.08 0.00 -0.02 531.52 -0.18 531.52 0.49 0.73

 HUB 15.21 0.00 -0.02 531.52 -0.18 531.52 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.65 46.36 5.29 671.61 856.63 4.70 495.97 484.77 4.30

 MEAN 48.03 42.30 5.73 590.83 794.86 4.70 495.97 484.77 4.30

 HUB 43.09 37.84 5.25 497.09 727.87 4.70 495.97 484.77 4.30

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 602.13 294.14 525.39 1111.45 0.54 2.33 2.04 9.02

 MEAN 18.01 618.67 310.93 534.86 1107.43 0.56 2.40 2.13 7.35

 HUB 15.22 674.33 397.09 545.02 1103.74 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.36 644.46 373.22 0.58 6010.12 0.92 0.91

 MEAN 588.60 602.64 277.67 0.54 5603.14 0.92 0.91 0.91 1.43

 HUB 497.51 554.19 100.42 0.50 6047.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.22 5.52 550.19 1.06 521.09 498.85 2.08

 MEAN 6.63 1.20 5.38 548.06 1.06 517.33 498.09 2.32

 HUB 6.73 1.22 5.25 550.39 1.06 513.88 499.42 2.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.24 35.39 31.50 3.89 0.93 0.37 1.40

 MEAN 30.17 27.44 23.50 3.94 0.92 0.36 1.63

 HUB 36.08 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 693.6453 311.8022 619.6153 1100.5236 0.6303 -0.1920 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6810 5.1291 510.9293 499.2539 2.8390 26.7124 30.6000 3.8876

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 584.1136 123.8362 570.8356 1112.5602 0.5250 0.1133 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6572 5.5303 522.1622 498.4473 491.5697 0.0282 0.2784

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 612.3513 0.0000 612.3513 1109.6455 0.5518 0.1803 0.5911

NASA/TM—2013-218094 J–92
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4089 519.4540 498.6560 0.0000 0.0600 0.0450 0.0208

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8706 6.6351 1.2013 549.5466 30.8923 257.0409 1.9926

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 192467.250 0.432 605.673 544973.500 0.683160E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.999 EfDer = 0.999 SH = 0.810314E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.686 3745.057 6.635 549.546 1.000 1.000 0.980

 W Kg/sec = 25.312 Wdry = 55.641 WH2O = 0.045 lbm/sec H2O = 0.385g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 126.987 3638.433 1.380 0.249 53.375 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112973.289 43680.402 1.467 545.479 371.902 424.468 1.141

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 497.05 -0.17 497.05 0.44 0.73 637.23

 MEAN 17.74 0.00 -0.02 497.05 -0.17 497.05 0.44 0.68

 HUB 15.05 0.00 -0.02 497.05 -0.17 497.05 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.85 46.36 6.49 655.92 823.12 5.81 529.73 498.40 2.08

 MEAN 49.40 43.40 6.00 579.73 763.77 5.81 529.73 498.40 2.08

 HUB 44.71 38.84 5.87 491.86 699.40 5.81 529.73 498.40 2.08

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 576.61 294.49 495.74 1145.37 0.50 2.26 1.98 8.75

 MEAN 17.51 591.27 309.86 503.57 1141.72 0.52 2.34 2.07 6.78

 HUB 14.85 643.66 390.04 512.03 1138.32 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.43 608.54 352.94 0.53 5837.28 0.92 0.91

 MEAN 572.15 567.79 262.29 0.50 5427.54 0.92 0.91 0.91 1.46

 HUB 485.32 520.82 95.28 0.46 5794.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.95 1.20 6.70 580.15 1.06 553.48 510.59 1.18

 MEAN 7.85 1.18 6.55 578.00 1.05 549.96 509.88 1.29

 HUB 7.94 1.20 6.41 579.92 1.06 546.69 510.86 1.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.71 35.45 31.50 3.95 0.93 0.39 1.40

 MEAN 31.60 27.51 23.50 4.01 0.92 0.38 1.62

 HUB 37.30 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 656.4210 311.8889 577.5931 1136.3044 0.5777 -0.1735 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8965 6.3164 544.8093 510.7370 1.4863 28.3682 31.5000 3.1318

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 557.0777 121.5227 543.6614 1146.3429 0.4860 0.1206 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8764 6.7158 554.4743 510.1889 451.3937 0.0247 0.3043

 

NASA/TM—2013-218094 J–93
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 568.8293 0.0000 568.8293 1145.2152 0.4967 0.2123 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6518 553.4150 510.2595 0.0000 0.0600 0.0400 0.0735

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8774 7.8558 1.1840 579.3530 29.8113 245.1777 1.9006

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 185931.969 0.444 585.107 520347.375 0.920909E-03

 

Melt Ratio at Stator LE, Throat, TE

0.20602E-01 0.32699E-01 0.72929E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.405 EfDer = 1.000 SH = 0.105086E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.686 3745.057 7.856 579.351 1.000 1.000 0.980

 W Kg/sec = 25.312 Wdry = 55.628 WH2O = 0.059 lbm/sec H2O = 0.570g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.126 3543.602 1.380 0.249 53.382 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 98851.281 43676.273 1.591 513.330 322.588 395.845 1.227

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 462.16 -0.16 462.16 0.40 0.68 595.57

 MEAN 16.97 0.00 -0.02 462.16 -0.16 462.16 0.40 0.63

 HUB 14.32 0.00 -0.02 462.16 -0.16 462.16 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.72 46.36 7.36 629.45 781.02 7.04 562.24 510.10 1.16

 MEAN 50.20 43.80 6.40 554.63 722.07 7.04 562.24 510.10 1.16

 HUB 45.37 37.84 7.53 468.00 657.85 7.04 562.24 510.10 1.16

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 545.12 287.01 463.45 1176.31 0.46 2.16 1.89 8.34

 MEAN 16.57 556.26 296.81 470.45 1172.68 0.47 2.24 1.97 6.35

 HUB 13.89 601.73 365.55 477.97 1169.25 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 617.03 568.94 330.02 0.48 5421.87 0.92 0.91

 MEAN 541.66 530.36 244.85 0.45 4922.00 0.92 0.91 0.91 1.48

 HUB 453.95 486.07 88.40 0.42 5079.82 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.21 1.17 7.97 607.74 1.05 583.93 520.42 0.74

 MEAN 9.08 1.16 7.80 605.12 1.04 580.33 519.58 0.80

 HUB 9.12 1.16 7.63 605.95 1.05 576.94 520.04 0.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.77 35.45 31.50 3.95 0.93 0.40 1.40

 MEAN 32.25 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.41 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 600.8248 298.4795 521.4407 1169.6094 0.5137 -0.1196 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1253 7.6404 577.3578 520.1320 0.8532 29.7874 32.4000 2.6126

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 516.1766 115.7633 503.0280 1177.2487 0.4385 0.1471 2.2705

 

NASA/TM—2013-218094 J–94
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1100 7.9972 584.9274 519.7866 432.2457 0.0214 0.3271

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 511.9218 0.0000 511.9218 1177.5626 0.4347 0.2384 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9943 585.2723 519.7507 0.0000 0.0600 0.0389 0.1450

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8795 9.0865 1.1567 606.2554 26.9187 247.3722 1.9176

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 168086.203 0.441 528.949 514189.000 0.113342E-02

 

Melt Ratio at Stator LE, Throat, TE

0.24754E+00 0.28136E+00 0.37128E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.732 EfDer = 1.000 SH = 0.122810E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.686 3745.057 9.087 606.251 1.000 1.000 0.980

 W Kg/sec = 25.312 Wdry = 55.618 WH2O = 0.068 lbm/sec H2O = 0.750g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.395 3464.087 1.379 0.250 53.388 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 87772.859 43673.223 1.786 509.668 285.348 384.739 1.348 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 413.31 -0.14 413.31 0.35 0.61 553.79

 MEAN 15.91 0.00 -0.02 413.31 -0.14 413.31 0.35 0.56

 HUB 13.07 0.00 -0.02 413.31 -0.14 413.31 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.39 47.36 8.03 598.73 727.65 8.36 592.58 519.62 0.69

 MEAN 51.53 44.80 6.73 520.07 664.41 8.36 592.58 519.62 0.69

 HUB 45.95 38.84 7.11 427.15 594.48 8.36 592.58 519.62 0.69

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 507.09 287.06 418.01 1204.70 0.42 2.05 1.78 7.43

 MEAN 15.50 511.43 284.59 424.93 1200.54 0.43 2.13 1.86 5.75

 HUB 12.59 544.95 331.88 432.23 1196.54 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 586.31 514.09 299.26 0.43 5152.39 0.92 0.91

 MEAN 506.49 479.38 221.90 0.40 4412.72 0.92 0.91 0.91 1.52

 HUB 411.46 439.50 79.58 0.37 4180.22 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.50 1.16 9.31 633.20 1.04 612.62 528.78 0.47

 MEAN 10.29 1.13 9.10 629.33 1.04 608.39 527.55 0.51

 HUB 10.23 1.13 8.89 628.11 1.04 604.34 527.26 0.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.48 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.81 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.52 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 569.1010 289.8081 489.7828 1196.4318 0.4757 -0.1983 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3153 8.8540 604.2960 527.9634 0.5545 30.6131 33.0000 2.3869

 

NASA/TM—2013-218094 J–95
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 495.1512 113.0682 482.0688 1202.6434 0.4117 0.0582 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2914 9.1725 610.5876 527.6946 410.5396 0.0393 0.3414

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 479.6475 0.0000 479.6475 1203.7889 0.3984 0.2642 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2401 611.7849 527.6777 0.0000 0.0600 0.0386 0.1127

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8822 10.2923 1.1327 630.1869 23.9599 254.1729 1.9703

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 149766.250 0.436 471.298 522331.156 0.128931E-02

 

Melt Ratio at Stator LE, Throat, TE

0.63385E+00 0.67294E+00 0.78322E+00

 trTOT = 1.3186 Tt4 = 630.1869 T1 = 477.9151

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 949772.56 2988.8291 184.2502 2.4134 0.8616 4.7778 1.3186 37.3740

NASA/TM—2013-218094 J–96
 25μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.828 EfDer = 0.984 SH = 0.565046E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.099 3888.739 4.265 457.736 1.000 1.000 0.980

 W Kg/sec = 28.681 Wdry = 63.095 WH2O = 0.004 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.316 4139.589 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 168200.719 49509.492 1.390 831.557 598.054 619.754 1.036

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 485.45 -0.17 485.45 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 485.45 -0.17 485.45 0.48 0.74

 HUB 12.51 0.00 -0.02 485.45 -0.17 485.45 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.27 50.47 4.80 700.09 852.07 3.66 438.78 448.47 4.25

 MEAN 50.03 47.20 2.83 578.95 755.67 3.66 438.78 448.47 4.25

 HUB 41.18 38.62 2.56 424.53 645.01 3.66 438.78 448.47 4.25

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 728.08 352.72 636.94 1038.54 0.70 7.29 6.52 16.04

 MEAN 18.04 773.21 411.18 654.82 1033.17 0.75 7.43 6.80 12.53

 HUB 15.00 914.31 580.05 706.75 1019.14 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.09 725.50 347.37 0.70 7280.03 0.92 0.90

 MEAN 612.06 684.94 200.88 0.66 7418.92 0.92 0.90 0.90 1.21

 HUB 509.03 710.31 71.02 0.70 8702.89 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 497.48 1.09 454.84 474.07 2.25

 MEAN 5.63 1.32 3.90 498.24 1.09 450.15 474.66 2.73

 HUB 5.89 1.38 3.51 505.25 1.10 438.01 479.32 4.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.98 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.13 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.38 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 836.4642 410.3824 728.8749 1026.1431 0.8152 -0.1085 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6893 3.6930 444.0413 476.0930 3.5478 29.3811 35.4000 6.0190

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 681.8669 166.8055 661.1493 1047.7263 0.6508 0.2264 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6277 4.2476 462.9241 475.3464 554.9116 0.0426 0.3574

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 684.2635 0.0000 684.2635 1047.4098 0.6533 0.2509 1.3089

NASA/TM—2013-218094 J–97
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.1938 462.6645 475.2309 0.0000 0.0600 0.0743 0.1979

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8212 5.5678 1.3056 500.3218 42.5867 238.3169 1.8474

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 264745.156 0.540 944.023 727553.000 0.632136E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.421 EfDer = 0.989 SH = 0.704128E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.099 3888.739 5.568 500.321 1.000 1.000 0.980

 W Kg/sec = 28.681 Wdry = 63.095 WH2O = 0.004 lbm/sec H2O = 0.029g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.614 3959.516 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 147242.313 49509.223 1.233 590.487 478.927 468.502 0.978

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 598.46 -0.21 598.46 0.57 0.87 710.05

 MEAN 18.08 0.00 -0.02 598.46 -0.21 598.46 0.57 0.81

 HUB 15.21 0.00 -0.02 598.46 -0.21 598.46 0.57 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.37 46.36 3.01 697.38 919.12 4.49 471.52 475.12 1.35

 MEAN 45.72 42.30 3.42 613.50 857.19 4.49 471.52 475.12 1.35

 HUB 40.79 37.84 2.95 516.16 790.43 4.49 471.52 475.12 1.35

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 648.35 273.86 587.67 1085.64 0.60 2.33 2.04 9.02

 MEAN 18.01 668.16 299.61 597.22 1082.17 0.62 2.40 2.13 7.35

 HUB 15.22 729.42 403.27 607.81 1079.06 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 692.97 721.80 419.10 0.66 5596.52 0.92 0.90

 MEAN 611.18 673.61 311.57 0.62 5399.68 0.92 0.90 0.90 1.37

 HUB 516.60 618.28 113.34 0.57 6142.06 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.21 5.33 530.87 1.06 497.06 490.55 0.56

 MEAN 6.72 1.21 5.21 529.79 1.06 493.89 490.08 0.62

 HUB 6.89 1.24 5.09 533.85 1.07 491.06 492.05 0.68

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 24.99 35.50 31.50 4.00 0.93 0.32 1.40

 MEAN 26.64 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.56 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 767.0062 300.4507 705.7109 1071.4673 0.7158 -0.2388 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7760 4.8342 484.1976 491.0187 0.8587 23.0615 30.6000 7.5385

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 663.6368 140.6957 648.5511 1084.5537 0.6119 0.0172 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7247 5.2383 496.0869 490.7155 491.5697 0.0425 0.2183

 

NASA/TM—2013-218094 J–98
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 707.2953 0.0000 707.2953 1079.2643 0.6553 0.0939 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0166 491.2769 490.6606 0.0000 0.0600 0.0761 -0.1231

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8214 6.6715 1.1982 531.5018 31.1816 281.6234 2.1831

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193915.484 0.404 691.460 658714.000 0.733452E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.781 EfDer = 0.991 SH = 0.781138E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.099 3888.739 6.672 531.501 1.000 1.000 0.980

 W Kg/sec = 28.681 Wdry = 63.094 WH2O = 0.005 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.737 3841.621 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126819.922 49509.074 1.324 545.479 411.979 424.468 1.030

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 557.98 -0.19 557.98 0.51 0.80 672.82

 MEAN 17.74 0.00 -0.02 557.98 -0.19 557.98 0.51 0.75

 HUB 15.05 0.00 -0.02 557.98 -0.19 557.98 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.68 46.36 4.32 681.09 880.62 5.60 506.47 490.51 0.45

 MEAN 47.18 43.40 3.78 601.97 820.94 5.60 506.47 490.51 0.45

 HUB 42.48 38.84 3.64 510.73 756.56 5.60 506.47 490.51 0.45

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 618.86 276.78 553.52 1121.66 0.55 2.26 1.98 8.75

 MEAN 17.51 636.80 300.32 561.54 1118.44 0.57 2.34 2.07 6.78

 HUB 14.85 694.79 396.66 570.43 1115.51 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.27 680.28 395.48 0.61 5486.94 0.92 0.91

 MEAN 594.10 633.74 293.78 0.57 5260.97 0.92 0.91 0.91 1.39

 HUB 503.94 580.43 107.28 0.52 5893.32 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.99 1.20 6.51 561.44 1.06 530.65 503.61 0.22

 MEAN 7.93 1.19 6.38 560.21 1.05 527.61 503.11 0.24

 HUB 8.10 1.21 6.25 563.66 1.06 524.85 504.58 0.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.57 35.55 31.50 4.05 0.93 0.34 1.40

 MEAN 28.14 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.81 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 718.9197 302.2900 652.2778 1110.5454 0.6474 -0.2067 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9908 6.0488 520.2238 503.7971 0.2993 24.8648 31.5000 6.6352

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 629.3885 137.2968 614.2308 1120.8640 0.5615 0.0311 2.3726

 

NASA/TM—2013-218094 J–99
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9493 6.4342 529.9252 503.6181 451.3937 0.0356 0.2515

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 646.8536 0.0000 646.8536 1118.9465 0.5781 0.1408 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3223 528.1362 503.5388 0.0000 0.0600 0.0613 -0.0378

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8432 7.9074 1.1852 561.7680 30.2684 267.1887 2.0712

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188299.844 0.417 671.436 622501.125 0.824291E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.357 EfDer = 0.994 SH = 0.905579E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.099 3888.739 7.907 561.767 1.000 1.000 0.980

 W Kg/sec = 28.681 Wdry = 63.093 WH2O = 0.006 lbm/sec H2O = 0.050g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.075 3736.701 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110335.977 49508.832 1.436 513.330 357.368 395.845 1.108

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 515.86 -0.18 515.86 0.46 0.74 628.03

 MEAN 16.97 0.00 -0.02 515.86 -0.18 515.86 0.46 0.68

 HUB 14.32 0.00 -0.02 515.86 -0.18 515.86 0.46 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.73 46.36 5.37 653.60 832.79 6.87 540.38 503.48 0.19

 MEAN 48.16 43.80 4.36 575.91 773.30 6.87 540.38 503.48 0.19

 HUB 43.30 37.84 5.46 485.96 708.83 6.87 540.38 503.48 0.19

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 582.63 273.01 514.71 1154.87 0.50 2.16 1.89 8.34

 MEAN 16.57 597.13 289.60 522.20 1151.46 0.52 2.24 1.97 6.35

 HUB 13.89 648.03 372.37 530.36 1148.31 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.70 632.55 367.69 0.55 5157.92 0.92 0.91

 MEAN 562.45 589.18 272.84 0.51 4802.88 0.92 0.91 0.91 1.42

 HUB 471.37 539.52 98.99 0.47 5174.82 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.29 1.18 7.83 589.90 1.05 562.62 514.52 0.11

 MEAN 9.19 1.16 7.67 587.96 1.05 559.31 513.80 0.12

 HUB 9.30 1.18 7.51 589.99 1.05 556.24 514.59 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.94 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.01 27.59 23.50 4.09 0.92 0.35 1.62

 HUB 35.07 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 651.0905 291.2332 582.3246 1147.2043 0.5675 -0.1378 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2454 7.4505 555.2249 514.2906 0.1367 26.5706 32.4000 5.8294

 

NASA/TM—2013-218094 J–100
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 577.4880 129.5137 562.7775 1154.6886 0.5001 0.0721 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2148 7.7842 562.4894 514.1835 432.2457 0.0292 0.2813

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 572.9138 0.0000 572.9138 1155.0992 0.4960 0.1836 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7801 562.9142 514.1195 0.0000 0.0600 0.0480 0.0695

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8609 9.1849 1.1615 589.2838 27.5183 267.5846 2.0743

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171269.047 0.417 610.708 609528.563 0.981847E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 4.956 EfDer = 0.997 SH = 0.113692E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.099 3888.739 9.185 589.283 1.000 1.000 0.980

 W Kg/sec = 28.681 Wdry = 63.092 WH2O = 0.007 lbm/sec H2O = 0.071g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.640 3648.418 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 97092.469 49508.383 1.617 509.668 315.134 384.739 1.221

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 457.20 -0.16 457.20 0.39 0.66 583.26

 MEAN 15.91 0.00 -0.02 457.20 -0.16 457.20 0.39 0.61

 HUB 13.07 0.00 -0.02 457.20 -0.16 457.20 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.68 47.36 6.32 621.70 771.84 8.27 572.49 514.10 0.11

 MEAN 49.76 44.80 4.96 540.02 707.69 8.27 572.49 514.10 0.11

 HUB 44.14 38.84 5.30 443.54 637.10 8.27 572.49 514.10 0.11

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 537.77 278.56 460.00 1185.84 0.45 2.05 1.78 7.43

 MEAN 15.50 545.66 280.81 467.86 1181.62 0.46 2.13 1.86 5.75

 HUB 12.59 584.49 338.97 476.17 1177.62 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.81 566.27 330.25 0.48 5000.16 0.92 0.91

 MEAN 525.92 528.17 245.11 0.45 4354.42 0.92 0.91 0.91 1.47

 HUB 427.25 484.28 88.28 0.41 4269.67 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.67 1.16 9.28 616.54 1.05 593.31 523.96 0.07

 MEAN 10.47 1.14 9.06 613.02 1.04 589.11 522.74 0.08

 HUB 10.44 1.14 8.84 612.56 1.04 585.12 522.59 0.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.20 35.68 31.50 4.18 0.93 0.39 1.40

 MEAN 30.97 27.65 23.50 4.15 0.92 0.37 1.64

 HUB 35.45 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 613.4089 285.9609 542.6757 1176.2651 0.5215 -0.2186 2.0437

 

NASA/TM—2013-218094 J–101
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4978 8.7420 583.8243 523.0637 0.0895 27.7868 33.0000 5.2132

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 550.2158 125.6423 535.6785 1182.2035 0.4654 -0.0241 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4522 9.0275 589.7280 522.9400 410.5396 0.0512 0.3020

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 531.6212 0.0000 531.6212 1183.7972 0.4491 0.2178 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1244 591.3445 522.9550 0.0000 0.0600 0.0458 0.0421

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8686 10.4601 1.1388 614.0372 24.7566 271.6182 2.1056

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154167.953 0.416 549.729 613623.750 0.125394E-03

 

Melt Ratio at Stator LE, Throat, TE

0.24461E-01 0.31499E-01 0.51742E-01

 trTOT = 1.3415 Tt4 = 614.0372 T1 = 457.7363

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 972397.50 3467.3569 204.3162 2.4527 0.8226 2.8280 1.3415 37.3740

NASA/TM—2013-218094 J–102
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.059 EfDer = 0.993 SH = 0.578964E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.945 3728.503 4.265 457.736 1.000 1.000 0.980

 W Kg/sec = 26.793 Wdry = 58.942 WH2O = 0.003 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 190.865 3969.018 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154352.500 46250.105 1.488 831.557 558.684 619.754 1.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.48 -0.15 445.48 0.44 0.79 714.52

 MEAN 17.06 0.00 -0.02 445.48 -0.15 445.48 0.44 0.70

 HUB 12.51 0.00 -0.02 445.48 -0.15 445.48 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.44 50.47 5.97 671.25 805.75 3.75 441.77 448.42 3.83

 MEAN 51.26 47.20 4.06 555.09 711.87 3.75 441.77 448.42 3.83

 HUB 42.43 38.62 3.81 407.04 603.54 3.75 441.77 448.42 3.83

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 679.57 355.49 579.17 1043.27 0.65 7.29 6.52 16.04

 MEAN 18.04 719.33 404.42 594.88 1037.93 0.69 7.43 6.80 12.53

 HUB 15.00 838.52 551.01 632.06 1026.61 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 671.25 659.65 315.75 0.63 7337.02 0.92 0.91

 MEAN 586.84 622.23 182.43 0.60 7296.69 0.92 0.91 0.91 1.26

 HUB 488.06 635.19 62.95 0.62 8267.03 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.20 496.14 1.08 458.99 473.24 1.99

 MEAN 5.56 1.30 4.05 495.93 1.08 454.31 473.24 2.39

 HUB 5.75 1.35 3.72 501.01 1.09 444.45 476.57 3.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.54 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.21 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.08 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 768.4450 403.6316 653.9031 1033.2190 0.7437 -0.0896 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6062 3.8987 450.1941 474.3752 2.8573 31.6856 35.4000 3.7144

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 616.9355 150.9213 598.1908 1052.4083 0.5862 0.2668 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5688 4.4250 467.0784 473.8753 554.9116 0.0329 0.3884

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 614.3217 0.0000 614.3217 1052.6812 0.5836 0.2982 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4078 467.3397 473.8119 0.0000 0.0600 0.0529 0.2564

NASA/TM—2013-218094 J–103
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8558 5.5361 1.2981 497.6910 39.9567 229.5995 1.7798

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 248407.484 0.551 827.454 667652.500 0.660535E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.916 EfDer = 0.997 SH = 0.750776E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.945 3728.503 5.536 497.691 1.000 1.000 0.980

 W Kg/sec = 26.793 Wdry = 58.941 WH2O = 0.004 lbm/sec H2O = 0.032g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 153.315 3806.385 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 133984.172 46249.797 1.316 590.487 448.781 468.502 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 544.57 -0.19 544.57 0.51 0.81 682.59

 MEAN 18.08 0.00 -0.02 544.57 -0.19 544.57 0.51 0.76

 HUB 15.21 0.00 -0.02 544.57 -0.19 544.57 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.85 46.36 4.49 668.64 862.49 4.63 473.84 473.76 1.34

 MEAN 47.22 42.30 4.92 588.22 801.73 4.63 473.84 473.76 1.34

 HUB 42.27 37.84 4.43 494.89 735.98 4.63 473.84 473.76 1.34

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 607.03 282.12 537.49 1086.90 0.56 2.33 2.04 9.02

 MEAN 18.01 624.53 301.68 546.84 1083.13 0.58 2.40 2.13 7.35

 HUB 15.22 681.24 392.31 556.93 1079.69 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 664.41 659.58 382.29 0.61 5764.77 0.92 0.91

 MEAN 586.00 616.33 284.32 0.57 5436.57 0.92 0.91 0.91 1.40

 HUB 495.32 566.38 103.00 0.52 5975.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.46 527.86 1.06 498.23 489.32 0.59

 MEAN 6.65 1.20 5.33 526.14 1.06 494.77 488.52 0.65

 HUB 6.77 1.22 5.20 528.96 1.06 491.64 489.94 0.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.69 35.42 31.50 3.92 0.93 0.35 1.40

 MEAN 28.88 27.47 23.50 3.97 0.92 0.35 1.63

 HUB 35.16 10.48 6.50 3.98 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 705.0492 302.5230 636.8471 1075.3116 0.6557 -0.2057 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7048 5.0403 487.6821 489.3368 0.8298 25.4092 30.6000 5.1908

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 600.1201 127.2297 586.4783 1087.3896 0.5519 0.0812 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6741 5.4398 498.6927 489.1161 491.5697 0.0321 0.2582

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 631.5406 0.0000 631.5406 1083.9751 0.5826 0.1527 0.5911

NASA/TM—2013-218094 J–104
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2945 495.5831 489.0909 0.0000 0.0600 0.0532 -0.0233

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8584 6.6447 1.2003 527.6512 29.9619 265.3938 2.0573

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186336.563 0.422 620.694 601507.250 0.787426E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.212 EfDer = 0.998 SH = 0.845991E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.945 3728.503 6.645 527.651 1.000 1.000 0.980

 W Kg/sec = 26.793 Wdry = 58.940 WH2O = 0.005 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 131.524 3696.742 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115635.320 46249.621 1.417 545.479 385.010 424.468 1.102 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 508.77 -0.18 508.77 0.46 0.76 647.44

 MEAN 17.74 0.00 -0.02 508.77 -0.18 508.77 0.46 0.70

 HUB 15.05 0.00 -0.02 508.77 -0.18 508.77 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.09 46.36 5.73 653.02 827.96 5.74 506.84 488.99 0.49

 MEAN 48.61 43.40 5.21 577.16 769.53 5.74 506.84 488.99 0.49

 HUB 43.92 38.84 5.08 489.69 706.27 5.74 506.84 488.99 0.49

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 580.62 283.35 506.78 1120.89 0.52 2.26 1.98 8.75

 MEAN 17.51 596.24 301.23 514.55 1117.44 0.53 2.34 2.07 6.78

 HUB 14.85 649.74 385.55 522.98 1114.26 0.58 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 644.56 622.34 361.21 0.56 5616.70 0.92 0.91

 MEAN 569.62 580.34 268.39 0.52 5276.56 0.92 0.91 0.91 1.43

 HUB 483.18 532.01 97.63 0.48 5728.11 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.95 1.20 6.64 557.04 1.06 529.93 502.16 0.25

 MEAN 7.87 1.18 6.50 555.26 1.05 526.68 501.42 0.28

 HUB 7.98 1.20 6.36 557.62 1.06 523.68 502.46 0.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.21 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.35 27.55 23.50 4.05 0.92 0.37 1.62

 HUB 36.40 10.57 6.50 4.07 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 665.3503 303.2036 592.2487 1111.4268 0.5986 -0.1838 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9193 6.2333 521.0519 502.0349 0.3261 27.1103 31.5000 4.3897

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 571.3957 124.6461 557.6346 1121.3492 0.5096 0.0901 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8939 6.6265 530.3908 501.8993 451.3937 0.0277 0.2859

 

NASA/TM—2013-218094 J–105
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 584.1874 0.0000 584.1874 1120.0712 0.5216 0.1895 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5528 529.2047 501.8584 0.0000 0.0600 0.0444 0.0388

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8702 7.8699 1.1844 556.6345 28.9854 252.6940 1.9589

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180322.734 0.434 600.661 572530.938 0.899993E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.675 EfDer = 0.999 SH = 0.998359E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.945 3728.503 7.870 556.634 1.000 1.000 0.980

 W Kg/sec = 26.793 Wdry = 58.939 WH2O = 0.006 lbm/sec H2O = 0.056g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.058 3599.214 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 100989.578 46249.348 1.537 513.330 333.901 395.845 1.186

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 472.16 -0.16 472.16 0.42 0.69 604.92

 MEAN 16.97 0.00 -0.02 472.16 -0.16 472.16 0.42 0.64

 HUB 14.32 0.00 -0.02 472.16 -0.16 472.16 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.01 46.36 6.65 626.67 784.76 6.99 538.72 501.82 0.23

 MEAN 49.48 43.80 5.68 552.18 726.65 6.99 538.72 501.82 0.23

 HUB 44.63 37.84 6.79 465.93 663.46 6.99 538.72 501.82 0.23

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 548.16 277.22 472.89 1152.04 0.48 2.16 1.89 8.34

 MEAN 16.57 560.31 289.17 479.93 1148.55 0.49 2.24 1.97 6.35

 HUB 13.89 606.91 361.52 487.49 1145.27 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 614.30 580.73 337.08 0.50 5237.09 0.92 0.91

 MEAN 539.27 541.18 250.10 0.47 4795.43 0.92 0.91 0.91 1.46

 HUB 451.94 495.81 90.43 0.43 5023.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.23 1.17 7.92 584.02 1.05 559.87 512.84 0.14

 MEAN 9.11 1.16 7.76 581.71 1.05 556.48 511.96 0.15

 HUB 9.17 1.17 7.59 582.91 1.05 553.30 512.44 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.38 35.48 31.50 3.98 0.93 0.38 1.40

 MEAN 31.07 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 36.56 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 607.0475 290.7963 532.8642 1145.1871 0.5301 -0.1255 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1561 7.5793 553.2710 512.4063 0.1636 28.6223 32.4000 3.7777

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 527.8383 118.3787 514.3926 1152.6376 0.4579 0.1209 2.2705

 

NASA/TM—2013-218094 J–106
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1370 7.9276 560.4932 512.3229 432.2457 0.0236 0.3103

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 523.5485 0.0000 523.5485 1152.9868 0.4541 0.2187 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9242 560.8571 512.2714 0.0000 0.0600 0.0415 0.1185

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8746 9.1116 1.1578 582.8776 26.2455 254.3253 1.9715

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 163348.453 0.433 544.119 564186.625 0.109066E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.077 EfDer = 0.999 SH = 0.126976E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.945 3728.503 9.112 582.877 1.000 1.000 0.980

 W Kg/sec = 26.793 Wdry = 58.938 WH2O = 0.007 lbm/sec H2O = 0.081g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 100.809 3517.256 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89455.836 46248.852 1.727 509.668 295.137 384.739 1.304

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 421.24 -0.15 421.24 0.36 0.63 562.29

 MEAN 15.91 0.00 -0.02 421.24 -0.15 421.24 0.36 0.58

 HUB 13.07 0.00 -0.02 421.24 -0.15 421.24 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.76 47.36 7.40 596.08 730.02 8.33 568.62 512.26 0.14

 MEAN 50.88 44.80 6.08 517.77 667.59 8.33 568.62 512.26 0.14

 HUB 45.28 38.84 6.44 425.26 598.68 8.33 568.62 512.26 0.14

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 508.71 278.84 425.48 1180.78 0.43 2.05 1.78 7.43

 MEAN 15.50 514.25 278.13 432.55 1176.68 0.44 2.13 1.86 5.75

 HUB 12.59 549.07 328.43 440.01 1172.75 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 583.72 523.43 304.87 0.44 5005.13 0.92 0.91

 MEAN 504.25 488.09 226.12 0.41 4312.68 0.92 0.91 0.91 1.50

 HUB 409.65 447.44 81.21 0.38 4136.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.54 1.16 9.30 609.04 1.04 588.25 521.97 0.09

 MEAN 10.34 1.13 9.08 605.42 1.04 584.18 520.68 0.10

 HUB 10.28 1.13 8.87 604.50 1.04 580.28 520.37 0.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.24 35.62 31.50 4.12 0.93 0.42 1.40

 MEAN 32.74 27.60 23.50 4.10 0.93 0.39 1.64

 HUB 36.74 10.46 6.50 3.96 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 574.2188 283.2315 499.5068 1172.2566 0.4898 -0.2052 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3610 8.8118 579.8396 520.9811 0.1124 29.5542 33.0000 3.4458

 

NASA/TM—2013-218094 J–107
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 505.4758 115.4258 492.1206 1178.2676 0.4290 0.0291 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3314 9.1185 585.7991 520.8886 410.5396 0.0427 0.3263

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 489.3237 0.0000 489.3237 1179.5399 0.4148 0.2467 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1940 587.0901 520.8934 0.0000 0.0600 0.0407 0.0869

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8781 10.3340 1.1342 606.3157 23.4412 260.4281 2.0188

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 145972.719 0.428 486.240 571619.938 0.139584E-03

 

Melt Ratio at Stator LE, Throat, TE

0.30866E-01 0.38070E-01 0.58341E-01

 trTOT = 1.3246 Tt4 = 606.3157 T1 = 457.7357

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 924388.00 3079.1687 190.8654 2.4232 0.8521 4.0592 1.3246 37.3740

NASA/TM—2013-218094 J–108
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.495 EfDer = 0.995 SH = 0.583609E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.623 3683.368 4.265 457.736 1.000 1.000 0.980

 W Kg/sec = 26.192 Wdry = 57.620 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 186.586 3920.971 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 150121.750 45213.129 1.523 831.557 546.158 619.754 1.135

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 433.27 -0.15 433.27 0.42 0.77 705.87

 MEAN 17.06 0.00 -0.02 433.27 -0.15 433.27 0.42 0.68

 HUB 12.51 0.00 -0.02 433.27 -0.15 433.27 0.42 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.85 50.47 6.38 663.12 792.24 3.78 442.64 448.41 3.72

 MEAN 51.69 47.20 4.49 548.37 699.00 3.78 442.64 448.41 3.72

 HUB 42.87 38.62 4.25 402.11 591.22 3.78 442.64 448.41 3.72

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 665.68 356.83 561.96 1044.61 0.64 7.29 6.52 16.04

 MEAN 18.04 703.78 402.82 577.10 1039.26 0.68 7.43 6.80 12.53

 HUB 15.00 817.43 542.92 611.08 1028.52 0.79 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 663.12 640.01 306.29 0.61 7364.56 0.92 0.91

 MEAN 579.74 603.61 176.92 0.58 7267.77 0.92 0.91 0.91 1.28

 HUB 482.15 614.09 60.77 0.60 8145.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.24 495.82 1.08 460.17 473.04 1.92

 MEAN 5.54 1.30 4.09 495.32 1.08 455.48 472.86 2.31

 HUB 5.71 1.34 3.78 499.86 1.09 446.11 475.84 3.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.41 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 34.92 17.04 12.70 4.34 0.92 0.27 2.22

 HUB 41.62 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 749.5178 402.0350 632.5700 1035.0693 0.7241 -0.0849 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5841 3.9540 451.8101 473.9319 2.7097 32.4383 35.4000 2.9617

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 598.0381 146.2984 579.8676 1053.7025 0.5676 0.2799 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5517 4.4735 468.2299 473.4813 554.9116 0.0307 0.3983

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 594.7446 0.0000 594.7446 1054.0392 0.5643 0.3119 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4624 468.5480 473.4292 0.0000 0.0600 0.0482 0.2728

NASA/TM—2013-218094 J–109
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8636 5.5243 1.2954 496.9954 39.2612 226.6529 1.7570

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244087.266 0.555 794.834 649352.188 0.669837E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.403 EfDer = 0.998 SH = 0.765572E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.623 3683.368 5.524 496.995 1.000 1.000 0.980

 W Kg/sec = 26.192 Wdry = 57.619 WH2O = 0.004 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.091 3762.938 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 130119.242 45212.813 1.344 590.487 439.345 468.502 1.066

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 528.86 -0.18 528.86 0.50 0.80 674.80

 MEAN 18.08 0.00 -0.02 528.86 -0.18 528.86 0.50 0.74

 HUB 15.21 0.00 -0.02 528.86 -0.18 528.86 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.33 46.36 4.97 660.55 846.32 4.67 474.50 473.39 1.34

 MEAN 47.70 42.30 5.40 581.10 785.86 4.67 474.50 473.39 1.34

 HUB 42.76 37.84 4.92 488.90 720.35 4.67 474.50 473.39 1.34

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 595.33 284.87 522.74 1087.29 0.55 2.33 2.04 9.02

 MEAN 18.01 612.01 302.59 531.98 1083.44 0.56 2.40 2.13 7.35

 HUB 15.22 667.28 389.35 541.92 1079.91 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.37 641.30 371.50 0.59 5820.86 0.92 0.91

 MEAN 578.90 599.46 276.32 0.55 5452.86 0.92 0.91 0.91 1.42

 HUB 489.32 551.06 99.97 0.51 5929.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.49 527.09 1.06 498.59 488.99 0.59

 MEAN 6.63 1.20 5.36 525.18 1.06 495.06 488.10 0.66

 HUB 6.74 1.22 5.22 527.65 1.06 491.84 489.35 0.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.59 35.40 31.50 3.90 0.93 0.36 1.40

 MEAN 29.63 27.45 23.50 3.95 0.92 0.36 1.63

 HUB 35.70 10.45 6.50 3.95 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 687.9528 303.4359 617.4186 1076.3062 0.6392 -0.1972 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6814 5.0917 488.5857 488.8797 0.8248 26.1722 30.6000 4.4278

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 582.1108 123.4116 568.8784 1088.1510 0.5350 0.1001 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6551 5.4901 499.3935 488.6768 491.5697 0.0296 0.2700

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 611.0557 0.0000 611.0557 1085.1047 0.5631 0.1690 0.5911

NASA/TM—2013-218094 J–110
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3605 496.6184 488.6581 0.0000 0.0600 0.0480 0.0033

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8663 6.6306 1.2003 526.6395 29.6459 260.4333 2.0189

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184372.594 0.428 600.382 584345.938 0.804642E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.666 EfDer = 0.999 SH = 0.866735E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.623 3683.368 6.631 526.639 1.000 1.000 0.980

 W Kg/sec = 26.192 Wdry = 57.618 WH2O = 0.005 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 128.725 3655.498 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112423.633 45212.629 1.448 545.479 376.818 424.468 1.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 494.64 -0.17 494.64 0.45 0.74 640.22

 MEAN 17.74 0.00 -0.02 494.64 -0.17 494.64 0.45 0.69

 HUB 15.05 0.00 -0.02 494.64 -0.17 494.64 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.53 46.36 6.17 645.12 813.06 5.78 506.97 488.57 0.50

 MEAN 49.07 43.40 5.67 570.18 754.96 5.78 506.97 488.57 0.50

 HUB 44.37 38.84 5.53 483.76 692.00 5.78 506.97 488.57 0.50

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 569.93 285.39 493.33 1120.71 0.51 2.26 1.98 8.75

 MEAN 17.51 584.79 301.65 500.98 1117.21 0.52 2.34 2.07 6.78

 HUB 14.85 636.88 382.45 509.26 1113.96 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 636.76 605.67 351.37 0.54 5657.08 0.92 0.91

 MEAN 562.72 564.93 261.07 0.51 5283.85 0.92 0.91 0.91 1.44

 HUB 477.33 518.02 94.88 0.47 5681.92 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.66 555.88 1.06 529.76 501.75 0.26

 MEAN 7.84 1.18 6.52 553.95 1.05 526.45 500.95 0.29

 HUB 7.94 1.20 6.38 556.00 1.06 523.40 501.86 0.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.05 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 31.05 27.52 23.50 4.02 0.92 0.37 1.62

 HUB 36.91 10.55 6.50 4.05 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 650.5506 303.6282 575.3486 1111.6451 0.5852 -0.1777 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8906 6.2750 521.2572 501.5374 0.3344 27.8219 31.5000 3.6781

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 555.1122 121.0940 541.7433 1121.4686 0.4950 0.1074 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8687 6.6694 530.5053 501.4109 451.3937 0.0258 0.2963

 

NASA/TM—2013-218094 J–111
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 567.0255 0.0000 567.0255 1120.3108 0.5061 0.2028 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6027 529.4326 501.3759 0.0000 0.0600 0.0412 0.0592

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8752 7.8474 1.1835 555.2741 28.6367 248.3866 1.9255

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 178155.172 0.439 580.136 557310.063 0.924445E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.082 EfDer = 0.999 SH = 0.102824E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.623 3683.368 7.847 555.274 1.000 1.000 0.980

 W Kg/sec = 26.192 Wdry = 57.617 WH2O = 0.006 lbm/sec H2O = 0.058g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 111.682 3559.996 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98340.547 45212.344 1.570 513.330 326.947 395.845 1.211

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 459.78 -0.16 459.78 0.41 0.68 598.33

 MEAN 16.97 0.00 -0.02 459.78 -0.16 459.78 0.41 0.63

 HUB 14.32 0.00 -0.02 459.78 -0.16 459.78 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.41 46.36 7.05 619.08 771.27 7.01 538.29 501.34 0.24

 MEAN 49.88 43.80 6.08 545.50 713.54 7.01 538.29 501.34 0.24

 HUB 45.04 37.84 7.20 460.29 650.70 7.01 538.29 501.34 0.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 538.59 278.45 461.03 1151.29 0.47 2.16 1.89 8.34

 MEAN 16.57 550.01 289.10 467.91 1147.77 0.48 2.24 1.97 6.35

 HUB 13.89 595.32 358.47 475.29 1144.46 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 606.87 566.05 328.42 0.49 5260.12 0.92 0.91

 MEAN 532.74 527.54 243.64 0.46 4794.15 0.92 0.91 0.91 1.47

 HUB 446.47 483.37 88.01 0.42 4981.37 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.20 1.17 7.93 582.45 1.05 559.14 512.35 0.15

 MEAN 9.07 1.16 7.77 580.04 1.04 555.73 511.42 0.16

 HUB 9.12 1.16 7.60 581.01 1.05 552.53 511.82 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.13 35.46 31.50 3.96 0.93 0.39 1.40

 MEAN 31.71 27.51 23.50 4.01 0.93 0.38 1.62

 HUB 37.02 10.49 6.50 3.99 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 594.8403 290.7232 518.9556 1144.6343 0.5197 -0.1222 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1163 7.6006 552.7360 511.8565 0.1721 29.2579 32.4000 3.1421

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 513.9497 115.2639 500.8578 1152.0708 0.4461 0.1353 2.2705

 

NASA/TM—2013-218094 J–112
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0996 7.9514 559.9420 511.7781 432.2457 0.0223 0.3193

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 509.7524 0.0000 509.7524 1152.4027 0.4423 0.2293 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9481 560.2886 511.7296 0.0000 0.0600 0.0400 0.1329

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8774 9.0754 1.1565 581.1638 25.8920 250.4634 1.9416

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161148.703 0.438 524.757 550160.250 0.112597E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.425 EfDer = 1.000 SH = 0.131293E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.623 3683.368 9.075 581.163 1.000 1.000 0.980

 W Kg/sec = 26.192 Wdry = 57.616 WH2O = 0.008 lbm/sec H2O = 0.083g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 98.796 3479.798 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 87281.109 45211.840 1.762 509.668 289.245 384.739 1.330

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 411.00 -0.14 411.00 0.35 0.62 556.31

 MEAN 15.91 0.00 -0.02 411.00 -0.14 411.00 0.35 0.57

 HUB 13.07 0.00 -0.02 411.00 -0.14 411.00 0.35 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.09 47.36 7.73 588.87 718.23 8.33 567.60 511.73 0.15

 MEAN 51.23 44.80 6.43 511.50 656.28 8.33 567.60 511.73 0.15

 HUB 45.64 38.84 6.80 420.11 587.82 8.33 567.60 511.73 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.59 279.01 415.62 1179.42 0.42 2.05 1.78 7.43

 MEAN 15.50 505.42 277.44 422.46 1175.35 0.43 2.13 1.86 5.75

 HUB 12.59 539.04 325.48 429.69 1171.45 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 576.65 511.20 297.64 0.43 5008.09 0.92 0.91

 MEAN 498.15 476.64 220.71 0.41 4301.92 0.92 0.91 0.91 1.51

 HUB 404.69 436.93 79.21 0.37 4099.64 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.49 1.16 9.28 607.02 1.04 586.89 521.39 0.10

 MEAN 10.28 1.13 9.07 603.38 1.04 582.86 520.08 0.11

 HUB 10.22 1.13 8.86 602.33 1.04 578.99 519.71 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.87 35.61 31.50 4.11 0.93 0.43 1.40

 MEAN 33.29 27.58 23.50 4.08 0.93 0.40 1.64

 HUB 37.14 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 563.2738 282.5283 487.2937 1171.1724 0.4809 -0.2015 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3044 8.8137 578.7642 520.3677 0.1197 30.1048 33.0000 2.8952

 

NASA/TM—2013-218094 J–113
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 492.9135 112.5572 479.8902 1177.1956 0.4187 0.0446 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2783 9.1246 584.7312 520.2816 410.5396 0.0407 0.3339

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 477.3799 0.0000 477.3799 1178.3887 0.4051 0.2556 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1948 585.9421 520.2842 0.0000 0.0600 0.0395 0.1002

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8801 10.2799 1.1327 604.2406 23.0798 257.1081 1.9931

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 143721.922 0.432 468.009 558359.875 0.144224E-03

 

Melt Ratio at Stator LE, Throat, TE

0.32609E-01 0.39860E-01 0.60151E-01

 trTOT = 1.3201 Tt4 = 604.2406 T1 = 457.7355

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 911485.69 2968.1169 186.5861 2.4105 0.8584 4.4950 1.3201 37.3740

NASA/TM—2013-218094 J–114
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.824 EfDer = 0.996 SH = 0.586999E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.671 3652.662 4.265 457.735 1.000 1.000 0.980

 W Kg/sec = 25.760 Wdry = 56.668 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 183.503 3888.284 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 147119.531 44466.000 1.548 831.557 537.133 619.754 1.154

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 424.61 -0.15 424.61 0.41 0.76 699.99

 MEAN 17.06 0.00 -0.02 424.61 -0.15 424.61 0.41 0.67

 HUB 12.51 0.00 -0.02 424.61 -0.15 424.61 0.41 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.16 50.47 6.69 657.59 782.89 3.80 443.23 448.41 3.64

 MEAN 52.02 47.20 4.82 543.80 690.05 3.80 443.23 448.41 3.64

 HUB 43.21 38.62 4.59 398.76 582.60 3.80 443.23 448.41 3.64

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 656.09 357.97 549.84 1045.54 0.63 7.29 6.52 16.04

 MEAN 18.04 693.01 401.86 564.60 1040.18 0.67 7.43 6.80 12.53

 HUB 15.00 802.94 537.43 596.56 1029.80 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 657.59 626.17 299.63 0.60 7387.86 0.92 0.91

 MEAN 574.91 590.53 173.05 0.57 7250.48 0.92 0.91 0.91 1.29

 HUB 478.13 599.50 59.30 0.58 8063.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.27 495.62 1.08 460.99 472.91 1.88

 MEAN 5.52 1.30 4.12 494.91 1.08 456.28 472.61 2.26

 HUB 5.68 1.33 3.82 499.08 1.09 447.22 475.35 3.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.07 28.59 24.20 4.39 0.93 0.33 1.80

 MEAN 35.44 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 42.02 -5.68 -9.30 3.62 0.92 0.14 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 736.5360 401.0810 617.7535 1036.3201 0.7107 -0.0817 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5694 3.9915 452.9040 473.6405 2.6162 32.9939 35.4000 2.4061

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 584.8069 143.0616 567.0384 1054.6017 0.5545 0.2895 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5400 4.5068 469.0307 473.2200 554.9116 0.0294 0.4056

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 581.1714 0.0000 581.1714 1054.9661 0.5509 0.3216 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4990 469.3737 473.1751 0.0000 0.0600 0.0453 0.2844

NASA/TM—2013-218094 J–115
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8684 5.5159 1.2934 496.5372 38.8032 224.4702 1.7401

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 241241.625 0.558 772.586 636366.438 0.676811E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.765 EfDer = 0.999 SH = 0.776540E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.671 3652.662 5.516 496.537 1.000 1.000 0.980

 W Kg/sec = 25.760 Wdry = 56.667 WH2O = 0.004 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 147.769 3733.290 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 127406.789 44465.664 1.365 590.487 432.548 468.502 1.083

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 517.84 -0.18 517.84 0.49 0.79 669.48

 MEAN 18.08 0.00 -0.02 517.84 -0.18 517.84 0.49 0.73

 HUB 15.21 0.00 -0.02 517.84 -0.18 517.84 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.68 46.36 5.32 655.04 835.15 4.70 474.97 473.15 1.34

 MEAN 48.07 42.30 5.77 576.25 774.87 4.70 474.97 473.15 1.34

 HUB 43.12 37.84 5.28 484.83 709.50 4.70 474.97 473.15 1.34

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 587.25 287.00 512.34 1087.60 0.54 2.33 2.04 9.02

 MEAN 18.01 603.33 303.40 521.49 1083.69 0.56 2.40 2.13 7.35

 HUB 15.22 657.55 387.38 531.32 1080.10 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 650.90 628.42 363.90 0.58 5864.21 0.92 0.91

 MEAN 574.08 587.56 270.68 0.54 5467.39 0.92 0.91 0.91 1.43

 HUB 485.24 540.26 97.86 0.50 5899.81 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.22 5.51 526.60 1.06 498.87 488.78 0.60

 MEAN 6.62 1.20 5.38 524.57 1.06 495.29 487.82 0.67

 HUB 6.71 1.22 5.24 526.78 1.06 492.01 488.96 0.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.26 35.38 31.50 3.88 0.93 0.37 1.40

 MEAN 30.19 27.43 23.50 3.93 0.92 0.36 1.63

 HUB 36.10 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 676.2067 304.2484 603.8943 1076.9996 0.6279 -0.1914 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6653 5.1264 489.2163 488.5790 0.8216 26.7395 30.6000 3.8605

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 569.5397 120.7465 556.5930 1088.7009 0.5231 0.1137 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6418 5.5241 499.8998 488.3870 491.5697 0.0280 0.2786

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 596.9388 0.0000 596.9388 1085.8821 0.5497 0.1806 0.5911

NASA/TM—2013-218094 J–116
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4043 497.3317 488.3723 0.0000 0.0600 0.0447 0.0217

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8712 6.6201 1.2002 525.9814 29.4460 256.8549 1.9911

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183130.641 0.432 586.483 572212.250 0.817418E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 6.002 EfDer = 0.999 SH = 0.882664E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.671 3652.662 6.620 525.981 1.000 1.000 0.980

 W Kg/sec = 25.760 Wdry = 56.666 WH2O = 0.005 lbm/sec H2O = 0.044g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 126.719 3627.291 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110170.609 44465.480 1.471 545.479 370.946 424.468 1.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 484.73 -0.17 484.73 0.44 0.73 635.28

 MEAN 17.74 0.00 -0.02 484.73 -0.17 484.73 0.44 0.68 

 HUB 15.05 0.00 -0.02 484.73 -0.17 484.73 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.86 46.36 6.50 639.74 802.77 5.80 507.09 488.30 0.51 

 MEAN 49.40 43.40 6.00 565.42 744.89 5.80 507.09 488.30 0.51

 HUB 44.71 38.84 5.87 479.73 682.10 5.80 507.09 488.30 0.51

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 562.58 287.02 483.85 1120.64 0.50 2.26 1.98 8.75

 MEAN 17.51 576.86 302.10 491.43 1117.10 0.52 2.34 2.07 6.78

 HUB 14.85 627.94 380.40 499.60 1113.80 0.56 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 631.45 593.93 344.44 0.53 5689.18 0.92 0.91

 MEAN 558.03 554.07 255.93 0.50 5291.76 0.92 0.91 0.91 1.45

 HUB 473.35 508.17 92.95 0.46 5651.49 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.92 1.20 6.68 555.14 1.06 529.69 501.49 0.27

 MEAN 7.82 1.18 6.54 553.10 1.05 526.35 500.63 0.29

 HUB 7.91 1.19 6.39 554.95 1.06 523.25 501.46 0.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.68 35.45 31.50 3.95 0.93 0.39 1.40

 MEAN 31.58 27.51 23.50 4.01 0.93 0.38 1.62

 HUB 37.29 10.54 6.50 4.04 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 640.3427 304.0861 563.5339 1111.8352 0.5759 -0.1734 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8704 6.3029 521.4359 501.2099 0.3403 28.3515 31.5000 3.1485

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 543.7192 118.6087 530.6246 1121.6003 0.4848 0.1200 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8507 6.6982 530.6312 501.0890 451.3937 0.0247 0.3038

 

NASA/TM—2013-218094 J–117
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 555.1722 0.0000 555.1722 1120.5092 0.4955 0.2116 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6346 529.6213 501.0552 0.0000 0.0600 0.0400 0.0728

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8776 7.8300 1.1828 554.3934 28.4141 245.2655 1.9013

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176771.391 0.443 566.118 546468.938 0.943389E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.381 EfDer = 1.000 SH = 0.105161E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.671 3652.662 7.830 554.393 1.000 1.000 0.980

 W Kg/sec = 25.760 Wdry = 56.665 WH2O = 0.006 lbm/sec H2O = 0.059g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 109.994 3533.122 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96491.219 44465.188 1.594 513.330 322.005 395.845 1.229

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 451.13 -0.16 451.13 0.40 0.67 593.81

 MEAN 16.97 0.00 -0.02 451.13 -0.16 451.13 0.40 0.62

 HUB 14.32 0.00 -0.02 451.13 -0.16 451.13 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.70 46.36 7.34 613.92 761.98 7.02 538.04 501.02 0.25

 MEAN 50.18 43.80 6.38 540.95 704.49 7.02 538.04 501.02 0.25

 HUB 45.35 37.84 7.51 456.46 641.88 7.02 538.04 501.02 0.25

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 532.03 279.46 452.72 1150.83 0.46 2.16 1.89 8.34

 MEAN 16.57 542.91 289.18 459.49 1147.30 0.47 2.24 1.97 6.35

 HUB 13.89 587.28 356.43 466.76 1143.97 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 601.81 555.75 322.35 0.48 5279.26 0.92 0.91

 MEAN 528.30 517.99 239.12 0.45 4795.42 0.92 0.91 0.91 1.48

 HUB 442.75 474.67 86.32 0.41 4953.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.17 1.17 7.94 581.44 1.05 558.69 512.02 0.15

 MEAN 9.04 1.15 7.77 578.96 1.04 555.27 511.07 0.16

 HUB 9.09 1.16 7.61 579.77 1.05 552.05 511.41 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.69 35.45 31.50 3.95 0.93 0.40 1.40

 MEAN 32.18 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.37 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 586.4301 290.8032 509.2483 1144.3118 0.5125 -0.1198 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0869 7.6133 552.4241 511.4908 0.1782 29.7283 32.4000 2.6717

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 504.2575 113.0902 491.4125 1151.7444 0.4378 0.1458 2.2705

 

NASA/TM—2013-218094 J–118
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0717 7.9659 559.6248 511.4151 432.2457 0.0214 0.3260

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 500.1288 0.0000 500.1288 1152.0640 0.4341 0.2370 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9625 559.9593 511.3685 0.0000 0.0600 0.0391 0.1433

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 9.0483 1.1556 580.0536 25.6624 247.6771 1.9200

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 159720.500 0.441 511.511 540106.438 0.115333E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.684 EfDer = 1.000 SH = 0.134651E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.671 3652.662 9.048 580.053 1.000 1.000 0.980

 W Kg/sec = 25.760 Wdry = 56.664 WH2O = 0.008 lbm/sec H2O = 0.086g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.362 3454.089 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85754.742 44464.672 1.788 509.668 285.045 384.739 1.350

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 403.81 -0.14 403.81 0.35 0.61 552.20

 MEAN 15.91 0.00 -0.02 403.81 -0.14 403.81 0.35 0.56

 HUB 13.07 0.00 -0.02 403.81 -0.14 403.81 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.34 47.36 7.98 583.96 710.10 8.33 566.96 511.37 0.15

 MEAN 51.48 44.80 6.68 507.23 648.46 8.33 566.96 511.37 0.15

 HUB 45.90 38.84 7.06 416.61 580.30 8.33 566.96 511.37 0.15

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 494.99 279.30 408.67 1178.56 0.42 2.05 1.78 7.43

 MEAN 15.50 499.30 277.10 415.36 1174.52 0.43 2.13 1.86 5.75

 HUB 12.59 532.10 323.57 422.42 1170.63 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 571.85 502.58 292.55 0.43 5013.19 0.92 0.91

 MEAN 493.99 468.58 216.90 0.40 4296.57 0.92 0.91 0.91 1.52

 HUB 401.31 429.52 77.75 0.37 4075.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.45 1.15 9.27 605.72 1.04 586.04 521.00 0.10

 MEAN 10.24 1.13 9.06 602.05 1.04 582.03 519.67 0.11

 HUB 10.18 1.12 8.85 600.92 1.04 578.18 519.28 0.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.35 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.71 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.45 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 555.6964 282.1791 478.7206 1170.5028 0.4748 -0.1987 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2635 8.8132 578.1007 519.9592 0.1250 30.5170 33.0000 2.4830

 

NASA/TM—2013-218094 J–119
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.1031 110.5454 471.3126 1176.5394 0.4115 0.0560 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2397 9.1270 584.0782 519.8771 410.5396 0.0394 0.3397

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 468.9889 0.0000 468.9889 1177.6793 0.3982 0.2622 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1935 585.2355 519.8783 0.0000 0.0600 0.0387 0.1101

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8813 10.2405 1.1318 602.8963 22.8458 254.6653 1.9741

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 142264.172 0.435 455.607 548780.125 0.147792E-03

 

Melt Ratio at Stator LE, Throat, TE

0.33936E-01 0.41235E-01 0.61572E-01

 trTOT = 1.3171 Tt4 = 602.8963 T1 = 457.7354

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 903128.31 2892.3057 183.5028 2.4012 0.8621 4.8241 1.3171 37.3740

NASA/TM—2013-218094 J–120
 25μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.849 EfDer = 0.984 SH = 0.116537E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.713 3973.534 4.265 477.917 1.000 1.000 0.980

 W Kg/sec = 28.051 Wdry = 61.706 WH2O = 0.007 lbm/sec H2O = 0.040g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.190 4139.589 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 171740.531 48420.855 1.391 831.557 597.709 619.754 1.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 495.67 -0.17 495.67 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 495.67 -0.17 495.67 0.48 0.74

 HUB 12.51 0.00 -0.02 495.67 -0.17 495.67 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.29 50.47 4.82 715.36 870.44 3.66 458.16 461.04 3.35

 MEAN 50.05 47.20 2.85 591.57 771.91 3.66 458.16 461.04 3.35

 HUB 41.20 38.62 2.58 433.79 658.80 3.66 458.16 461.04 3.35

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 743.49 360.80 650.07 1061.29 0.70 7.29 6.52 16.04

 MEAN 18.04 789.57 420.36 668.37 1055.79 0.75 7.43 6.80 12.53

 HUB 15.00 933.49 592.61 721.26 1041.48 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.36 740.48 354.55 0.70 7446.90 0.92 0.90

 MEAN 625.41 699.12 205.05 0.66 7584.54 0.92 0.90 0.90 1.21

 HUB 520.13 724.90 72.48 0.70 8891.31 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 519.45 1.09 475.00 484.00 1.86

 MEAN 5.63 1.32 3.90 520.22 1.09 470.08 484.59 2.23

 HUB 5.89 1.38 3.52 527.51 1.10 457.43 489.13 3.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.03 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.17 17.06 12.70 4.36 0.91 0.22 2.22

 HUB 39.41 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 853.9658 419.5438 743.8015 1048.6494 0.8143 -0.1081 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6901 3.6966 463.7432 486.0110 2.8526 29.4253 35.4000 5.9747

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 695.7693 170.2064 674.6293 1070.7015 0.6498 0.2275 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6290 4.2521 483.4619 485.0045 554.9116 0.0424 0.3582

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 698.0885 0.0000 698.0885 1070.3904 0.6522 0.2521 1.3089

NASA/TM—2013-218094 J–121
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.1991 483.2070 484.8703 0.0000 0.0600 0.0739 0.1994

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8219 5.5696 1.3060 522.3918 44.4759 238.1453 1.8461

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 276545.031 0.540 964.439 688540.938 0.131983E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.458 EfDer = 0.989 SH = 0.147921E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.713 3973.534 5.570 522.391 1.000 1.000 0.980

 W Kg/sec = 28.051 Wdry = 61.704 WH2O = 0.009 lbm/sec H2O = 0.059g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.458 3959.469 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 150255.609 48420.258 1.234 590.487 478.496 468.502 0.979

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 610.70 -0.21 610.70 0.57 0.87 710.04

 MEAN 18.08 0.00 -0.02 610.70 -0.21 610.70 0.57 0.81

 HUB 15.21 0.00 -0.02 610.70 -0.21 610.70 0.57 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.41 46.36 3.05 712.58 938.64 4.50 492.41 484.72 1.17

 MEAN 45.76 42.30 3.46 626.87 875.33 4.50 492.41 484.72 1.17

 HUB 40.83 37.84 2.99 527.42 807.06 4.50 492.41 484.72 1.17

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 661.90 280.53 599.51 1109.45 0.60 2.33 2.04 9.02

 MEAN 18.01 682.13 306.64 609.33 1105.88 0.62 2.40 2.13 7.35

 HUB 15.22 744.71 412.25 620.19 1102.68 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.08 736.35 427.54 0.66 5732.79 0.92 0.90

 MEAN 624.51 687.26 317.87 0.62 5526.30 0.92 0.90 0.90 1.37

 HUB 527.87 630.87 115.61 0.57 6278.96 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.77 1.22 5.34 554.36 1.06 519.13 498.74 0.51

 MEAN 6.72 1.21 5.22 553.20 1.06 515.79 498.31 0.57

 HUB 6.89 1.24 5.10 557.40 1.07 512.81 500.15 0.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.08 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.71 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.61 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 782.7081 307.4963 719.7763 1095.0103 0.7148 -0.2379 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7805 4.8421 505.7412 499.2523 0.7672 23.1327 30.6000 7.4673

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 676.7531 143.4765 661.3692 1108.3971 0.6106 0.0194 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7297 5.2478 518.1687 498.8494 491.5697 0.0421 0.2198

 

NASA/TM—2013-218094 J–122
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 720.9962 0.0000 720.9962 1103.0468 0.6536 0.0960 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0282 513.2018 498.8109 0.0000 0.0600 0.0754 -0.1197

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8226 6.6772 1.1989 554.9855 32.5952 281.1149 2.1792

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 202775.203 0.404 707.170 623577.250 0.154206E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.833 EfDer = 0.991 SH = 0.164178E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.713 3973.534 6.677 554.985 1.000 1.000 0.980

 W Kg/sec = 28.051 Wdry = 61.703 WH2O = 0.010 lbm/sec H2O = 0.075g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.533 3841.442 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 129348.734 48419.949 1.326 545.479 411.411 424.468 1.032

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 569.11 -0.20 569.11 0.51 0.80 672.78

 MEAN 17.74 0.00 -0.02 569.11 -0.20 569.11 0.51 0.75

 HUB 15.05 0.00 -0.02 569.11 -0.20 569.11 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.73 46.36 4.37 695.94 899.16 5.61 528.96 498.58 0.42

 MEAN 47.23 43.40 3.83 615.09 838.13 5.61 528.96 498.58 0.42

 HUB 42.53 38.84 3.69 521.87 772.29 5.61 528.96 498.58 0.42

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 631.66 283.69 564.37 1146.30 0.55 2.26 1.98 8.75

 MEAN 17.51 649.95 307.48 572.62 1142.98 0.57 2.34 2.07 6.78

 HUB 14.85 709.14 405.52 581.75 1139.96 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 693.62 403.23 0.61 5623.85 0.92 0.91

 MEAN 607.05 646.25 299.57 0.57 5386.42 0.92 0.91 0.91 1.40

 HUB 514.93 591.95 109.41 0.52 6024.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.00 1.20 6.53 586.33 1.06 554.26 510.74 0.22

 MEAN 7.94 1.19 6.40 585.01 1.05 551.06 510.28 0.24

 HUB 8.10 1.21 6.26 588.56 1.06 548.15 511.65 0.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.69 35.55 31.50 4.05 0.93 0.34 1.40

 MEAN 28.23 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.88 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 733.4656 309.4991 664.9678 1134.9642 0.6462 -0.2059 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0005 6.0620 543.4089 510.9514 0.2877 24.9589 31.5000 6.5411

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 641.4871 139.9361 626.0380 1145.5382 0.5600 0.0338 2.3726

 

NASA/TM—2013-218094 J–123
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9596 6.4499 553.5674 510.7216 451.3937 0.0352 0.2531

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 659.1487 0.0000 659.1487 1143.5997 0.5764 0.1431 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3394 551.7258 510.6434 0.0000 0.0600 0.0606 -0.0343

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8444 7.9185 1.1859 586.6313 31.6479 266.5661 2.0664

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 196973.625 0.417 686.937 589370.563 0.172927E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.422 EfDer = 0.995 SH = 0.188695E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.713 3973.534 7.918 586.631 1.000 1.000 0.980

 W Kg/sec = 28.051 Wdry = 61.701 WH2O = 0.012 lbm/sec H2O = 0.100g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.836 3736.392 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112483.953 48419.484 1.439 513.330 356.704 395.845 1.110

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 525.90 -0.18 525.90 0.45 0.74 627.98

 MEAN 16.97 0.00 -0.02 525.90 -0.18 525.90 0.45 0.68

 HUB 14.32 0.00 -0.02 525.90 -0.18 525.90 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.79 46.36 5.43 667.85 850.20 6.88 564.42 510.55 0.19

 MEAN 48.22 43.80 4.42 588.47 789.36 6.88 564.42 510.55 0.19

 HUB 43.37 37.84 5.53 496.56 723.41 6.88 564.42 510.55 0.19

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 594.60 279.95 524.57 1180.25 0.50 2.16 1.89 8.34

 MEAN 16.57 609.34 296.62 532.27 1176.74 0.52 2.24 1.97 6.35

 HUB 13.89 661.27 380.77 540.64 1173.49 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.68 644.67 374.73 0.55 5288.90 0.92 0.91

 MEAN 574.71 600.54 278.09 0.51 4919.26 0.92 0.91 0.91 1.42

 HUB 481.64 549.97 100.87 0.47 5291.49 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.31 1.18 7.85 616.09 1.05 587.69 520.96 0.12

 MEAN 9.21 1.16 7.69 614.03 1.05 584.21 520.27 0.13

 HUB 9.31 1.18 7.53 616.11 1.05 580.98 521.02 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.09 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.13 27.59 23.50 4.09 0.92 0.35 1.62

 HUB 35.16 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 664.2007 298.2906 593.4521 1172.4172 0.5665 -0.1371 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2617 7.4696 579.9852 520.7540 0.1381 26.6858 32.4000 5.7142

 

NASA/TM—2013-218094 J–124
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 588.3720 131.9546 573.3843 1180.1038 0.4986 0.0751 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2316 7.8066 587.6111 520.6212 432.2457 0.0289 0.2831

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 583.6974 0.0000 583.6974 1180.5160 0.4944 0.1859 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.8027 588.0540 520.5522 0.0000 0.0600 0.0476 0.0726

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8618 9.2019 1.1621 615.4078 28.7789 266.8243 2.0684

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 179225.469 0.418 625.041 577108.375 0.201860E-03

 

Melt Ratio at Stator LE, Throat, TE

0.13877E-02 0.76840E-02 0.23798E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.029 EfDer = 0.997 SH = 0.221533E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.713 3973.534 9.202 615.407 1.000 1.000 0.980

 W Kg/sec = 28.051 Wdry = 61.699 WH2O = 0.014 lbm/sec H2O = 0.133g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.384 3647.990 1.380 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98952.352 48418.863 1.621 509.668 314.423 384.739 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 465.96 -0.16 465.96 0.39 0.66 583.19

 MEAN 15.91 0.00 -0.02 465.96 -0.16 465.96 0.39 0.61

 HUB 13.07 0.00 -0.02 465.96 -0.16 465.96 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.75 47.36 6.39 635.26 787.96 8.29 597.98 520.51 0.11

 MEAN 49.83 44.80 5.03 551.79 722.34 8.29 597.98 520.51 0.11

 HUB 44.22 38.84 5.38 453.21 650.13 8.29 597.98 520.51 0.11

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 548.87 285.62 468.70 1211.88 0.45 2.05 1.78 7.43

 MEAN 15.50 556.80 287.65 476.74 1207.55 0.46 2.13 1.86 5.75

 HUB 12.59 596.34 346.63 485.25 1203.44 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 576.96 336.46 0.48 5126.97 0.92 0.91

 MEAN 537.39 538.19 249.74 0.45 4460.49 0.92 0.91 0.91 1.47

 HUB 436.57 493.51 89.94 0.41 4366.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.69 1.16 9.31 643.94 1.05 619.76 529.91 0.07

 MEAN 10.49 1.14 9.09 640.23 1.04 615.35 528.73 0.08

 HUB 10.46 1.14 8.87 639.71 1.04 611.17 528.59 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.36 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.11 27.65 23.50 4.15 0.92 0.38 1.64

 HUB 35.54 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 625.6859 292.9281 552.8797 1202.1107 0.5205 -0.2177 2.0437

 

NASA/TM—2013-218094 J–125
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5206 8.7673 609.8831 529.0524 0.0863 27.9156 33.0000 5.0844

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 560.3842 127.9642 545.5782 1208.2257 0.4638 -0.0201 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4758 9.0572 616.0964 528.9111 410.5396 0.0506 0.3039

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 541.4936 0.0000 541.4936 1209.8311 0.4476 0.2202 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1534 617.7679 528.9226 0.0000 0.0600 0.0454 0.0457

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8694 10.4835 1.1393 641.2928 25.8895 270.7858 2.0991

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161345.141 0.417 562.684 580983.000 0.233373E-03

 

Melt Ratio at Stator LE, Throat, TE

0.86851E-01 0.96352E-01 0.12316E+00

 trTOT = 1.3418 Tt4 = 641.2928 T1 = 477.9170

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1016864.50 3546.2717 204.1905 2.4583 0.8236 2.8490 1.3418 37.3740

NASA/TM—2013-218094 J–126
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 3.960 EfDer = 0.992 SH = 0.119570E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.014 3823.140 4.265 477.917 1.000 1.000 0.980

 W Kg/sec = 26.370 Wdry = 58.007 WH2O = 0.007 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 191.950 3982.910 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 158834.750 45518.203 1.480 831.557 561.882 619.754 1.103

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 458.42 -0.16 458.42 0.44 0.79 717.02

 MEAN 17.06 0.00 -0.02 458.42 -0.16 458.42 0.44 0.70

 HUB 12.51 0.00 -0.02 458.42 -0.16 458.42 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.34 50.47 5.87 688.28 827.10 3.74 461.02 460.98 3.08

 MEAN 51.16 47.20 3.96 569.18 730.96 3.74 461.02 460.98 3.08

 HUB 42.33 38.62 3.71 417.37 620.07 3.74 461.02 460.98 3.08

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 698.17 363.19 596.27 1065.68 0.66 7.29 6.52 16.04

 MEAN 18.04 739.23 413.89 612.50 1060.22 0.70 7.43 6.80 12.53

 HUB 15.00 862.55 565.36 651.43 1048.48 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 688.28 679.13 325.10 0.64 7495.79 0.92 0.91

 MEAN 601.74 640.66 187.85 0.60 7467.60 0.92 0.91 0.91 1.26

 HUB 500.45 654.65 64.91 0.62 8482.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.57 1.31 4.19 518.14 1.08 478.94 483.26 1.68

 MEAN 5.56 1.30 4.03 517.99 1.08 474.04 483.36 2.00

 HUB 5.76 1.35 3.71 523.43 1.10 463.60 486.67 2.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.35 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.05 17.05 12.70 4.35 0.92 0.25 2.22

 HUB 40.95 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 790.3317 413.0850 673.7841 1055.2651 0.7489 -0.0908 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6132 3.8847 469.6227 484.4772 2.3785 31.5117 35.4000 3.8883

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 635.2681 155.4060 615.9664 1075.0448 0.5909 0.2640 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5744 4.4136 487.4014 483.7665 554.9116 0.0335 0.3862

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 632.8136 0.0000 632.8136 1075.2975 0.5885 0.2950 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.3947 487.6553 483.6878 0.0000 0.0600 0.0542 0.2525

NASA/TM—2013-218094 J–127
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8536 5.5401 1.2991 519.8531 41.9379 230.2712 1.7850

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 260780.688 0.550 854.944 636799.438 0.137421E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.808 EfDer = 0.996 SH = 0.156221E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.014 3823.140 5.540 519.853 1.000 1.000 0.980

 W Kg/sec = 26.370 Wdry = 58.005 WH2O = 0.009 lbm/sec H2O = 0.063g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 154.102 3818.898 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 137903.844 45517.543 1.309 590.487 451.112 468.502 1.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 560.50 -0.19 560.50 0.52 0.82 684.83

 MEAN 18.08 0.00 -0.02 560.50 -0.19 560.50 0.52 0.76

 HUB 15.21 0.00 -0.02 560.50 -0.19 560.50 0.52 0.70

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.74 46.36 4.38 685.61 885.72 4.63 494.60 483.62 1.17

 MEAN 47.11 42.30 4.81 603.15 823.52 4.63 494.60 483.62 1.17

 HUB 42.17 37.84 4.33 507.45 756.22 4.63 494.60 483.62 1.17

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 623.39 287.95 552.90 1110.56 0.56 2.33 2.04 9.02

 MEAN 18.01 641.46 308.34 562.50 1106.71 0.58 2.40 2.13 7.35

 HUB 15.22 699.79 401.88 572.88 1103.21 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 681.28 678.53 393.32 0.61 5883.98 0.92 0.91

 MEAN 600.87 634.02 292.53 0.57 5556.60 0.92 0.91 0.91 1.40

 HUB 507.89 582.60 106.00 0.53 6120.82 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.45 551.42 1.06 520.17 497.72 0.54

 MEAN 6.66 1.20 5.32 549.66 1.06 516.58 497.02 0.59

 HUB 6.79 1.22 5.19 552.69 1.06 513.32 498.39 0.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.51 35.43 31.50 3.93 0.93 0.35 1.40

 MEAN 28.73 27.48 23.50 3.98 0.92 0.34 1.63

 HUB 35.05 10.48 6.50 3.98 0.92 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 724.9170 309.2012 655.6671 1098.5433 0.6599 -0.2077 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7137 5.0293 509.0143 497.8330 0.7466 25.2477 30.6000 5.3523

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 617.7047 130.9578 603.6631 1110.9661 0.5560 0.0771 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6818 5.4300 520.5830 497.5248 491.5697 0.0327 0.2557

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 650.4768 0.0000 650.4768 1107.3741 0.5874 0.1492 0.5911

NASA/TM—2013-218094 J–128
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2805 517.2456 497.5089 0.0000 0.0600 0.0545 -0.0292

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8564 6.6512 1.2005 551.2532 31.4017 266.4631 2.0656

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195358.328 0.421 640.463 574143.688 0.163708E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.120 EfDer = 0.997 SH = 0.175352E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.014 3823.140 6.651 551.253 1.000 1.000 0.980

 W Kg/sec = 26.370 Wdry = 58.003 WH2O = 0.010 lbm/sec H2O = 0.082g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 132.180 3708.538 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 118956.781 45517.203 1.410 545.479 386.961 424.468 1.097

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 523.39 -0.18 523.39 0.47 0.76 649.51

 MEAN 17.74 0.00 -0.02 523.39 -0.18 523.39 0.47 0.71

 HUB 15.05 0.00 -0.02 523.39 -0.18 523.39 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.99 46.36 5.63 669.60 850.02 5.74 529.24 497.36 0.45

 MEAN 48.52 43.40 5.12 591.81 790.18 5.74 529.24 497.36 0.45

 HUB 43.82 38.84 4.98 502.12 725.42 5.74 529.24 497.36 0.45

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 596.07 289.47 521.07 1145.47 0.52 2.26 1.98 8.75

 MEAN 17.51 612.22 308.07 529.06 1141.95 0.54 2.34 2.07 6.78

 HUB 14.85 667.22 395.00 537.73 1138.70 0.59 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.92 639.92 371.46 0.56 5737.93 0.92 0.91

 MEAN 584.07 596.72 276.00 0.52 5396.48 0.92 0.91 0.91 1.43

 HUB 495.44 547.03 100.45 0.48 5868.42 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.96 1.20 6.64 582.02 1.06 553.47 509.54 0.24

 MEAN 7.88 1.18 6.50 580.19 1.05 550.07 508.87 0.27

 HUB 8.00 1.20 6.35 582.72 1.06 546.94 509.88 0.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.05 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.21 27.55 23.50 4.05 0.92 0.36 1.62

 HUB 36.30 10.58 6.50 4.08 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 683.6570 310.0939 609.2855 1135.6757 0.6020 -0.1851 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9319 6.2273 544.0918 509.4756 0.3098 26.9737 31.5000 4.5263

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 587.7576 128.2153 573.6025 1145.8610 0.5129 0.0867 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9056 6.6214 553.8865 509.2912 451.3937 0.0281 0.2839

 

NASA/TM—2013-218094 J–129
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 601.0734 0.0000 601.0734 1144.5172 0.5252 0.1869 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5458 552.6179 509.2496 0.0000 0.0600 0.0453 0.0346

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8688 7.8807 1.1849 581.6418 30.3907 253.5447 1.9655

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189154.891 0.433 620.126 546281.188 0.185713E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.600 EfDer = 0.999 SH = 0.203865E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.014 3823.140 7.881 581.641 1.000 1.000 0.980

 W Kg/sec = 26.370 Wdry = 58.002 WH2O = 0.012 lbm/sec H2O = 0.110g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.591 3610.360 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 103828.258 45516.695 1.530 513.330 335.494 395.845 1.180

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 485.43 -0.17 485.43 0.42 0.70 606.79

 MEAN 16.97 0.00 -0.02 485.43 -0.17 485.43 0.42 0.65

 HUB 14.32 0.00 -0.02 485.43 -0.17 485.43 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.94 46.36 6.58 642.58 805.46 6.99 562.71 509.19 0.22

 MEAN 49.40 43.80 5.60 566.20 745.93 6.99 562.71 509.19 0.22

 HUB 44.55 37.84 6.71 477.76 681.22 6.99 562.71 509.19 0.22

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 562.58 283.45 485.95 1177.46 0.48 2.16 1.89 8.34

 MEAN 16.57 575.16 295.90 493.20 1173.88 0.49 2.24 1.97 6.35

 HUB 13.89 623.08 370.44 501.00 1170.52 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 629.90 596.81 346.45 0.51 5354.76 0.92 0.91

 MEAN 552.96 556.17 257.05 0.47 4907.12 0.92 0.91 0.91 1.45

 HUB 463.41 509.55 92.98 0.44 5147.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.25 1.17 7.93 610.34 1.05 584.92 519.54 0.14

 MEAN 9.13 1.16 7.76 607.94 1.05 581.37 518.72 0.15

 HUB 9.19 1.17 7.60 609.23 1.05 578.05 519.21 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.25 35.49 31.50 3.99 0.93 0.38 1.40

 MEAN 30.96 27.53 23.50 4.03 0.92 0.38 1.62

 HUB 36.48 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 623.3550 297.5684 547.7450 1170.3816 0.5326 -0.1262 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1743 7.5814 577.9681 519.1614 0.1606 28.5135 32.4000 3.8865

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 542.5479 121.6776 528.7275 1178.0161 0.4606 0.1185 2.2705

 

NASA/TM—2013-218094 J–130
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1546 7.9304 585.5327 519.0511 432.2457 0.0238 0.3088

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 538.1417 0.0000 538.1417 1178.3710 0.4567 0.2170 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9270 585.9172 518.9932 0.0000 0.0600 0.0418 0.1161

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 9.1290 1.1584 609.1672 27.5280 255.0070 1.9768

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171437.109 0.432 562.040 538096.313 0.218420E-03

 

Melt Ratio at Stator LE, Throat, TE

0.86114E-02 0.15252E-01 0.32152E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.022 EfDer = 0.999 SH = 0.238677E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.014 3823.140 9.129 609.167 1.000 1.000 0.980

 W Kg/sec = 26.370 Wdry = 58.000 WH2O = 0.014 lbm/sec H2O = 0.145g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 101.236 3527.850 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 91905.844 45516.070 1.719 509.668 296.422 384.739 1.298

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 432.78 -0.15 432.78 0.36 0.63 563.99

 MEAN 15.91 0.00 -0.02 432.78 -0.15 432.78 0.36 0.58

 HUB 13.07 0.00 -0.02 432.78 -0.15 432.78 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.71 47.36 7.35 611.21 749.04 8.34 594.13 518.96 0.13

 MEAN 50.82 44.80 6.02 530.91 685.07 8.34 594.13 518.96 0.13

 HUB 45.23 38.84 6.39 436.06 614.47 8.34 594.13 518.96 0.13

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 521.90 285.42 436.94 1206.96 0.43 2.05 1.78 7.43

 MEAN 15.50 527.68 284.78 444.24 1202.76 0.44 2.13 1.86 5.75

 HUB 12.59 563.52 336.61 451.94 1198.73 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 598.54 537.55 313.12 0.45 5123.13 0.92 0.91

 MEAN 517.05 501.29 232.27 0.42 4415.81 0.92 0.91 0.91 1.50

 HUB 420.04 459.57 83.43 0.38 4239.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.57 1.16 9.31 636.60 1.05 614.74 528.20 0.09

 MEAN 10.36 1.13 9.09 632.82 1.04 610.47 526.97 0.09

 HUB 10.31 1.13 8.88 631.87 1.04 606.38 526.68 0.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.15 35.63 31.50 4.13 0.93 0.42 1.40

 MEAN 32.66 27.60 23.50 4.10 0.93 0.39 1.64

 HUB 36.68 10.46 6.50 3.96 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 589.4113 290.0040 513.1310 1198.1820 0.4919 -0.2058 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3868 8.8221 605.8865 527.2597 0.1033 29.4736 33.0000 3.5264

 

NASA/TM—2013-218094 J–131
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 519.2570 118.5728 505.5376 1204.3391 0.4312 0.0268 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3564 9.1295 612.1267 527.1479 410.5396 0.0431 0.3253

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 502.6116 0.0000 502.6116 1205.6499 0.4169 0.2456 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2063 613.4922 527.1500 0.0000 0.0600 0.0409 0.0850

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8778 10.3593 1.1348 633.7604 24.5977 260.9218 2.0226

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 153289.406 0.428 502.544 544921.125 0.251139E-03

 

Melt Ratio at Stator LE, Throat, TE

0.95410E-01 0.10519E+00 0.13224E+00

 trTOT = 1.3261 Tt4 = 633.7604 T1 = 477.9165

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 970020.38 3180.1160 191.9502 2.4291 0.8504 3.9596 1.3261 37.3740

NASA/TM—2013-218094 J–132
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.390 EfDer = 0.994 SH = 0.120686E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.717 3776.068 4.265 477.916 1.000 1.000 0.980

 W Kg/sec = 25.781 Wdry = 56.710 WH2O = 0.007 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 187.661 3933.871 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154481.719 44501.090 1.514 831.557 549.327 619.754 1.128

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.86 -0.15 445.86 0.43 0.78 708.20

 MEAN 17.06 0.00 -0.02 445.86 -0.15 445.86 0.43 0.69

 HUB 12.51 0.00 -0.02 445.86 -0.15 445.86 0.43 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.75 50.47 6.28 679.81 813.10 3.77 461.93 460.96 3.00

 MEAN 51.59 47.20 4.39 562.17 717.63 3.77 461.93 460.96 3.00

 HUB 42.77 38.62 4.15 412.23 607.33 3.77 461.93 460.96 3.00

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 683.76 364.46 578.53 1067.07 0.64 7.29 6.52 16.04

 MEAN 18.04 723.12 412.16 594.16 1061.60 0.68 7.43 6.80 12.53

 HUB 15.00 840.62 556.92 629.67 1050.48 0.80 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 679.81 658.89 315.34 0.62 7522.07 0.92 0.91

 MEAN 594.33 621.46 182.18 0.59 7436.27 0.92 0.91 0.91 1.28

 HUB 494.29 632.78 62.63 0.60 8355.67 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.23 517.78 1.08 480.18 483.06 1.63

 MEAN 5.54 1.30 4.08 517.33 1.08 475.28 482.99 1.94

 HUB 5.72 1.34 3.77 522.20 1.09 465.37 485.96 2.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.21 28.59 24.20 4.39 0.93 0.31 1.80

 MEAN 34.75 17.05 12.70 4.35 0.92 0.27 2.22

 HUB 41.49 -5.68 -9.30 3.62 0.92 0.12 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 770.6697 411.3551 651.7045 1057.1921 0.7290 -0.0860 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5903 3.9410 471.3422 484.0397 2.2636 32.2601 35.4000 3.1399

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 615.7686 150.6358 597.0593 1076.3781 0.5721 0.2769 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5568 4.4627 488.6139 483.3971 554.9116 0.0312 0.3960

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 612.5488 0.0000 612.5488 1076.7051 0.5689 0.3088 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4503 488.9352 483.3332 0.0000 0.0600 0.0493 0.2691

NASA/TM—2013-218094 J–133
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8618 5.5282 1.2963 519.1034 41.1884 227.3489 1.7624

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 256124.719 0.554 820.917 619347.063 0.139505E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.292 EfDer = 0.998 SH = 0.159430E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.717 3776.068 5.528 519.103 1.000 1.000 0.980

 W Kg/sec = 25.781 Wdry = 56.708 WH2O = 0.009 lbm/sec H2O = 0.065g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.874 3774.601 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 133918.234 44500.414 1.337 590.487 441.663 468.502 1.061

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 544.30 -0.19 544.30 0.50 0.80 676.89

 MEAN 18.08 0.00 -0.02 544.30 -0.19 544.30 0.50 0.74

 HUB 15.21 0.00 -0.02 544.30 -0.19 544.30 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.22 46.36 4.86 677.17 868.95 4.66 495.29 483.28 1.17

 MEAN 47.59 42.30 5.29 595.72 807.08 4.66 495.29 483.28 1.17

 HUB 42.65 37.84 4.81 501.21 740.04 4.66 495.29 483.28 1.17

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 611.26 290.67 537.73 1110.94 0.55 2.33 2.04 9.02

 MEAN 18.01 628.52 309.16 547.22 1107.01 0.57 2.40 2.13 7.35

 HUB 15.22 685.36 398.72 557.43 1103.42 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.89 659.73 382.22 0.59 5939.28 0.92 0.91 

 MEAN 593.47 616.67 284.31 0.56 5571.41 0.92 0.91 0.91 1.41

 HUB 501.63 566.85 102.91 0.51 6072.64 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.22 5.48 550.57 1.06 520.53 497.41 0.54

 MEAN 6.64 1.20 5.35 548.62 1.06 516.86 496.63 0.61

 HUB 6.75 1.22 5.22 551.28 1.06 513.52 497.85 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.39 35.41 31.50 3.91 0.93 0.36 1.40

 MEAN 29.47 27.45 23.50 3.95 0.92 0.35 1.63

 HUB 35.58 10.46 6.50 3.96 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 707.1891 310.0313 635.6077 1099.5590 0.6432 -0.1991 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6896 5.0815 509.9574 497.4034 0.7442 26.0018 30.6000 4.5982

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 599.1392 127.0218 585.5196 1111.7294 0.5389 0.0960 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6623 5.4808 521.3014 497.1177 491.5697 0.0302 0.2674

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 629.2781 0.0000 629.2781 1108.5298 0.5677 0.1655 0.5911

NASA/TM—2013-218094 J–134
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3476 518.3284 497.1081 0.0000 0.0600 0.0491 -0.0025

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8646 6.6367 1.2005 550.1549 31.0532 261.5280 2.0273

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193193.406 0.427 619.213 557756.188 0.167371E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.568 EfDer = 0.999 SH = 0.179692E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.717 3776.068 6.637 550.155 1.000 1.000 0.980

 W Kg/sec = 25.781 Wdry = 56.707 WH2O = 0.010 lbm/sec H2O = 0.085g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 129.379 3666.532 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115650.672 44500.059 1.440 545.479 378.762 424.468 1.121

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 508.84 -0.18 508.84 0.45 0.75 642.15

 MEAN 17.74 0.00 -0.02 508.84 -0.18 508.84 0.45 0.69

 HUB 15.05 0.00 -0.02 508.84 -0.18 508.84 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.43 46.36 6.07 661.35 834.59 5.77 529.35 496.98 0.46

 MEAN 48.97 43.40 5.57 584.53 775.11 5.77 529.35 496.98 0.46

 HUB 44.27 38.84 5.43 495.93 710.66 5.77 529.35 496.98 0.46

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 585.02 291.44 507.26 1145.24 0.51 2.26 1.98 8.75

 MEAN 17.51 600.38 308.39 515.13 1141.66 0.53 2.34 2.07 6.78

 HUB 14.85 653.96 391.75 523.64 1138.35 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.79 622.80 361.35 0.54 5776.91 0.92 0.91

 MEAN 576.88 580.90 268.50 0.51 5401.90 0.92 0.91 0.91 1.44

 HUB 489.34 532.65 97.59 0.47 5820.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.94 1.20 6.66 580.75 1.06 553.25 509.16 0.25

 MEAN 7.85 1.18 6.52 578.76 1.05 549.80 508.43 0.28

 HUB 7.95 1.20 6.38 580.98 1.06 546.61 509.33 0.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.88 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 30.91 27.53 23.50 4.03 0.92 0.37 1.62

 HUB 36.80 10.56 6.50 4.06 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 668.3433 310.4101 591.8854 1135.8672 0.5884 -0.1790 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9023 6.2693 544.2759 509.0096 0.3182 27.6744 31.5000 3.8256

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 571.0107 124.5621 557.2590 1145.9414 0.4983 0.1039 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8796 6.6643 553.9664 508.8360 451.3937 0.0262 0.2942

 

NASA/TM—2013-218094 J–135
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 583.3409 0.0000 583.3409 1144.7305 0.5096 0.2004 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5966 552.8258 508.8021 0.0000 0.0600 0.0416 0.0554

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8744 7.8581 1.1840 580.1620 30.0092 249.2668 1.9323

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186782.625 0.438 598.666 531787.750 0.190686E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.003 EfDer = 0.999 SH = 0.209739E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.717 3776.068 7.858 580.162 1.000 1.000 0.980

 W Kg/sec = 25.781 Wdry = 56.705 WH2O = 0.012 lbm/sec H2O = 0.113g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 112.210 3570.453 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 101099.172 44499.539 1.563 513.330 328.523 395.845 1.205 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 472.67 -0.16 472.67 0.41 0.69 600.09

 MEAN 16.97 0.00 -0.02 472.67 -0.16 472.67 0.41 0.63

 HUB 14.32 0.00 -0.02 472.67 -0.16 472.67 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.33 46.36 6.97 634.66 791.47 7.01 562.22 508.75 0.23

 MEAN 49.80 43.80 6.00 559.23 732.35 7.01 562.22 508.75 0.23

 HUB 44.96 37.84 7.12 471.88 668.01 7.01 562.22 508.75 0.23

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 552.67 284.60 473.76 1176.62 0.47 2.16 1.89 8.34

 MEAN 16.57 564.50 295.73 480.84 1173.03 0.48 2.24 1.97 6.35

 HUB 13.89 611.09 367.22 488.45 1169.64 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.14 581.70 337.54 0.49 5376.41 0.92 0.91

 MEAN 546.15 542.14 250.42 0.46 4904.10 0.92 0.91 0.91 1.47

 HUB 457.71 496.76 90.49 0.42 5103.07 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.21 1.17 7.94 608.62 1.05 584.09 519.08 0.14

 MEAN 9.09 1.16 7.77 606.12 1.04 580.53 518.22 0.16

 HUB 9.14 1.16 7.61 607.17 1.05 577.18 518.63 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.99 35.47 31.50 3.97 0.93 0.39 1.40

 MEAN 31.59 27.51 23.50 4.01 0.93 0.38 1.62

 HUB 36.94 10.50 6.50 4.00 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 610.7258 297.3896 533.4280 1169.7618 0.5221 -0.1228 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1337 7.6028 577.3548 518.6436 0.1686 29.1399 32.4000 3.2601

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 528.2614 118.4736 514.8049 1177.3761 0.4487 0.1327 2.2705

 

NASA/TM—2013-218094 J–136
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1165 7.9543 584.8963 518.5382 432.2457 0.0225 0.3177

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 523.9495 0.0000 523.9495 1177.7130 0.4449 0.2274 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9510 585.2625 518.4833 0.0000 0.0600 0.0402 0.1303

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8769 9.0921 1.1570 607.3021 27.1426 251.1751 1.9471

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 169038.766 0.437 541.794 524770.563 0.224778E-03

 

Melt Ratio at Stator LE, Throat, TE

0.10869E-01 0.17618E-01 0.34763E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.364 EfDer = 1.000 SH = 0.245324E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.717 3776.068 9.092 607.301 1.000 1.000 0.980

 W Kg/sec = 25.781 Wdry = 56.703 WH2O = 0.014 lbm/sec H2O = 0.149g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 99.224 3489.760 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89672.094 44498.910 1.754 509.668 290.530 384.739 1.324

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 422.26 -0.15 422.26 0.36 0.62 557.90

 MEAN 15.91 0.00 -0.02 422.26 -0.15 422.26 0.36 0.57

 HUB 13.07 0.00 -0.02 422.26 -0.15 422.26 0.36 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.03 47.36 7.67 603.69 736.83 8.34 592.99 518.46 0.14

 MEAN 51.16 44.80 6.36 524.37 673.37 8.34 592.99 518.46 0.14

 HUB 45.58 38.84 6.74 430.69 603.26 8.34 592.99 518.46 0.14

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 513.49 285.45 426.83 1205.49 0.43 2.05 1.78 7.43

 MEAN 15.50 518.56 283.98 433.89 1201.33 0.43 2.13 1.86 5.75

 HUB 12.59 553.20 333.54 441.34 1197.33 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 591.17 525.02 305.71 0.44 5123.67 0.92 0.91

 MEAN 510.68 489.55 226.70 0.41 4403.32 0.92 0.91 0.91 1.51

 HUB 414.87 448.77 81.33 0.37 4201.16 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.51 1.16 9.29 634.40 1.04 613.24 527.63 0.09

 MEAN 10.30 1.13 9.08 630.59 1.04 609.01 526.39 0.10

 HUB 10.25 1.13 8.87 629.52 1.04 604.96 526.06 0.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.77 35.61 31.50 4.11 0.93 0.42 1.40

 MEAN 33.20 27.59 23.50 4.09 0.93 0.40 1.64

 HUB 37.08 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 578.1240 289.1872 500.5977 1196.9994 0.4830 -0.2021 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3287 8.8234 604.6865 526.6730 0.1095 30.0143 33.0000 2.9857

 

NASA/TM—2013-218094 J–137
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 506.3702 115.6301 492.9914 1203.1648 0.4209 0.0421 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3019 9.1348 610.9299 526.5682 410.5396 0.0410 0.3328

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 490.3647 0.0000 490.3647 1204.3934 0.4071 0.2543 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2061 612.2105 526.5680 0.0000 0.0600 0.0397 0.0982

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8798 10.3037 1.1333 631.5030 24.2054 257.6471 1.9973

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 150843.969 0.432 483.477 532360.563 0.258052E-03

 

Melt Ratio at Stator LE, Throat, TE

0.98128E-01 0.10800E+00 0.13515E+00

 trTOT = 1.3214 Tt4 = 631.5030 T1 = 477.9164

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 955983.50 3064.0667 187.6611 2.4161 0.8570 4.3898 1.3214 37.3740

NASA/TM—2013-218094 J–138
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.722 EfDer = 0.996 SH = 0.121507E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.773 3744.245 4.265 477.916 1.000 1.000 0.980

 W Kg/sec = 25.352 Wdry = 55.767 WH2O = 0.007 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 184.538 3900.718 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 151361.219 43760.555 1.539 831.557 540.187 619.754 1.147

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 436.85 -0.15 436.85 0.42 0.77 702.23

 MEAN 17.06 0.00 -0.02 436.85 -0.15 436.85 0.42 0.68

 HUB 12.51 0.00 -0.02 436.85 -0.15 436.85 0.42 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.06 50.47 6.59 674.08 803.38 3.79 462.57 460.95 2.94

 MEAN 51.92 47.20 4.72 557.44 708.34 3.79 462.57 460.95 2.94

 HUB 43.11 38.62 4.49 408.76 598.37 3.79 462.57 460.95 2.94

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 673.75 365.69 565.86 1068.05 0.63 7.29 6.52 16.04

 MEAN 18.04 711.88 411.19 581.11 1062.57 0.67 7.43 6.80 12.53

 HUB 15.00 825.46 551.21 614.46 1051.84 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 674.08 644.44 308.39 0.60 7547.33 0.92 0.91

 MEAN 589.32 607.80 178.13 0.57 7418.89 0.92 0.91 0.91 1.29

 HUB 490.12 617.49 61.09 0.59 8270.00 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.26 517.58 1.08 481.07 482.95 1.59

 MEAN 5.53 1.30 4.11 516.90 1.08 476.15 482.76 1.90

 HUB 5.69 1.33 3.81 521.38 1.09 466.58 485.49 2.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.87 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 35.28 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 41.89 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 757.0659 410.3964 636.1788 1058.5216 0.7152 -0.0826 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5756 3.9800 472.5304 483.7579 2.1895 32.8259 35.4000 2.5741

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 601.9114 147.2459 583.6231 1077.3376 0.5587 0.2868 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5452 4.4975 489.4874 483.1570 554.9116 0.0298 0.4035

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 598.2971 0.0000 598.2971 1077.6981 0.5552 0.3188 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4887 489.8392 483.1021 0.0000 0.0600 0.0461 0.2811

NASA/TM—2013-218094 J–139
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8669 5.5202 1.2944 518.6196 40.7047 225.1278 1.7452

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 253120.641 0.557 797.788 606836.563 0.141021E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.661 EfDer = 0.999 SH = 0.161816E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.773 3744.245 5.520 518.619 1.000 1.000 0.980

 W Kg/sec = 25.352 Wdry = 55.764 WH2O = 0.009 lbm/sec H2O = 0.066g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 148.511 3744.535 1.381 0.248 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 131079.484 43759.863 1.358 590.487 434.746 468.502 1.078 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 532.76 -0.18 532.76 0.49 0.79 671.50

 MEAN 18.08 0.00 -0.02 532.76 -0.18 532.76 0.49 0.73

 HUB 15.21 0.00 -0.02 532.76 -0.18 532.76 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.58 46.36 5.22 671.47 857.29 4.69 495.80 483.06 1.17

 MEAN 47.96 42.30 5.66 590.70 795.60 4.69 495.80 483.06 1.17

 HUB 43.02 37.84 5.18 496.98 728.71 4.69 495.80 483.06 1.17

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 602.80 292.96 526.83 1111.28 0.54 2.33 2.04 9.02

 MEAN 18.01 619.43 310.08 536.24 1107.30 0.56 2.40 2.13 7.35

 HUB 15.22 675.20 396.74 546.34 1103.63 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.22 646.23 374.26 0.58 5986.04 0.92 0.91

 MEAN 588.47 604.20 278.39 0.55 5587.77 0.92 0.91 0.91 1.42

 HUB 497.41 555.54 100.67 0.50 6042.36 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.51 550.07 1.06 520.85 497.23 0.55

 MEAN 6.63 1.20 5.37 547.97 1.06 517.13 496.38 0.61

 HUB 6.72 1.22 5.24 550.36 1.06 513.71 497.49 0.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.08 35.39 31.50 3.89 0.93 0.37 1.40

 MEAN 30.04 27.44 23.50 3.94 0.92 0.36 1.63

 HUB 35.99 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 694.8465 310.9462 621.3889 1100.3154 0.6315 -0.1931 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6742 5.1183 510.6603 497.1315 0.7418 26.5836 30.6000 4.0164

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 585.9120 124.2175 572.5931 1112.3368 0.5267 0.1101 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6499 5.5173 521.8734 496.8602 491.5697 0.0285 0.2763

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 614.3751 0.0000 614.3751 1109.3845 0.5538 0.1776 0.5911

NASA/TM—2013-218094 J–140
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3946 519.1302 496.8543 0.0000 0.0600 0.0456 0.0167

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8698 6.6274 1.2006 549.4665 30.8486 257.8339 1.9987

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191922.359 0.431 604.903 546024.750 0.170123E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.915 EfDer = 0.999 SH = 0.182949E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.773 3744.245 6.627 549.466 1.000 1.000 0.980

 W Kg/sec = 25.352 Wdry = 55.763 WH2O = 0.010 lbm/sec H2O = 0.087g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 127.325 3637.909 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 113283.359 43759.500 1.463 545.479 372.749 424.468 1.139

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 498.42 -0.17 498.42 0.44 0.74 637.14

 MEAN 17.74 0.00 -0.02 498.42 -0.17 498.42 0.44 0.68

 HUB 15.05 0.00 -0.02 498.42 -0.17 498.42 0.44 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.77 46.36 6.41 655.78 823.83 5.80 529.50 496.74 0.47

 MEAN 49.31 43.40 5.91 579.60 764.57 5.80 529.50 496.74 0.47

 HUB 44.62 38.84 5.78 491.75 700.30 5.80 529.50 496.74 0.47

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 577.30 293.22 497.28 1145.19 0.50 2.26 1.98 8.75

 MEAN 17.51 592.06 308.93 505.07 1141.57 0.52 2.34 2.07 6.78

 HUB 14.85 644.60 389.66 513.48 1138.21 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.29 610.45 354.06 0.53 5812.22 0.92 0.91

 MEAN 572.02 569.49 263.09 0.50 5411.39 0.92 0.91 0.91 1.45

 HUB 485.22 522.30 95.55 0.46 5789.11 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.68 579.99 1.06 553.21 508.93 0.26

 MEAN 7.84 1.18 6.54 577.88 1.05 549.71 508.15 0.28

 HUB 7.93 1.20 6.39 579.87 1.06 546.48 508.96 0.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.53 35.45 31.50 3.95 0.93 0.39 1.40

 MEAN 31.45 27.51 23.50 4.01 0.92 0.38 1.62

 HUB 37.19 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 657.6006 310.9596 579.4331 1136.1034 0.5788 -0.1745 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8837 6.3001 544.5031 508.7184 0.3234 28.2208 31.5000 3.2792

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 558.9899 121.9399 545.5276 1146.1198 0.4877 0.1170 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8634 6.6965 554.1405 508.5515 451.3937 0.0250 0.3020

 

NASA/TM—2013-218094 J–141
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 570.8267 0.0000 570.8267 1144.9803 0.4985 0.2096 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6320 553.0688 508.5189 0.0000 0.0600 0.0403 0.0696

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8769 7.8426 1.1833 579.2444 29.7799 246.0323 1.9072

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 185357.766 0.442 584.213 521307.750 0.194417E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.313 EfDer = 1.000 SH = 0.214165E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.773 3744.245 7.843 579.244 1.000 1.000 0.980

 W Kg/sec = 25.352 Wdry = 55.762 WH2O = 0.012 lbm/sec H2O = 0.116g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.474 3543.166 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99152.281 43758.965 1.587 513.330 323.443 395.845 1.224

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 463.57 -0.16 463.57 0.40 0.68 595.50

 MEAN 16.97 0.00 -0.02 463.57 -0.16 463.57 0.40 0.63

 HUB 14.32 0.00 -0.02 463.57 -0.16 463.57 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.63 46.36 7.27 629.31 781.75 7.03 561.98 508.47 0.24

 MEAN 50.11 43.80 6.31 554.51 722.88 7.03 561.98 508.47 0.24

 HUB 45.28 37.84 7.44 467.90 658.77 7.03 561.98 508.47 0.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 545.78 285.75 465.00 1176.18 0.46 2.16 1.89 8.34

 MEAN 16.57 557.05 295.88 471.97 1172.57 0.48 2.24 1.97 6.35

 HUB 13.89 602.67 365.14 479.46 1169.16 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 616.90 570.86 331.14 0.49 5398.11 0.92 0.91

 MEAN 541.55 532.08 245.67 0.45 4906.59 0.92 0.91 0.91 1.47

 HUB 453.85 487.59 88.71 0.42 5074.10 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.19 1.17 7.95 607.58 1.05 583.65 518.80 0.15

 MEAN 9.06 1.16 7.78 605.00 1.04 580.07 517.90 0.16

 HUB 9.11 1.16 7.61 605.88 1.05 576.70 518.25 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.57 35.46 31.50 3.96 0.93 0.40 1.40

 MEAN 32.08 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.29 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 601.8807 297.5440 523.1902 1169.4647 0.5147 -0.1204 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1066 7.6188 577.0612 518.3168 0.1741 29.6274 32.4000 2.7726

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 518.0281 116.1786 504.8324 1177.0787 0.4401 0.1437 2.2705

 

NASA/TM—2013-218094 J–142
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0910 7.9724 584.6011 518.2144 432.2457 0.0216 0.3246

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 513.7876 0.0000 513.7876 1177.4027 0.4364 0.2355 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9691 584.9543 518.1616 0.0000 0.0600 0.0392 0.1412

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8787 9.0674 1.1562 606.1470 26.9052 248.2776 1.9246

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 167561.500 0.440 528.122 515061.188 0.229554E-03

 

Melt Ratio at Stator LE, Throat, TE

0.12663E-01 0.19518E-01 0.36893E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.634 EfDer = 1.000 SH = 0.250323E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.773 3744.245 9.067 606.146 1.000 1.000 0.980

 W Kg/sec = 25.352 Wdry = 55.760 WH2O = 0.014 lbm/sec H2O = 0.153g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.744 3463.645 1.380 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 88063.000 43758.344 1.781 509.668 286.200 384.739 1.344

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 414.68 -0.14 414.68 0.35 0.61 553.72

 MEAN 15.91 0.00 -0.02 414.68 -0.14 414.68 0.35 0.56

 HUB 13.07 0.00 -0.02 414.68 -0.14 414.68 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.29 47.36 7.93 598.60 728.32 8.34 592.34 518.14 0.14

 MEAN 51.43 44.80 6.63 519.95 665.18 8.34 592.34 518.14 0.14

 HUB 45.85 38.84 7.01 427.06 595.37 8.34 592.34 518.14 0.14

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 507.63 285.86 419.49 1204.64 0.42 2.05 1.78 7.43

 MEAN 15.50 512.15 283.69 426.40 1200.50 0.43 2.13 1.86 5.75

 HUB 12.59 545.89 331.53 433.68 1196.51 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 586.18 515.92 300.32 0.43 5130.97 0.92 0.91

 MEAN 506.38 481.04 222.69 0.40 4398.82 0.92 0.91 0.91 1.52

 HUB 411.37 440.97 79.84 0.37 4175.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.48 1.16 9.29 633.06 1.04 612.37 527.28 0.10

 MEAN 10.27 1.13 9.07 629.22 1.04 608.16 526.02 0.10

 HUB 10.20 1.13 8.86 628.05 1.04 604.13 525.66 0.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.27 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.64 27.58 23.50 4.08 0.93 0.41 1.64

 HUB 37.40 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 570.1560 288.8942 491.5465 1196.3442 0.4766 -0.1992 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2907 8.8267 604.0222 526.3030 0.1136 30.4438 33.0000 2.5562

 

NASA/TM—2013-218094 J–143
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 497.0560 113.5032 483.9232 1202.5277 0.4133 0.0540 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2663 9.1415 610.2814 526.2027 410.5396 0.0397 0.3388

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 481.4974 0.0000 481.4974 1203.6995 0.4000 0.2612 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2091 611.5035 526.2010 0.0000 0.0600 0.0388 0.1085

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8811 10.2673 1.1323 630.1045 23.9620 255.0995 1.9775

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 149327.156 0.435 470.651 523122.063 0.263244E-03

 

Melt Ratio at Stator LE, Throat, TE

0.10051E+00 0.11047E+00 0.13778E+00

 trTOT = 1.3184 Tt4 = 630.1045 T1 = 477.9162

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 947289.38 2985.6772 184.5384 2.4076 0.8610 4.7224 1.3184 37.3740

NASA/TM—2013-218094 J–144
 50μm, ISA +18R 

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.825 EfDer = 0.984 SH = 0.470373E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.104 3888.739 4.265 457.738 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.101 WH2O = 0.003 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.333 4139.589 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 168217.859 49513.680 1.390 831.557 598.101 619.754 1.036

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 485.50 -0.17 485.50 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 485.50 -0.17 485.50 0.48 0.74

 HUB 12.51 0.00 -0.02 485.50 -0.17 485.50 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.27 50.47 4.80 700.09 852.10 3.66 438.78 448.40 3.54

 MEAN 50.03 47.20 2.83 578.95 755.70 3.66 438.78 448.40 3.54

 HUB 41.18 38.62 2.56 424.53 645.05 3.66 438.78 448.40 3.54

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 728.14 352.66 637.04 1038.53 0.70 7.29 6.52 16.04

 MEAN 18.04 773.28 411.15 654.92 1033.16 0.75 7.43 6.80 12.53

 HUB 15.00 914.41 580.07 706.87 1019.13 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.09 725.62 347.43 0.70 7278.91 0.92 0.90

 MEAN 612.06 685.04 200.91 0.66 7418.39 0.92 0.90 0.90 1.21

 HUB 509.03 710.43 71.03 0.70 8703.07 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 497.48 1.09 454.83 473.93 1.78

 MEAN 5.63 1.32 3.90 498.24 1.09 450.14 474.48 2.15

 HUB 5.89 1.38 3.51 505.25 1.10 437.99 478.98 3.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.97 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.12 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.37 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 836.5598 410.3527 729.0013 1026.1261 0.8153 -0.1085 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6891 3.6925 444.0272 475.8420 2.7746 29.3750 35.4000 6.0250

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 681.9921 166.8361 661.2708 1047.7100 0.6509 0.2262 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6275 4.2470 462.9096 475.2237 554.9116 0.0426 0.3573

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 684.4077 0.0000 684.4077 1047.3927 0.6534 0.2507 1.3089

NASA/TM—2013-218094 J–145
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.1930 462.6477 475.0965 0.0000 0.0600 0.0744 0.1977

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8211 5.5676 1.3055 500.3225 42.5850 238.3406 1.8476

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 264727.969 0.540 944.038 727627.125 0.480804E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.416 EfDer = 0.989 SH = 0.488788E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.104 3888.739 5.568 500.322 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.101 WH2O = 0.003 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.635 3959.514 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 147267.531 49513.645 1.233 590.487 478.983 468.502 0.978

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 598.56 -0.21 598.56 0.57 0.87 710.05

 MEAN 18.08 0.00 -0.02 598.56 -0.21 598.56 0.57 0.81

 HUB 15.21 0.00 -0.02 598.56 -0.21 598.56 0.57 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.37 46.36 3.01 697.38 919.18 4.49 471.51 474.98 0.94

 MEAN 45.72 42.30 3.42 613.50 857.27 4.49 471.51 474.98 0.94

 HUB 40.78 37.84 2.94 516.16 790.51 4.49 471.51 474.98 0.94

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 648.42 273.77 587.79 1085.62 0.60 2.33 2.04 9.02

 MEAN 18.01 668.23 299.55 597.34 1082.16 0.62 2.40 2.13 7.35

 HUB 15.22 729.50 403.24 607.92 1079.05 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 692.97 721.95 419.19 0.67 5594.72 0.92 0.90

 MEAN 611.18 673.74 311.63 0.62 5398.56 0.92 0.90 0.90 1.37

 HUB 516.60 618.40 113.36 0.57 6141.72 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.21 5.33 530.86 1.06 497.05 490.43 0.38

 MEAN 6.72 1.21 5.21 529.79 1.06 493.88 489.95 0.42

 HUB 6.89 1.24 5.09 533.85 1.07 491.05 491.90 0.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 24.97 35.50 31.50 4.00 0.93 0.32 1.40

 MEAN 26.63 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.56 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 767.1357 300.3882 705.8783 1071.4468 0.7160 -0.2389 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7754 4.8331 484.1755 490.8363 0.5853 23.0523 30.6000 7.5477

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 663.8070 140.7318 648.7174 1084.5320 0.6121 0.0169 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7240 5.2371 496.0635 490.5897 491.5697 0.0425 0.2182

 

NASA/TM—2013-218094 J–146
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 707.5146 0.0000 707.5146 1079.2352 0.6556 0.0937 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0150 491.2467 490.5086 0.0000 0.0600 0.0762 -0.1235

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8212 6.6708 1.1981 531.4995 31.1778 281.6879 2.1836

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193878.422 0.404 691.384 658794.688 0.490935E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.774 EfDer = 0.991 SH = 0.491262E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.104 3888.739 6.671 531.499 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.101 WH2O = 0.003 lbm/sec H2O = 0.024g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.764 3841.629 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126849.648 49513.637 1.324 545.479 412.051 424.468 1.030 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 558.11 -0.19 558.11 0.51 0.80 672.82

 MEAN 17.74 0.00 -0.02 558.11 -0.19 558.11 0.51 0.75

 HUB 15.05 0.00 -0.02 558.11 -0.19 558.11 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.68 46.36 4.32 681.09 880.70 5.60 506.45 490.39 0.28

 MEAN 47.17 43.40 3.77 601.97 821.03 5.60 506.45 490.39 0.28

 HUB 42.47 38.84 3.63 510.73 756.66 5.60 506.45 490.39 0.28

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 618.95 276.67 553.67 1121.64 0.55 2.26 1.98 8.75

 MEAN 17.51 636.89 300.24 561.68 1118.42 0.57 2.34 2.07 6.78

 HUB 14.85 694.89 396.63 570.57 1115.50 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.27 680.47 395.59 0.61 5484.76 0.92 0.91

 MEAN 594.10 633.91 293.86 0.57 5259.58 0.92 0.91 0.91 1.39

 HUB 503.94 580.57 107.31 0.52 5892.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.99 1.20 6.51 561.43 1.06 530.63 503.50 0.14

 MEAN 7.93 1.19 6.38 560.20 1.05 527.59 503.00 0.15

 HUB 8.10 1.21 6.25 563.66 1.06 524.83 504.45 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.55 35.55 31.50 4.05 0.93 0.34 1.40

 MEAN 28.13 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.81 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 719.0605 302.2104 652.4699 1110.5226 0.6475 -0.2068 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9895 6.0471 520.1974 503.6555 0.1837 24.8526 31.5000 6.6474

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 629.5907 137.3410 614.4281 1120.8384 0.5617 0.0308 2.3726

 

NASA/TM—2013-218094 J–147
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9479 6.4321 529.8958 503.5070 451.3937 0.0356 0.2513

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 647.0823 0.0000 647.0823 1118.9177 0.5783 0.1405 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3200 528.1037 503.4174 0.0000 0.0600 0.0614 -0.0382

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8430 7.9060 1.1852 561.7626 30.2641 267.2670 2.0718

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188255.766 0.417 671.333 622580.813 0.493694E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.349 EfDer = 0.994 SH = 0.496608E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.104 3888.739 7.906 561.762 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.101 WH2O = 0.003 lbm/sec H2O = 0.027g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.106 3736.719 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110367.977 49513.625 1.436 513.330 357.452 395.845 1.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 516.01 -0.18 516.01 0.46 0.74 628.03

 MEAN 16.97 0.00 -0.02 516.01 -0.18 516.01 0.46 0.68

 HUB 14.32 0.00 -0.02 516.01 -0.18 516.01 0.46 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.72 46.36 5.36 653.60 832.88 6.87 540.36 503.37 0.11

 MEAN 48.15 43.80 4.35 575.91 773.40 6.87 540.36 503.37 0.11

 HUB 43.29 37.84 5.45 485.96 708.94 6.87 540.36 503.37 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 582.72 272.89 514.87 1154.85 0.50 2.16 1.89 8.34

 MEAN 16.57 597.23 289.52 522.37 1151.45 0.52 2.24 1.97 6.35

 HUB 13.89 648.14 372.34 530.52 1148.29 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.70 632.76 367.81 0.55 5155.60 0.92 0.91

 MEAN 562.45 589.37 272.93 0.51 4801.41 0.92 0.91 0.91 1.42

 HUB 471.37 539.68 99.02 0.47 5174.37 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.29 1.18 7.83 589.89 1.05 562.59 514.41 0.06

 MEAN 9.19 1.16 7.67 587.95 1.05 559.29 513.68 0.07

 HUB 9.30 1.18 7.51 589.99 1.05 556.22 514.46 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.92 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.00 27.59 23.50 4.09 0.92 0.35 1.62

 HUB 35.06 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 651.2233 291.1436 582.5179 1147.1838 0.5677 -0.1379 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2433 7.4481 555.1974 514.1618 0.0721 26.5560 32.4000 5.8440

 

NASA/TM—2013-218094 J–148
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 577.6968 129.5605 562.9811 1154.6641 0.5003 0.0718 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2127 7.7814 562.4577 514.0717 432.2457 0.0292 0.2811

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 573.1284 0.0000 573.1284 1155.0750 0.4962 0.1833 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7772 562.8824 514.0033 0.0000 0.0600 0.0481 0.0691

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8607 9.1826 1.1615 589.2754 27.5144 267.6786 2.0750

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171222.063 0.417 610.590 609604.375 0.500520E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 4.946 EfDer = 0.997 SH = 0.507613E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.104 3888.739 9.183 589.275 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.101 WH2O = 0.003 lbm/sec H2O = 0.032g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.674 3648.445 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 97123.633 49513.605 1.617 509.668 315.222 384.739 1.221

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 457.35 -0.16 457.35 0.39 0.66 583.27

 MEAN 15.91 0.00 -0.02 457.35 -0.16 457.35 0.39 0.61

 HUB 13.07 0.00 -0.02 457.35 -0.16 457.35 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.67 47.36 6.31 621.70 771.93 8.27 572.47 513.98 0.05

 MEAN 49.75 44.80 4.95 540.02 707.78 8.27 572.47 513.98 0.05

 HUB 44.13 38.84 5.29 443.54 637.21 8.27 572.47 513.98 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 537.84 278.44 460.16 1185.82 0.45 2.05 1.78 7.43

 MEAN 15.50 545.75 280.72 468.01 1181.61 0.46 2.13 1.86 5.75

 HUB 12.59 584.60 338.94 476.32 1177.61 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.81 566.47 330.37 0.48 4998.01 0.92 0.91

 MEAN 525.92 528.36 245.20 0.45 4353.04 0.92 0.91 0.91 1.47

 HUB 427.25 484.44 88.31 0.41 4269.25 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.67 1.16 9.28 616.53 1.05 593.29 523.83 0.03

 MEAN 10.47 1.14 9.06 613.01 1.04 589.08 522.60 0.03

 HUB 10.44 1.14 8.84 612.55 1.04 585.10 522.45 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.18 35.68 31.50 4.18 0.93 0.39 1.40

 MEAN 30.96 27.65 23.50 4.15 0.92 0.37 1.64

 HUB 35.43 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 613.5391 285.8705 542.8705 1176.2482 0.5216 -0.2187 2.0437

 

NASA/TM—2013-218094 J–149
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4949 8.7387 583.7950 522.9138 0.0379 27.7709 33.0000 5.2291

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 550.4341 125.6921 535.8910 1182.1819 0.4656 -0.0246 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4491 9.0237 589.6935 522.8042 410.5396 0.0512 0.3017

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 531.8278 0.0000 531.8278 1183.7786 0.4493 0.2175 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1208 591.3127 522.8184 0.0000 0.0600 0.0458 0.0417

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8685 10.4570 1.1388 614.0280 24.7545 271.7217 2.1064

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154122.766 0.416 549.613 613687.750 0.514635E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3414 Tt4 = 614.0280 T1 = 457.7381

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 972206.94 3466.9580 204.3327 2.4520 0.8224 2.8251 1.3414 37.3740

NASA/TM—2013-218094 J–150
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.055 EfDer = 0.993 SH = 0.473126E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl 

 58.952 3728.441 4.265 457.738 1.000 1.000 0.980

 W Kg/sec = 26.796 Wdry = 58.950 WH2O = 0.003 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 190.889 3968.951 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154375.625 46256.027 1.488 831.557 558.751 619.754 1.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.55 -0.15 445.55 0.44 0.79 714.51

 MEAN 17.06 0.00 -0.02 445.55 -0.15 445.55 0.44 0.70

 HUB 12.51 0.00 -0.02 445.55 -0.15 445.55 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.43 50.47 5.96 671.23 805.78 3.75 441.77 448.35 3.13

 MEAN 51.25 47.20 4.05 555.08 711.90 3.75 441.77 448.35 3.13

 HUB 42.42 38.62 3.80 407.04 603.59 3.75 441.77 448.35 3.13

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 679.64 355.42 579.30 1043.25 0.65 7.29 6.52 16.04

 MEAN 18.04 719.41 404.37 595.00 1037.92 0.69 7.43 6.80 12.53

 HUB 15.00 838.62 551.01 632.20 1026.59 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 671.23 659.79 315.82 0.63 7335.40 0.92 0.91

 MEAN 586.83 622.35 182.46 0.60 7295.85 0.92 0.91 0.91 1.26

 HUB 488.05 635.32 62.96 0.62 8267.11 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.20 496.13 1.08 458.98 473.10 1.53

 MEAN 5.56 1.30 4.04 495.93 1.08 454.30 473.07 1.84

 HUB 5.75 1.35 3.72 501.01 1.09 444.44 476.30 2.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.53 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.20 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.07 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 768.5444 403.5849 654.0488 1033.2013 0.7438 -0.0897 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6060 3.8981 450.1786 474.1646 2.1717 31.6769 35.4000 3.7231

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 617.0828 150.9573 598.3336 1052.3896 0.5864 0.2667 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5685 4.4243 467.0610 473.7608 554.9116 0.0329 0.3882

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 614.4775 0.0000 614.4775 1052.6631 0.5837 0.2980 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4070 467.3217 473.6884 0.0000 0.0600 0.0530 0.2561

NASA/TM—2013-218094 J–151
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8557 5.5358 1.2981 497.6898 39.9529 229.6347 1.7801

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 248376.016 0.551 827.452 667752.563 0.486384E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.909 EfDer = 0.997 SH = 0.496737E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.952 3728.441 5.536 497.690 1.000 1.000 0.980

 W Kg/sec = 26.796 Wdry = 58.949 WH2O = 0.003 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 153.342 3806.326 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 134013.641 46255.984 1.316 590.487 448.855 468.502 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 544.69 -0.19 544.69 0.51 0.81 682.58

 MEAN 18.08 0.00 -0.02 544.69 -0.19 544.69 0.51 0.76

 HUB 15.21 0.00 -0.02 544.69 -0.19 544.69 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.84 46.36 4.48 668.63 862.56 4.63 473.83 473.62 0.89

 MEAN 47.21 42.30 4.91 588.21 801.81 4.63 473.83 473.62 0.89

 HUB 42.27 37.84 4.43 494.88 736.06 4.63 473.83 473.62 0.89

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 607.11 282.01 537.63 1086.88 0.56 2.33 2.04 9.02

 MEAN 18.01 624.61 301.60 546.97 1083.11 0.58 2.40 2.13 7.35

 HUB 15.22 681.32 392.28 557.06 1079.68 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 664.40 659.75 382.39 0.61 5762.50 0.92 0.91

 MEAN 585.99 616.49 284.39 0.57 5435.10 0.92 0.91 0.91 1.40

 HUB 495.31 566.51 103.03 0.52 5974.48 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.46 527.85 1.06 498.20 489.19 0.38

 MEAN 6.65 1.20 5.33 526.13 1.06 494.76 488.38 0.43

 HUB 6.77 1.22 5.20 528.96 1.06 491.62 489.78 0.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.68 35.42 31.50 3.92 0.93 0.35 1.40

 MEAN 28.87 27.47 23.50 3.97 0.92 0.35 1.63

 HUB 35.15 10.48 6.50 3.98 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 705.1759 302.4415 637.0261 1075.2897 0.6558 -0.2058 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7041 5.0392 487.6581 489.1562 0.5373 25.3970 30.6000 5.2030

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 600.3012 127.2681 586.6552 1087.3658 0.5521 0.0808 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6733 5.4385 498.6666 488.9868 491.5697 0.0321 0.2579

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 631.7528 0.0000 631.7528 1083.9471 0.5828 0.1524 0.5911

NASA/TM—2013-218094 J–152
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2929 495.5530 488.9429 0.0000 0.0600 0.0533 -0.0237

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8583 6.6439 1.2002 527.6454 29.9565 265.4713 2.0579

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186287.219 0.422 620.606 601609.000 0.499595E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.204 EfDer = 0.998 SH = 0.501570E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.952 3728.441 6.644 527.645 1.000 1.000 0.980

 W Kg/sec = 26.796 Wdry = 58.949 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 131.556 3696.701 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115667.359 46255.977 1.416 545.479 385.096 424.468 1.102

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 508.91 -0.18 508.91 0.46 0.76 647.44

 MEAN 17.74 0.00 -0.02 508.91 -0.18 508.91 0.46 0.70

 HUB 15.05 0.00 -0.02 508.91 -0.18 508.91 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.08 46.36 5.72 653.01 828.04 5.74 506.82 488.87 0.29

 MEAN 48.60 43.40 5.20 577.15 769.61 5.74 506.82 488.87 0.29

 HUB 43.91 38.84 5.07 489.68 706.36 5.74 506.82 488.87 0.29

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 580.70 283.22 506.94 1120.87 0.52 2.26 1.98 8.75

 MEAN 17.51 596.33 301.15 514.70 1117.43 0.53 2.34 2.07 6.78

 HUB 14.85 649.83 385.51 523.13 1114.25 0.58 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 644.55 622.54 361.33 0.56 5614.18 0.92 0.91

 MEAN 569.61 580.51 268.45 0.52 5275.24 0.92 0.91 0.91 1.43

 HUB 483.17 532.17 97.66 0.48 5727.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.95 1.20 6.64 557.02 1.06 529.91 502.04 0.15

 MEAN 7.87 1.18 6.50 555.25 1.05 526.65 501.29 0.16

 HUB 7.98 1.20 6.35 557.61 1.06 523.66 502.32 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.19 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.33 27.55 23.50 4.05 0.92 0.37 1.62

 HUB 36.39 10.57 6.50 4.07 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 665.4915 303.1279 592.4461 1111.4019 0.5988 -0.1839 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9179 6.2315 521.0225 501.8815 0.1879 27.0968 31.5000 4.4032

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 571.5968 124.6900 557.8309 1121.3226 0.5098 0.0897 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8925 6.6244 530.3593 501.7773 451.3937 0.0277 0.2857

 

NASA/TM—2013-218094 J–153
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 584.4047 0.0000 584.4047 1120.0428 0.5218 0.1893 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5507 529.1714 501.7275 0.0000 0.0600 0.0445 0.0384

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8701 7.8684 1.1843 556.6248 28.9805 252.7778 1.9595

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180272.391 0.434 600.568 572629.563 0.504999E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.666 EfDer = 0.999 SH = 0.510548E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.952 3728.441 7.868 556.625 1.000 1.000 0.980

 W Kg/sec = 26.796 Wdry = 58.949 WH2O = 0.003 lbm/sec H2O = 0.029g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.092 3599.184 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 101021.844 46255.961 1.537 513.330 333.992 395.845 1.185

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 472.31 -0.16 472.31 0.42 0.69 604.92

 MEAN 16.97 0.00 -0.02 472.31 -0.16 472.31 0.42 0.64

 HUB 14.32 0.00 -0.02 472.31 -0.16 472.31 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.00 46.36 6.64 626.66 784.85 6.99 538.69 501.69 0.12

 MEAN 49.47 43.80 5.67 552.17 726.74 6.99 538.69 501.69 0.12

 HUB 44.62 37.84 6.78 465.93 663.57 6.99 538.69 501.69 0.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 548.24 277.09 473.06 1152.02 0.48 2.16 1.89 8.34

 MEAN 16.57 560.40 289.07 480.09 1148.53 0.49 2.24 1.97 6.35

 HUB 13.89 607.01 361.47 487.65 1145.25 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 614.29 580.94 337.21 0.50 5234.58 0.92 0.91

 MEAN 539.26 541.37 250.19 0.47 4793.80 0.92 0.91 0.91 1.45

 HUB 451.94 495.97 90.46 0.43 5023.20 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.23 1.17 7.92 584.00 1.05 559.84 512.71 0.07

 MEAN 9.11 1.16 7.75 581.70 1.05 556.46 511.83 0.07

 HUB 9.17 1.17 7.59 582.90 1.05 553.28 512.30 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.36 35.48 31.50 3.98 0.93 0.38 1.40

 MEAN 31.05 27.53 23.50 4.03 0.92 0.38 1.62

 HUB 36.55 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 607.1664 290.6972 533.0536 1145.1653 0.5302 -0.1256 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1540 7.5769 553.2408 512.2585 0.0803 28.6055 32.4000 3.7945

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 528.0408 118.4241 514.5899 1152.6117 0.4581 0.1206 2.2705

 

NASA/TM—2013-218094 J–154
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1348 7.9248 560.4587 512.1949 432.2457 0.0236 0.3100

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 523.7514 0.0000 523.7514 1152.9614 0.4543 0.2184 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9213 560.8229 512.1381 0.0000 0.0600 0.0415 0.1181

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8745 9.1095 1.1577 582.8641 26.2410 254.4248 1.9723

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 163294.453 0.433 544.007 564279.438 0.516740E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.067 EfDer = 0.999 SH = 0.526254E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.952 3728.441 9.109 582.864 1.000 1.000 0.980

 W Kg/sec = 26.796 Wdry = 58.949 WH2O = 0.003 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 100.844 3517.238 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89486.250 46255.934 1.726 509.668 295.228 384.739 1.303

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 421.39 -0.15 421.39 0.36 0.63 562.29

 MEAN 15.91 0.00 -0.02 421.39 -0.15 421.39 0.36 0.58

 HUB 13.07 0.00 -0.02 421.39 -0.15 421.39 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.75 47.36 7.39 596.07 730.10 8.33 568.60 512.12 0.06

 MEAN 50.87 44.80 6.07 517.76 667.67 8.33 568.60 512.12 0.06

 HUB 45.27 38.84 6.43 425.26 598.78 8.33 568.60 512.12 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 508.77 278.72 425.64 1180.76 0.43 2.05 1.78 7.43

 MEAN 15.50 514.33 278.04 432.70 1176.66 0.44 2.13 1.86 5.75

 HUB 12.59 549.17 328.39 440.16 1172.74 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 583.71 523.63 304.99 0.44 5002.87 0.92 0.91

 MEAN 504.24 488.26 226.20 0.41 4311.23 0.92 0.91 0.91 1.50

 HUB 409.64 447.60 81.24 0.38 4136.39 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.54 1.16 9.29 609.02 1.04 588.22 521.82 0.04

 MEAN 10.33 1.13 9.08 605.40 1.04 584.15 520.53 0.04

 HUB 10.28 1.13 8.86 604.49 1.04 580.26 520.20 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.22 35.62 31.50 4.12 0.93 0.42 1.40

 MEAN 32.72 27.60 23.50 4.10 0.93 0.39 1.64

 HUB 36.73 10.46 6.50 3.96 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 574.3334 283.1360 499.6928 1172.2385 0.4899 -0.2053 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3582 8.8086 579.8073 520.8080 0.0443 29.5368 33.0000 3.4632

 

NASA/TM—2013-218094 J–155
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 505.6795 115.4723 492.3189 1178.2456 0.4292 0.0286 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3285 9.1150 585.7625 520.7327 410.5396 0.0427 0.3260

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 489.5190 0.0000 489.5190 1179.5205 0.4150 0.2464 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1905 587.0556 520.7363 0.0000 0.0600 0.0407 0.0864

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8780 10.3311 1.1341 606.3013 23.4390 260.5340 2.0196

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 145923.578 0.428 486.137 571701.938 0.535296E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3246 Tt4 = 606.3013 T1 = 457.7377

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 924153.63 3078.7695 190.8891 2.4225 0.8520 4.0545 1.3246 37.3740

NASA/TM—2013-218094 J–156
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.490 EfDer = 0.995 SH = 0.474081E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.631 3683.296 4.265 457.738 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.628 WH2O = 0.003 lbm/sec H2O = 0.018g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 186.611 3920.894 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 150146.031 45219.445 1.522 831.557 546.230 619.754 1.135

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 433.34 -0.15 433.34 0.42 0.77 705.86

 MEAN 17.06 0.00 -0.02 433.34 -0.15 433.34 0.42 0.68

 HUB 12.51 0.00 -0.02 433.34 -0.15 433.34 0.42 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.84 50.47 6.37 663.11 792.27 3.78 442.63 448.34 3.02

 MEAN 51.69 47.20 4.49 548.36 699.04 3.78 442.63 448.34 3.02

 HUB 42.87 38.62 4.25 402.11 591.27 3.78 442.63 448.34 3.02

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 665.74 356.75 562.08 1044.59 0.64 7.29 6.52 16.04

 MEAN 18.04 703.85 402.77 577.22 1039.25 0.68 7.43 6.80 12.53

 HUB 15.00 817.53 542.93 611.21 1028.51 0.79 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 663.11 640.15 306.35 0.61 7362.87 0.92 0.91

 MEAN 579.73 603.74 176.96 0.58 7266.88 0.92 0.91 0.91 1.28

 HUB 482.14 614.23 60.79 0.60 8145.78 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.24 495.81 1.08 460.16 472.90 1.46

 MEAN 5.54 1.30 4.09 495.31 1.08 455.46 472.70 1.76

 HUB 5.71 1.34 3.78 499.86 1.09 446.10 475.58 2.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.40 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 34.91 17.04 12.70 4.34 0.92 0.27 2.22

 HUB 41.61 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 749.6144 401.9857 632.7157 1035.0524 0.7242 -0.0849 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5839 3.9534 451.7950 473.7292 2.0408 32.4292 35.4000 2.9708

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 598.1852 146.3344 580.0101 1053.6843 0.5677 0.2797 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5514 4.4728 468.2128 473.3686 554.9116 0.0307 0.3981

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 594.8980 0.0000 594.8980 1054.0219 0.5644 0.3117 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4616 468.5306 473.3078 0.0000 0.0600 0.0482 0.2726

NASA/TM—2013-218094 J–157
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8635 5.5240 1.2953 496.9940 39.2572 226.6901 1.7573

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244053.844 0.555 794.832 649457.438 0.488015E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.396 EfDer = 0.998 SH = 0.499195E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.631 3683.296 5.524 496.994 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.628 WH2O = 0.003 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.119 3762.870 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 130148.711 45219.402 1.344 590.487 439.421 468.502 1.066

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 528.98 -0.18 528.98 0.50 0.80 674.79

 MEAN 18.08 0.00 -0.02 528.98 -0.18 528.98 0.50 0.74 

 HUB 15.21 0.00 -0.02 528.98 -0.18 528.98 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.32 46.36 4.96 660.53 846.39 4.67 474.49 473.25 0.87 

 MEAN 47.70 42.30 5.40 581.09 785.94 4.67 474.49 473.25 0.87

 HUB 42.76 37.84 4.92 488.89 720.43 4.67 474.49 473.25 0.87

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 595.39 284.76 522.88 1087.27 0.55 2.33 2.04 9.02

 MEAN 18.01 612.09 302.50 532.11 1083.43 0.56 2.40 2.13 7.35

 HUB 15.22 667.37 389.32 542.05 1079.90 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.36 641.47 371.60 0.59 5818.55 0.92 0.91

 MEAN 578.89 599.61 276.39 0.55 5451.36 0.92 0.91 0.91 1.42

 HUB 489.31 551.19 99.99 0.51 5929.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.49 527.08 1.06 498.57 488.86 0.38

 MEAN 6.63 1.20 5.35 525.18 1.06 495.05 487.96 0.43

 HUB 6.74 1.22 5.22 527.65 1.06 491.83 489.19 0.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.57 35.40 31.50 3.90 0.93 0.36 1.40

 MEAN 29.62 27.45 23.50 3.95 0.92 0.36 1.63

 HUB 35.69 10.45 6.50 3.95 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 688.0723 303.3523 617.5928 1076.2855 0.6393 -0.1973 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6807 5.0907 488.5626 488.6991 0.5258 26.1596 30.6000 4.4404

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 582.2867 123.4489 569.0502 1088.1284 0.5351 0.0998 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6544 5.4888 499.3682 488.5464 491.5697 0.0297 0.2698

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 611.2584 0.0000 611.2584 1085.0785 0.5633 0.1688 0.5911

NASA/TM—2013-218094 J–158
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3590 496.5898 488.5105 0.0000 0.0600 0.0480 0.0028

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8662 6.6298 1.2002 526.6335 29.6403 260.5113 2.0195

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184322.078 0.428 600.299 584450.125 0.502231E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.658 EfDer = 0.999 SH = 0.505524E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.631 3683.296 6.630 526.633 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.628 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 128.757 3655.447 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112454.984 45219.387 1.447 545.479 376.903 424.468 1.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 494.78 -0.17 494.78 0.45 0.74 640.21

 MEAN 17.74 0.00 -0.02 494.78 -0.17 494.78 0.45 0.69

 HUB 15.05 0.00 -0.02 494.78 -0.17 494.78 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.52 46.36 6.16 645.11 813.14 5.78 506.95 488.45 0.29

 MEAN 49.06 43.40 5.66 570.16 755.04 5.78 506.95 488.45 0.29

 HUB 44.36 38.84 5.52 483.75 692.09 5.78 506.95 488.45 0.29

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 570.00 285.27 493.48 1120.69 0.51 2.26 1.98 8.75

 MEAN 17.51 584.87 301.56 501.13 1117.19 0.52 2.34 2.07 6.78

 HUB 14.85 636.97 382.41 509.41 1113.94 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 636.75 605.86 351.48 0.54 5654.59 0.92 0.91

 MEAN 562.71 565.10 261.15 0.51 5282.22 0.92 0.91 0.91 1.44

 HUB 477.32 518.17 94.91 0.47 5681.31 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.66 555.86 1.06 529.74 501.63 0.15

 MEAN 7.84 1.18 6.52 553.94 1.05 526.43 500.81 0.16

 HUB 7.94 1.20 6.38 556.00 1.06 523.38 501.72 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.03 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 31.04 27.53 23.50 4.03 0.92 0.37 1.62

 HUB 36.90 10.55 6.50 4.05 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 650.6728 303.5342 575.5363 1111.6224 0.5853 -0.1778 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8893 6.2733 521.2296 501.3807 0.1893 27.8069 31.5000 3.6931

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 555.3069 121.1364 541.9333 1121.4427 0.4952 0.1071 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8673 6.6674 530.4743 501.2862 451.3937 0.0259 0.2960

 

NASA/TM—2013-218094 J–159
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 567.2315 0.0000 567.2315 1120.2839 0.5063 0.2025 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6006 529.4005 501.2422 0.0000 0.0600 0.0413 0.0588

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8751 7.8460 1.1834 555.2639 28.6315 248.4722 1.9261

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 178101.813 0.439 580.040 557410.500 0.509397E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.073 EfDer = 0.999 SH = 0.515200E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.631 3683.296 7.846 555.264 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.628 WH2O = 0.003 lbm/sec H2O = 0.029g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 111.716 3559.959 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98371.508 45219.371 1.570 513.330 327.036 395.845 1.210

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 459.92 -0.16 459.92 0.41 0.68 598.32

 MEAN 16.97 0.00 -0.02 459.92 -0.16 459.92 0.41 0.63

 HUB 14.32 0.00 -0.02 459.92 -0.16 459.92 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.40 46.36 7.04 619.07 771.34 7.01 538.26 501.21 0.12

 MEAN 49.87 43.80 6.07 545.49 713.62 7.01 538.26 501.21 0.12

 HUB 45.03 37.84 7.19 460.29 650.80 7.01 538.26 501.21 0.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 538.66 278.32 461.19 1151.27 0.47 2.16 1.89 8.34

 MEAN 16.57 550.10 289.00 468.06 1147.76 0.48 2.24 1.97 6.35

 HUB 13.89 595.42 358.43 475.45 1144.45 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 606.86 566.24 328.54 0.49 5257.68 0.92 0.91

 MEAN 532.73 527.72 243.73 0.46 4792.57 0.92 0.91 0.91 1.47

 HUB 446.46 483.53 88.04 0.42 4980.80 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.19 1.17 7.93 582.43 1.05 559.11 512.21 0.07

 MEAN 9.07 1.16 7.77 580.03 1.04 555.70 511.28 0.08

 HUB 9.12 1.16 7.60 581.00 1.05 552.50 511.67 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.11 35.47 31.50 3.97 0.93 0.39 1.40

 MEAN 31.69 27.51 23.50 4.01 0.93 0.38 1.62

 HUB 37.01 10.49 6.50 3.99 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 594.9504 290.6271 519.1357 1144.6138 0.5198 -0.1223 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1143 7.5984 552.7067 511.7034 0.0826 29.2414 32.4000 3.1586

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 514.1414 115.3069 501.0446 1152.0466 0.4463 0.1350 2.2705

 

NASA/TM—2013-218094 J–160
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0975 7.9488 559.9086 511.6454 432.2457 0.0223 0.3190

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 509.9442 0.0000 509.9442 1152.3789 0.4425 0.2290 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9455 560.2556 511.5914 0.0000 0.0600 0.0400 0.1325

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8774 9.0734 1.1564 581.1501 25.8879 250.5591 1.9423

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161096.359 0.437 524.657 550254.938 0.521801E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.415 EfDer = 1.000 SH = 0.532872E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.631 3683.296 9.073 581.150 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.628 WH2O = 0.003 lbm/sec H2O = 0.034g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 98.831 3479.770 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 87310.016 45219.340 1.762 509.668 289.333 384.739 1.330

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 411.14 -0.14 411.14 0.35 0.62 556.30

 MEAN 15.91 0.00 -0.02 411.14 -0.14 411.14 0.35 0.57

 HUB 13.07 0.00 -0.02 411.14 -0.14 411.14 0.35 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.08 47.36 7.72 588.86 718.30 8.33 567.57 511.58 0.06

 MEAN 51.22 44.80 6.42 511.49 656.35 8.33 567.57 511.58 0.06

 HUB 45.63 38.84 6.79 420.11 587.91 8.33 567.57 511.58 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.64 278.89 415.76 1179.40 0.42 2.05 1.78 7.43

 MEAN 15.50 505.49 277.35 422.61 1175.34 0.43 2.13 1.86 5.75

 HUB 12.59 539.16 325.49 429.83 1171.44 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 576.64 511.39 297.75 0.43 5005.90 0.92 0.91 

 MEAN 498.14 476.81 220.79 0.41 4300.53 0.92 0.91 0.91 1.51

 HUB 404.68 437.06 79.19 0.37 4099.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.49 1.16 9.28 607.00 1.04 586.87 521.23 0.04

 MEAN 10.28 1.13 9.07 603.36 1.04 582.83 519.91 0.04

 HUB 10.22 1.13 8.85 602.32 1.04 578.97 519.54 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.85 35.61 31.50 4.11 0.93 0.43 1.40

 MEAN 33.28 27.58 23.50 4.08 0.93 0.40 1.64

 HUB 37.13 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 563.3777 282.4365 487.4669 1171.1572 0.4810 -0.2015 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3018 8.8109 578.7341 520.1885 0.0463 30.0878 33.0000 2.9122

 

NASA/TM—2013-218094 J–161
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 493.1024 112.6003 480.0741 1177.1770 0.4189 0.0442 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2757 9.1214 584.6973 520.1205 410.5396 0.0407 0.3337

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 477.5614 0.0000 477.5614 1178.3724 0.4053 0.2553 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1915 585.9102 520.1218 0.0000 0.0600 0.0395 0.0998

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 10.2772 1.1327 604.2274 23.0792 257.2005 1.9938

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 143681.203 0.432 467.940 558443.188 0.542688E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3200 Tt4 = 604.2274 T1 = 457.7376

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 911255.31 2967.7683 186.6113 2.4098 0.8583 4.4899 1.3200 37.3740

NASA/TM—2013-218094 J–162
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.819 EfDer = 0.996 SH = 0.474858E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.679 3652.585 4.265 457.737 1.000 1.000 0.980

 W Kg/sec = 25.763 Wdry = 56.677 WH2O = 0.003 lbm/sec H2O = 0.018g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 183.529 3888.203 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 147144.141 44472.469 1.548 831.557 537.207 619.754 1.154

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 424.68 -0.15 424.68 0.41 0.76 699.98

 MEAN 17.06 0.00 -0.02 424.68 -0.15 424.68 0.41 0.67

 HUB 12.51 0.00 -0.02 424.68 -0.15 424.68 0.41 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.15 50.47 6.68 657.58 782.91 3.80 443.23 448.34 2.95

 MEAN 52.02 47.20 4.82 543.79 690.09 3.80 443.23 448.34 2.95

 HUB 43.21 38.62 4.59 398.75 582.64 3.80 443.23 448.34 2.95

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 656.15 357.88 549.96 1045.52 0.63 7.29 6.52 16.04

 MEAN 18.04 693.09 401.83 564.72 1040.17 0.67 7.43 6.80 12.53

 HUB 15.00 803.05 537.44 596.69 1029.79 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 657.58 626.32 299.69 0.60 7386.17 0.92 0.91

 MEAN 574.90 590.65 173.07 0.57 7249.87 0.92 0.91 0.91 1.29

 HUB 478.12 599.64 59.31 0.58 8063.37 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.27 495.61 1.08 460.98 472.78 1.42

 MEAN 5.52 1.30 4.12 494.91 1.08 456.27 472.45 1.71

 HUB 5.68 1.33 3.82 499.09 1.09 447.21 475.11 2.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.05 28.59 24.20 4.39 0.93 0.33 1.80

 MEAN 35.43 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 42.01 -5.68 -9.30 3.62 0.92 0.14 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 736.6399 401.0471 617.8994 1036.3031 0.7108 -0.0817 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5692 3.9910 452.8887 473.4436 1.9580 32.9855 35.4000 2.4145

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 584.9489 143.0964 567.1760 1054.5851 0.5547 0.2894 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5397 4.5061 469.0149 473.1090 554.9116 0.0294 0.4055

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 581.3181 0.0000 581.3181 1054.9506 0.5510 0.3215 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4983 469.3577 473.0551 0.0000 0.0600 0.0453 0.2842

NASA/TM—2013-218094 J–163
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8683 5.5156 1.2933 496.5363 38.7996 224.5057 1.7404

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 241210.781 0.558 772.596 636472.625 0.489336E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.758 EfDer = 0.999 SH = 0.501081E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.679 3652.585 5.516 496.536 1.000 1.000 0.980

 W Kg/sec = 25.763 Wdry = 56.676 WH2O = 0.003 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 147.796 3733.215 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 127435.148 44472.422 1.365 590.487 432.622 468.502 1.083

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 517.95 -0.18 517.95 0.49 0.79 669.47

 MEAN 18.08 0.00 -0.02 517.95 -0.18 517.95 0.49 0.73

 HUB 15.21 0.00 -0.02 517.95 -0.18 517.95 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.67 46.36 5.31 655.03 835.21 4.70 474.96 473.00 0.86

 MEAN 48.06 42.30 5.76 576.24 774.94 4.70 474.96 473.00 0.86

 HUB 43.12 37.84 5.28 484.82 709.57 4.70 474.96 473.00 0.86

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 587.31 286.89 512.47 1087.58 0.54 2.33 2.04 9.02

 MEAN 18.01 603.40 303.32 521.62 1083.68 0.56 2.40 2.13 7.35

 HUB 15.22 657.63 387.35 531.45 1080.09 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 650.88 628.59 363.99 0.58 5861.99 0.92 0.91

 MEAN 574.06 587.70 270.75 0.54 5465.92 0.92 0.91 0.91 1.43

 HUB 485.23 540.39 97.89 0.50 5899.27 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.22 5.51 526.59 1.06 498.85 488.65 0.38

 MEAN 6.62 1.20 5.37 524.56 1.06 495.28 487.68 0.43

 HUB 6.71 1.22 5.24 526.78 1.06 492.00 488.79 0.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.24 35.38 31.50 3.88 0.93 0.37 1.40

 MEAN 30.18 27.43 23.50 3.93 0.92 0.36 1.63

 HUB 36.09 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 676.3171 304.1667 604.0591 1076.9814 0.6280 -0.1915 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6646 5.1254 489.1952 488.3987 0.5180 26.7270 30.6000 3.8730

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 569.7059 120.7817 556.7554 1088.6808 0.5233 0.1134 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6411 5.5229 499.8766 488.2564 491.5697 0.0281 0.2784

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 597.1281 0.0000 597.1281 1085.8590 0.5499 0.1804 0.5911

NASA/TM—2013-218094 J–164
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4030 497.3057 488.2253 0.0000 0.0600 0.0447 0.0213

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8711 6.6194 1.2001 525.9763 29.4408 256.9293 1.9917

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183082.156 0.432 586.411 572315.000 0.504399E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.994 EfDer = 0.999 SH = 0.508472E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.679 3652.585 6.619 525.976 1.000 1.000 0.980

 W Kg/sec = 25.763 Wdry = 56.676 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 126.750 3627.233 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110200.273 44472.414 1.470 545.479 371.028 424.468 1.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 484.86 -0.17 484.86 0.44 0.73 635.27

 MEAN 17.74 0.00 -0.02 484.86 -0.17 484.86 0.44 0.68

 HUB 15.05 0.00 -0.02 484.86 -0.17 484.86 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.85 46.36 6.49 639.73 802.84 5.80 507.07 488.17 0.29

 MEAN 49.39 43.40 5.99 565.41 744.96 5.80 507.07 488.17 0.29

 HUB 44.70 38.84 5.86 479.72 682.19 5.80 507.07 488.17 0.29

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 562.64 286.90 484.00 1120.62 0.50 2.26 1.98 8.75

 MEAN 17.51 576.93 302.01 491.57 1117.08 0.52 2.34 2.07 6.78

 HUB 14.85 628.02 380.36 499.74 1113.79 0.56 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 631.44 594.11 344.54 0.53 5686.79 0.92 0.91

 MEAN 558.02 554.24 256.00 0.50 5290.19 0.92 0.91 0.91 1.45

 HUB 473.34 508.31 92.98 0.46 5650.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.92 1.20 6.68 555.12 1.06 529.67 501.36 0.15

 MEAN 7.82 1.18 6.54 553.09 1.05 526.33 500.50 0.17

 HUB 7.91 1.19 6.39 554.94 1.06 523.23 501.31 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.66 35.45 31.50 3.95 0.93 0.39 1.40

 MEAN 31.57 27.51 23.50 4.01 0.92 0.38 1.62

 HUB 37.28 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 640.4548 303.9962 563.7098 1111.8154 0.5760 -0.1735 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8692 6.3013 521.4108 501.0514 0.1902 28.3370 31.5000 3.1630

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 543.9008 118.6483 530.8019 1121.5776 0.4849 0.1197 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8494 6.6964 530.6030 500.9627 451.3937 0.0247 0.3036

 

NASA/TM—2013-218094 J–165
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 555.3640 0.0000 555.3640 1120.4856 0.4956 0.2113 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6327 529.5921 500.9201 0.0000 0.0600 0.0400 0.0724

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8775 7.8288 1.1827 554.3845 28.4093 245.3468 1.9019

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176720.078 0.443 566.033 546566.938 0.512971E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.372 EfDer = 1.000 SH = 0.519516E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.679 3652.585 7.829 554.384 1.000 1.000 0.980

 W Kg/sec = 25.763 Wdry = 56.676 WH2O = 0.003 lbm/sec H2O = 0.029g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.026 3533.076 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 96520.289 44472.395 1.594 513.330 322.089 395.845 1.229

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 451.27 -0.16 451.27 0.40 0.67 593.80

 MEAN 16.97 0.00 -0.02 451.27 -0.16 451.27 0.40 0.62

 HUB 14.32 0.00 -0.02 451.27 -0.16 451.27 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.69 46.36 7.33 613.91 762.05 7.02 538.02 500.89 0.12

 MEAN 50.17 43.80 6.37 540.94 704.57 7.02 538.02 500.89 0.12

 HUB 45.34 37.84 7.50 456.45 641.97 7.02 538.02 500.89 0.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 532.09 279.34 452.87 1150.81 0.46 2.16 1.89 8.34

 MEAN 16.57 542.99 289.09 459.64 1147.29 0.47 2.24 1.97 6.35

 HUB 13.89 587.37 356.39 466.90 1143.95 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 601.80 555.94 322.46 0.48 5276.94 0.92 0.91

 MEAN 528.29 518.15 239.20 0.45 4793.90 0.92 0.91 0.91 1.48

 HUB 442.74 474.82 86.35 0.42 4952.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.17 1.17 7.94 581.42 1.05 558.67 511.88 0.07

 MEAN 9.04 1.15 7.77 578.95 1.04 555.25 510.92 0.08

 HUB 9.08 1.16 7.61 579.76 1.05 552.03 511.25 0.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.67 35.45 31.50 3.95 0.93 0.40 1.40

 MEAN 32.17 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.35 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 586.5303 290.7112 509.4162 1144.2944 0.5126 -0.1199 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0851 7.6112 552.3975 511.3344 0.0842 29.7123 32.4000 2.6877

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 504.4359 113.1302 491.5864 1151.7238 0.4380 0.1455 2.2705

 

NASA/TM—2013-218094 J–166
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0699 7.9634 559.5945 511.2797 432.2457 0.0215 0.3257

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 500.3070 0.0000 500.3070 1152.0438 0.4343 0.2367 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9601 559.9294 511.2276 0.0000 0.0600 0.0391 0.1430

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 9.0465 1.1555 580.0416 25.6588 247.7675 1.9207

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 159670.438 0.441 511.423 540198.438 0.526369E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.675 EfDer = 1.000 SH = 0.538471E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.679 3652.585 9.046 580.041 1.000 1.000 0.980

 W Kg/sec = 25.763 Wdry = 56.676 WH2O = 0.003 lbm/sec H2O = 0.034g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.394 3454.052 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85781.719 44472.359 1.788 509.668 285.127 384.739 1.349 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 403.94 -0.14 403.94 0.35 0.61 552.19

 MEAN 15.91 0.00 -0.02 403.94 -0.14 403.94 0.35 0.56

 HUB 13.07 0.00 -0.02 403.94 -0.14 403.94 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.33 47.36 7.97 583.95 710.16 8.33 566.93 511.21 0.06

 MEAN 51.47 44.80 6.67 507.22 648.53 8.33 566.93 511.21 0.06

 HUB 45.89 38.84 7.05 416.60 580.38 8.33 566.93 511.21 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 495.04 279.18 408.80 1178.55 0.42 2.05 1.78 7.43

 MEAN 15.50 499.37 277.01 415.49 1174.51 0.43 2.13 1.86 5.75

 HUB 12.59 532.19 323.53 422.56 1170.62 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 571.83 502.76 292.65 0.43 5011.13 0.92 0.91

 MEAN 493.98 468.73 216.97 0.40 4295.26 0.92 0.91 0.91 1.52

 HUB 401.30 429.65 77.78 0.37 4075.04 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.45 1.15 9.27 605.71 1.04 586.02 520.84 0.04

 MEAN 10.24 1.13 9.06 602.04 1.04 582.01 519.51 0.04

 HUB 10.17 1.12 8.84 600.91 1.04 578.16 519.10 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.33 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.69 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.44 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 555.7930 282.0930 478.8835 1170.4902 0.4748 -0.1988 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2611 8.8106 578.0728 519.7755 0.0476 30.5008 33.0000 2.4992

 

NASA/TM—2013-218094 J–167
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.2798 110.5857 471.4846 1176.5239 0.4116 0.0556 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2372 9.1240 584.0468 519.7122 410.5396 0.0394 0.3395

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 469.1588 0.0000 469.1588 1177.6660 0.3984 0.2619 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1905 585.2060 519.7121 0.0000 0.0600 0.0387 0.1097

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8813 10.2381 1.1317 602.8844 22.8446 254.7601 1.9749

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 142219.531 0.435 455.528 548861.125 0.548905E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3171 Tt4 = 602.8844 T1 = 457.7375

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 902903.00 2891.9919 183.5287 2.4007 0.8620 4.8189 1.3171 37.3740

NASA/TM—2013-218094 J–168
 50μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.844 EfDer = 0.984 SH = 0.942187E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.722 3973.534 4.265 477.919 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.716 WH2O = 0.006 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.221 4139.589 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171771.500 48428.578 1.391 831.557 597.792 619.754 1.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 495.76 -0.17 495.76 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 495.76 -0.17 495.76 0.48 0.74

 HUB 12.51 0.00 -0.02 495.76 -0.17 495.76 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.28 50.47 4.81 715.36 870.49 3.66 458.15 460.91 2.71

 MEAN 50.04 47.20 2.84 591.57 771.97 3.66 458.15 460.91 2.71

 HUB 41.20 38.62 2.58 433.79 658.86 3.66 458.15 460.91 2.71

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 743.60 360.71 650.26 1061.27 0.70 7.29 6.52 16.04

 MEAN 18.04 789.70 420.32 668.55 1055.77 0.75 7.43 6.80 12.53

 HUB 15.00 933.68 592.64 721.48 1041.45 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.36 740.68 354.65 0.70 7444.88 0.92 0.90

 MEAN 625.41 699.30 205.09 0.66 7583.85 0.92 0.90 0.90 1.21

 HUB 520.13 725.11 72.50 0.70 8891.67 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 519.44 1.09 474.97 483.75 1.42

 MEAN 5.63 1.32 3.90 520.22 1.09 470.06 484.30 1.70

 HUB 5.89 1.38 3.52 527.51 1.10 457.40 488.59 2.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.02 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.16 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.40 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 854.1495 419.5058 744.0338 1048.6185 0.8145 -0.1082 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6899 3.6957 463.7132 485.6089 2.1610 29.4154 35.4000 5.9846

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 695.9929 170.2611 674.8461 1070.6743 0.6501 0.2272 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6287 4.2511 483.4336 484.7977 554.9116 0.0424 0.3580

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 698.3423 0.0000 698.3423 1070.3605 0.6524 0.2518 1.3089

NASA/TM—2013-218094 J–169
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.1979 483.1751 484.6455 0.0000 0.0600 0.0740 0.1990

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8218 5.5692 1.3059 522.3923 44.4744 238.1873 1.8464

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 276513.406 0.540 964.474 688665.250 0.972625E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.450 EfDer = 0.989 SH = 0.100067E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.722 3973.534 5.569 522.392 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.716 WH2O = 0.006 lbm/sec H2O = 0.040g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.496 3959.467 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 150299.734 48428.461 1.234 590.487 478.593 468.502 0.979

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 610.88 -0.21 610.88 0.57 0.87 710.04

 MEAN 18.08 0.00 -0.02 610.88 -0.21 610.88 0.57 0.81

 HUB 15.21 0.00 -0.02 610.88 -0.21 610.88 0.57 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.40 46.36 3.04 712.58 938.75 4.49 492.38 484.49 0.79

 MEAN 45.75 42.30 3.45 626.87 875.45 4.49 492.38 484.49 0.79

 HUB 40.82 37.84 2.98 527.42 807.20 4.49 492.38 484.49 0.79

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 662.03 280.38 599.73 1109.42 0.60 2.33 2.04 9.02

 MEAN 18.01 682.27 306.53 609.53 1105.86 0.62 2.40 2.13 7.35

 HUB 15.22 744.85 412.22 620.38 1102.66 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.08 736.61 427.70 0.66 5729.66 0.92 0.90

 MEAN 624.51 687.49 317.98 0.62 5524.36 0.92 0.90 0.90 1.37

 HUB 527.87 631.07 115.65 0.57 6278.35 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.77 1.22 5.34 554.34 1.06 519.10 498.54 0.34

 MEAN 6.72 1.21 5.22 553.20 1.06 515.77 498.09 0.38

 HUB 6.89 1.24 5.10 557.40 1.07 512.79 499.90 0.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.06 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.70 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.60 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 782.9358 307.3885 720.0700 1094.9746 0.7150 -0.2381 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7795 4.8403 505.7002 498.9572 0.5107 23.1170 30.6000 7.4830

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 677.0516 143.5397 661.6609 1108.3602 0.6109 0.0189 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7286 5.2457 518.1257 498.6407 491.5697 0.0422 0.2194

 

NASA/TM—2013-218094 J–170
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 721.3776 0.0000 721.3776 1102.9967 0.6540 0.0956 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0256 513.1467 498.5623 0.0000 0.0600 0.0755 -0.1205

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8223 6.6760 1.1987 554.9811 32.5896 281.2249 2.1800

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 202709.453 0.404 707.047 623711.750 0.100931E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.821 EfDer = 0.991 SH = 0.101950E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.722 3973.534 6.676 554.981 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.716 WH2O = 0.006 lbm/sec H2O = 0.047g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.581 3841.458 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 129400.414 48428.430 1.325 545.479 411.535 424.468 1.031

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 569.34 -0.20 569.34 0.51 0.80 672.79

 MEAN 17.74 0.00 -0.02 569.34 -0.20 569.34 0.51 0.75

 HUB 15.05 0.00 -0.02 569.34 -0.20 569.34 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.72 46.36 4.36 695.94 899.30 5.61 528.93 498.40 0.26

 MEAN 47.22 43.40 3.82 615.09 838.29 5.61 528.93 498.40 0.26

 HUB 42.52 38.84 3.68 521.87 772.46 5.61 528.93 498.40 0.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 631.81 283.50 564.64 1146.27 0.55 2.26 1.98 8.75

 MEAN 17.51 650.11 307.34 572.87 1142.95 0.57 2.34 2.07 6.78

 HUB 14.85 709.33 405.50 581.99 1139.94 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 693.95 403.42 0.61 5620.09 0.92 0.91

 MEAN 607.05 646.53 299.71 0.57 5384.02 0.92 0.91 0.91 1.40

 HUB 514.93 592.19 109.43 0.52 6024.70 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.00 1.20 6.52 586.31 1.06 554.22 510.56 0.13

 MEAN 7.94 1.19 6.39 584.99 1.05 551.02 510.09 0.14

 HUB 8.10 1.21 6.26 588.57 1.06 548.12 511.45 0.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.66 35.55 31.50 4.05 0.93 0.34 1.40

 MEAN 28.21 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.87 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 733.7064 309.3612 665.2975 1134.9271 0.6465 -0.2060 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9984 6.0592 543.3623 510.7206 0.1747 24.9383 31.5000 6.5617

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 641.8356 140.0121 626.3782 1145.4963 0.5603 0.0333 2.3726

 

NASA/TM—2013-218094 J–171
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9574 6.4465 553.5154 510.5378 451.3937 0.0353 0.2527

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 659.5397 0.0000 659.5397 1143.5521 0.5767 0.1426 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3357 551.6683 510.4440 0.0000 0.0600 0.0608 -0.0350

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8441 7.9161 1.1858 586.6224 31.6423 266.6945 2.0674

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 196899.719 0.417 686.783 589501.813 0.102831E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.409 EfDer = 0.995 SH = 0.104054E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.722 3973.534 7.916 586.622 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.716 WH2O = 0.006 lbm/sec H2O = 0.055g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.891 3736.421 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112538.602 48428.391 1.439 513.330 356.845 395.845 1.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 526.16 -0.18 526.16 0.45 0.74 627.98

 MEAN 16.97 0.00 -0.02 526.16 -0.18 526.16 0.45 0.68

 HUB 14.32 0.00 -0.02 526.16 -0.18 526.16 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.78 46.36 5.42 667.85 850.36 6.88 564.38 510.37 0.11

 MEAN 48.21 43.80 4.41 588.47 789.53 6.88 564.38 510.37 0.11

 HUB 43.35 37.84 5.51 496.56 723.59 6.88 564.38 510.37 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 594.75 279.74 524.86 1180.22 0.50 2.16 1.89 8.34

 MEAN 16.57 609.51 296.47 532.55 1176.72 0.52 2.24 1.97 6.35

 HUB 13.89 661.46 380.71 540.91 1173.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.68 645.02 374.94 0.55 5284.95 0.92 0.91

 MEAN 574.71 600.85 278.24 0.51 4916.75 0.92 0.91 0.91 1.42

 HUB 481.64 550.25 100.93 0.47 5290.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.31 1.18 7.84 616.07 1.05 587.65 520.78 0.06

 MEAN 9.21 1.16 7.68 614.02 1.05 584.17 520.09 0.07

 HUB 9.31 1.18 7.52 616.10 1.05 580.95 520.82 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.06 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.10 27.59 23.50 4.09 0.92 0.35 1.62

 HUB 35.14 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 664.4277 298.1385 593.7825 1172.3848 0.5667 -0.1373 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2582 7.4655 579.9369 520.5452 0.0737 26.6612 32.4000 5.7388

 

NASA/TM—2013-218094 J–172
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 588.7303 132.0350 573.7335 1180.0646 0.4989 0.0745 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2281 7.8019 587.5552 520.4386 432.2457 0.0290 0.2828

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 584.0569 0.0000 584.0569 1180.4778 0.4948 0.1854 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7979 587.9987 520.3650 0.0000 0.0600 0.0477 0.0719

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8616 9.1983 1.1620 615.3939 28.7731 266.9841 2.0696

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 179140.578 0.418 624.839 577230.938 0.105151E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.014 EfDer = 0.997 SH = 0.107281E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.722 3973.534 9.198 615.393 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.716 WH2O = 0.007 lbm/sec H2O = 0.064g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.441 3648.031 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99005.203 48428.328 1.620 509.668 314.569 384.739 1.223

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 466.21 -0.16 466.21 0.39 0.66 583.20

 MEAN 15.91 0.00 -0.02 466.21 -0.16 466.21 0.39 0.61

 HUB 13.07 0.00 -0.02 466.21 -0.16 466.21 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.73 47.36 6.37 635.26 788.10 8.29 597.94 520.33 0.05

 MEAN 49.81 44.80 5.01 551.79 722.50 8.29 597.94 520.33 0.05

 HUB 44.20 38.84 5.36 453.21 650.31 8.29 597.94 520.33 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 549.00 285.42 468.97 1211.86 0.45 2.05 1.78 7.43

 MEAN 15.50 556.96 287.51 477.01 1207.53 0.46 2.13 1.86 5.75

 HUB 12.59 596.52 346.58 485.52 1203.43 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 577.30 336.66 0.48 5123.35 0.92 0.91

 MEAN 537.39 538.50 249.88 0.45 4458.20 0.92 0.91 0.91 1.47

 HUB 436.57 493.79 89.99 0.41 4365.48 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.69 1.16 9.30 643.92 1.05 619.72 529.73 0.03

 MEAN 10.49 1.14 9.08 640.22 1.04 615.31 528.55 0.04

 HUB 10.46 1.14 8.86 639.70 1.04 611.13 528.39 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.32 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.08 27.65 23.50 4.15 0.92 0.37 1.64

 HUB 35.52 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 625.9087 292.7776 553.2115 1202.0842 0.5207 -0.2179 2.0437

 

NASA/TM—2013-218094 J–173
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5159 8.7620 609.8335 528.8409 0.0408 27.8893 33.0000 5.1107

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 560.7544 128.0487 545.9387 1208.1915 0.4641 -0.0209 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4709 9.0511 616.0385 528.7194 410.5396 0.0507 0.3035

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 541.8454 0.0000 541.8454 1209.8020 0.4479 0.2197 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1474 617.7146 528.7327 0.0000 0.0600 0.0454 0.0449

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8692 10.4786 1.1392 641.2789 25.8868 270.9525 2.1004

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161270.422 0.417 562.509 581088.438 0.108952E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3418 Tt4 = 641.2789 T1 = 477.9185

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1016533.63 3545.6521 204.2212 2.4571 0.8233 2.8439 1.3418 37.3740

NASA/TM—2013-218094 J–174
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 3.953 EfDer = 0.992 SH = 0.949700E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.025 3823.067 4.265 477.918 1.000 1.000 0.980

 W Kg/sec = 26.375 Wdry = 58.019 WH2O = 0.006 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 191.987 3982.834 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 158869.984 45527.348 1.480 831.557 561.982 619.754 1.103

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 458.52 -0.16 458.52 0.44 0.79 717.01

 MEAN 17.06 0.00 -0.02 458.52 -0.16 458.52 0.44 0.70

 HUB 12.51 0.00 -0.02 458.52 -0.16 458.52 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.33 50.47 5.86 688.27 827.15 3.74 461.01 460.85 2.44

 MEAN 51.15 47.20 3.95 569.17 731.01 3.74 461.01 460.85 2.44

 HUB 42.32 38.62 3.70 417.37 620.14 3.74 461.01 460.85 2.44

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 698.27 363.07 596.46 1065.66 0.66 7.29 6.52 16.04

 MEAN 18.04 739.34 413.82 612.68 1060.20 0.70 7.43 6.80 12.53

 HUB 15.00 862.71 565.37 651.63 1048.46 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 688.27 679.35 325.20 0.64 7493.41 0.92 0.91

 MEAN 601.73 640.85 187.91 0.60 7466.38 0.92 0.91 0.91 1.26

 HUB 500.44 654.86 64.93 0.62 8482.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.57 1.31 4.19 518.13 1.08 478.92 483.03 1.25

 MEAN 5.56 1.30 4.03 517.99 1.08 474.02 483.08 1.49

 HUB 5.76 1.35 3.71 523.44 1.10 463.58 486.23 2.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.33 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.04 17.05 12.70 4.35 0.92 0.25 2.22

 HUB 40.95 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 790.4847 413.0173 674.0051 1055.2396 0.7491 -0.0909 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6129 3.8839 469.5964 484.1318 1.7569 31.4992 35.4000 3.9008

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 635.4916 155.4606 616.1830 1075.0188 0.5911 0.2637 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5740 4.4125 487.3732 483.5727 554.9116 0.0335 0.3860

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 633.0502 0.0000 633.0502 1075.2712 0.5887 0.2947 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.3935 487.6259 483.4799 0.0000 0.0600 0.0543 0.2522

NASA/TM—2013-218094 J–175
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8535 5.5397 1.2990 519.8514 41.9340 230.3247 1.7855

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 260731.813 0.550 854.947 636940.625 0.984502E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.798 EfDer = 0.996 SH = 0.101721E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.025 3823.067 5.540 519.851 1.000 1.000 0.980

 W Kg/sec = 26.375 Wdry = 58.019 WH2O = 0.006 lbm/sec H2O = 0.041g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 154.143 3818.831 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 137947.844 45527.230 1.309 590.487 451.219 468.502 1.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 560.68 -0.19 560.68 0.52 0.82 684.82

 MEAN 18.08 0.00 -0.02 560.68 -0.19 560.68 0.52 0.76

 HUB 15.21 0.00 -0.02 560.68 -0.19 560.68 0.52 0.70

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.73 46.36 4.37 685.60 885.82 4.62 494.57 483.39 0.76

 MEAN 47.10 42.30 4.80 603.14 823.63 4.62 494.57 483.39 0.76

 HUB 42.16 37.84 4.32 507.44 756.35 4.62 494.57 483.39 0.76

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 623.50 287.79 553.11 1110.53 0.56 2.33 2.04 9.02

 MEAN 18.01 641.58 308.22 562.70 1106.69 0.58 2.40 2.13 7.35

 HUB 15.22 699.92 401.83 573.07 1103.20 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 681.26 678.79 393.47 0.61 5880.63 0.92 0.91

 MEAN 600.86 634.25 292.64 0.57 5554.46 0.92 0.91 0.91 1.40

 HUB 507.88 582.80 106.04 0.53 6120.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.45 551.40 1.06 520.14 497.51 0.34

 MEAN 6.66 1.20 5.32 549.65 1.06 516.55 496.79 0.38

 HUB 6.79 1.22 5.19 552.69 1.06 513.30 498.14 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.49 35.43 31.50 3.93 0.93 0.35 1.40

 MEAN 28.71 27.48 23.50 3.98 0.92 0.34 1.63

 HUB 35.04 10.48 6.50 3.98 0.92 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 725.1088 309.0821 655.9352 1098.5129 0.6601 -0.2079 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7127 5.0276 508.9768 497.5442 0.4770 25.2302 30.6000 5.3698

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 617.9764 131.0154 603.9286 1110.9337 0.5563 0.0767 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6807 5.4281 520.5430 497.3143 491.5697 0.0328 0.2554

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 650.7952 0.0000 650.7952 1107.3346 0.5877 0.1488 0.5911

NASA/TM—2013-218094 J–176
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2783 517.1990 497.2696 0.0000 0.0600 0.0546 -0.0298

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8562 6.6500 1.2004 551.2459 31.3953 266.5764 2.0665

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195284.484 0.421 640.343 574286.000 0.102703E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.108 EfDer = 0.997 SH = 0.103893E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.025 3823.067 6.650 551.246 1.000 1.000 0.980

 W Kg/sec = 26.375 Wdry = 58.019 WH2O = 0.006 lbm/sec H2O = 0.049g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 132.228 3708.493 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 119004.453 45527.191 1.409 545.479 387.085 424.468 1.097 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 523.60 -0.18 523.60 0.47 0.76 649.50

 MEAN 17.74 0.00 -0.02 523.60 -0.18 523.60 0.47 0.71

 HUB 15.05 0.00 -0.02 523.60 -0.18 523.60 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.98 46.36 5.62 669.59 850.14 5.74 529.21 497.16 0.27

 MEAN 48.51 43.40 5.11 591.80 790.31 5.74 529.21 497.16 0.27

 HUB 43.81 38.84 4.97 502.11 725.57 5.74 529.21 497.16 0.27

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 596.19 289.28 521.31 1145.44 0.52 2.26 1.98 8.75

 MEAN 17.51 612.35 307.94 529.29 1141.92 0.54 2.34 2.07 6.78

 HUB 14.85 667.36 394.94 537.96 1138.68 0.59 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.91 640.21 371.63 0.56 5734.24 0.92 0.91

 MEAN 584.06 596.99 276.13 0.52 5394.09 0.92 0.91 0.91 1.43

 HUB 495.43 547.26 100.49 0.48 5867.58 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.96 1.20 6.63 582.00 1.06 553.43 509.34 0.14

 MEAN 7.88 1.18 6.49 580.18 1.05 550.04 508.67 0.15

 HUB 7.99 1.20 6.35 582.72 1.06 546.92 509.66 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.03 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.19 27.55 23.50 4.05 0.92 0.36 1.62

 HUB 36.28 10.58 6.50 4.08 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 683.8542 309.9561 609.5767 1135.6438 0.6022 -0.1853 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9299 6.2247 544.0485 509.2320 0.1791 26.9523 31.5000 4.5477

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 588.0618 128.2817 573.8994 1145.8250 0.5132 0.0862 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9036 6.6184 553.8384 509.0953 451.3937 0.0281 0.2836

 

NASA/TM—2013-218094 J–177
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 601.4011 0.0000 601.4011 1144.4783 0.5255 0.1864 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5426 552.5668 509.0401 0.0000 0.0600 0.0454 0.0339

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8687 7.8786 1.1848 581.6293 30.3846 253.6723 1.9665

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189073.828 0.433 619.978 546416.000 0.104948E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.586 EfDer = 0.999 SH = 0.106620E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.025 3823.067 7.879 581.629 1.000 1.000 0.980

 W Kg/sec = 26.375 Wdry = 58.019 WH2O = 0.006 lbm/sec H2O = 0.057g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.643 3610.330 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 103876.477 45527.141 1.529 513.330 335.626 395.845 1.179

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 485.66 -0.17 485.66 0.42 0.70 606.79

 MEAN 16.97 0.00 -0.02 485.66 -0.17 485.66 0.42 0.65

 HUB 14.32 0.00 -0.02 485.66 -0.17 485.66 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.92 46.36 6.56 642.56 805.58 6.99 562.68 508.99 0.12

 MEAN 49.39 43.80 5.59 566.19 746.07 6.99 562.68 508.99 0.12

 HUB 44.54 37.84 6.70 477.75 681.37 6.99 562.68 508.99 0.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 562.70 283.25 486.21 1177.43 0.48 2.16 1.89 8.34

 MEAN 16.57 575.29 295.76 493.45 1173.86 0.49 2.24 1.97 6.35

 HUB 13.89 623.23 370.38 501.24 1170.50 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 629.89 597.12 346.63 0.51 5351.05 0.92 0.91

 MEAN 552.95 556.45 257.19 0.47 4904.74 0.92 0.91 0.91 1.45

 HUB 463.41 509.80 93.03 0.44 5146.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.24 1.17 7.92 610.31 1.05 584.88 519.34 0.07

 MEAN 9.12 1.16 7.76 607.92 1.05 581.33 518.52 0.08

 HUB 9.19 1.17 7.59 609.22 1.05 578.01 518.99 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.22 35.49 31.50 3.99 0.93 0.38 1.40

 MEAN 30.94 27.53 23.50 4.03 0.92 0.38 1.62

 HUB 36.46 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 623.5355 297.4242 548.0286 1170.3552 0.5328 -0.1263 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1713 7.5778 577.9235 518.9315 0.0811 28.4894 32.4000 3.9106

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 542.8514 121.7457 529.0233 1177.9845 0.4608 0.1179 2.2705

 

NASA/TM—2013-218094 J–178
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1515 7.9263 585.4822 518.8508 432.2457 0.0239 0.3084

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 538.4454 0.0000 538.4454 1178.3405 0.4570 0.2165 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9229 585.8673 518.7881 0.0000 0.0600 0.0418 0.1155

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8739 9.1258 1.1583 609.1511 27.5234 255.1529 1.9779

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171355.344 0.432 561.879 538221.375 0.107969E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.007 EfDer = 0.999 SH = 0.110580E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.025 3823.067 9.126 609.151 1.000 1.000 0.980

 W Kg/sec = 26.375 Wdry = 58.018 WH2O = 0.006 lbm/sec H2O = 0.067g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 101.289 3527.829 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91951.844 45527.070 1.719 509.668 296.554 384.739 1.297

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 433.00 -0.15 433.00 0.36 0.63 563.98

 MEAN 15.91 0.00 -0.02 433.00 -0.15 433.00 0.36 0.58

 HUB 13.07 0.00 -0.02 433.00 -0.15 433.00 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.69 47.36 7.33 611.20 749.16 8.33 594.10 518.76 0.06

 MEAN 50.81 44.80 6.01 530.90 685.20 8.33 594.10 518.76 0.06

 HUB 45.21 38.84 6.37 436.05 614.62 8.33 594.10 518.76 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 522.00 285.23 437.18 1206.95 0.43 2.05 1.78 7.43

 MEAN 15.50 527.80 284.64 444.47 1202.75 0.44 2.13 1.86 5.75

 HUB 12.59 563.67 336.55 452.17 1198.72 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 598.52 537.84 313.29 0.45 5119.77 0.92 0.91

 MEAN 517.04 501.56 232.40 0.42 4413.66 0.92 0.91 0.91 1.50

 HUB 420.03 459.81 83.48 0.38 4239.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.56 1.16 9.31 636.58 1.05 614.70 527.99 0.04

 MEAN 10.36 1.13 9.09 632.80 1.04 610.43 526.76 0.04

 HUB 10.31 1.13 8.87 631.86 1.04 606.35 526.46 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.12 35.63 31.50 4.13 0.93 0.42 1.40

 MEAN 32.64 27.60 23.50 4.10 0.93 0.39 1.64

 HUB 36.66 10.46 6.50 3.96 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 589.5882 289.8629 513.4138 1198.1625 0.4921 -0.2060 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3827 8.8175 605.8418 527.0284 0.0469 29.4482 33.0000 3.5518

 

NASA/TM—2013-218094 J–179
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 519.5662 118.6434 505.8387 1204.3143 0.4314 0.0261 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3521 9.1243 612.0759 526.9392 410.5396 0.0431 0.3249

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 502.9091 0.0000 502.9091 1205.6290 0.4171 0.2451 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2011 613.4451 526.9426 0.0000 0.0600 0.0409 0.0843

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8776 10.3551 1.1347 633.7456 24.5963 261.0726 2.0238

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 153218.734 0.428 502.409 545031.063 0.112628E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3261 Tt4 = 633.7456 T1 = 477.9182

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 969664.25 3179.5566 191.9870 2.4281 0.8503 3.9529 1.3261 37.3740

NASA/TM—2013-218094 J–180
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.382 EfDer = 0.994 SH = 0.952386E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.729 3775.949 4.265 477.918 1.000 1.000 0.980

 W Kg/sec = 25.786 Wdry = 56.724 WH2O = 0.005 lbm/sec H2O = 0.034g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 187.702 3933.747 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 154519.922 44511.102 1.513 831.557 549.438 619.754 1.128

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.97 -0.15 445.97 0.43 0.78 708.17

 MEAN 17.06 0.00 -0.02 445.97 -0.15 445.97 0.43 0.69

 HUB 12.51 0.00 -0.02 445.97 -0.15 445.97 0.43 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.74 50.47 6.27 679.79 813.15 3.77 461.92 460.84 2.37

 MEAN 51.58 47.20 4.38 562.16 717.69 3.77 461.92 460.84 2.37

 HUB 42.76 38.62 4.14 412.22 607.40 3.77 461.92 460.84 2.37

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 683.86 364.33 578.73 1067.04 0.64 7.29 6.52 16.04

 MEAN 18.04 723.24 412.08 594.36 1061.58 0.68 7.43 6.80 12.53

 HUB 15.00 840.80 556.95 629.89 1050.46 0.80 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 679.79 659.12 315.45 0.62 7519.38 0.92 0.91

 MEAN 594.31 621.67 182.24 0.59 7434.84 0.92 0.91 0.91 1.27

 HUB 494.27 633.00 62.67 0.60 8356.10 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.23 517.77 1.08 480.16 482.83 1.20

 MEAN 5.54 1.30 4.08 517.32 1.08 475.26 482.73 1.43

 HUB 5.72 1.34 3.77 522.21 1.09 465.35 485.54 2.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.19 28.59 24.20 4.39 0.93 0.31 1.80

 MEAN 34.73 17.05 12.70 4.35 0.92 0.27 2.22

 HUB 41.48 -5.68 -9.30 3.62 0.92 0.12 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 770.8202 411.2758 651.9325 1057.1671 0.7291 -0.0860 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5900 3.9402 471.3159 483.7073 1.6570 32.2460 35.4000 3.1540

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 616.0010 150.6927 597.2847 1076.3514 0.5723 0.2767 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5564 4.4616 488.5849 483.2062 554.9116 0.0313 0.3958

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 612.7910 0.0000 612.7910 1076.6787 0.5691 0.3085 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4491 488.9054 483.1282 0.0000 0.0600 0.0493 0.2688

NASA/TM—2013-218094 J–181
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8617 5.5278 1.2962 519.1010 41.1837 227.4061 1.7628

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 256070.281 0.554 820.919 619500.313 0.988882E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.281 EfDer = 0.998 SH = 0.102348E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.729 3775.949 5.528 519.101 1.000 1.000 0.980

 W Kg/sec = 25.786 Wdry = 56.724 WH2O = 0.006 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.918 3774.491 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 133964.016 44510.980 1.337 590.487 441.778 468.502 1.060

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 544.49 -0.19 544.49 0.50 0.80 676.87

 MEAN 18.08 0.00 -0.02 544.49 -0.19 544.49 0.50 0.74

 HUB 15.21 0.00 -0.02 544.49 -0.19 544.49 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.21 46.36 4.85 677.15 869.05 4.66 495.26 483.05 0.75

 MEAN 47.58 42.30 5.28 595.70 807.19 4.66 495.26 483.05 0.75

 HUB 42.64 37.84 4.80 501.19 740.17 4.66 495.26 483.05 0.75

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 611.37 290.49 537.95 1110.91 0.55 2.33 2.04 9.02

 MEAN 18.01 628.63 309.03 547.43 1106.99 0.57 2.40 2.13 7.35

 HUB 15.22 685.49 398.67 557.63 1103.41 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.87 660.00 382.38 0.59 5935.64 0.92 0.91

 MEAN 593.45 616.91 284.42 0.56 5569.06 0.92 0.91 0.91 1.41

 HUB 501.62 567.06 102.95 0.51 6071.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.22 5.48 550.55 1.06 520.50 497.19 0.34

 MEAN 6.64 1.20 5.35 548.61 1.06 516.84 496.40 0.38

 HUB 6.75 1.22 5.22 551.27 1.06 513.49 497.58 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.37 35.41 31.50 3.91 0.93 0.36 1.40

 MEAN 29.45 27.45 23.50 3.95 0.92 0.35 1.63

 HUB 35.56 10.46 6.50 3.96 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 707.3780 309.9005 635.8815 1099.5281 0.6433 -0.1993 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6885 5.0798 509.9189 497.1136 0.4684 25.9825 30.6000 4.6175

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 599.4171 127.0807 585.7913 1111.6958 0.5392 0.0955 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6612 5.4788 521.2598 496.9047 491.5697 0.0302 0.2671

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 629.5977 0.0000 629.5977 1108.4900 0.5680 0.1651 0.5911

NASA/TM—2013-218094 J–182
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3454 518.2811 496.8684 0.0000 0.0600 0.0492 -0.0031

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8644 6.6355 1.2004 550.1459 31.0457 261.6479 2.0283

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193111.453 0.427 619.084 557907.625 0.103392E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.555 EfDer = 0.999 SH = 0.104681E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.729 3775.949 6.636 550.146 1.000 1.000 0.980

 W Kg/sec = 25.786 Wdry = 56.724 WH2O = 0.006 lbm/sec H2O = 0.049g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 129.429 3666.446 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115699.609 44510.938 1.440 545.479 378.892 424.468 1.120

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 509.06 -0.18 509.06 0.45 0.75 642.14

 MEAN 17.74 0.00 -0.02 509.06 -0.18 509.06 0.45 0.69

 HUB 15.05 0.00 -0.02 509.06 -0.18 509.06 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.42 46.36 6.06 661.33 834.70 5.77 529.32 496.77 0.27

 MEAN 48.96 43.40 5.56 584.51 775.24 5.77 529.32 496.77 0.27

 HUB 44.26 38.84 5.42 495.92 710.81 5.77 529.32 496.77 0.27

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 585.13 291.24 507.50 1145.21 0.51 2.26 1.98 8.75

 MEAN 17.51 600.51 308.24 515.36 1141.64 0.53 2.34 2.07 6.78

 HUB 14.85 654.11 391.69 523.87 1138.33 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.77 623.10 361.53 0.54 5772.97 0.92 0.91

 MEAN 576.86 581.17 268.63 0.51 5399.32 0.92 0.91 0.91 1.44

 HUB 489.33 532.89 97.64 0.47 5819.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.94 1.20 6.66 580.73 1.06 553.21 508.95 0.14

 MEAN 7.85 1.18 6.52 578.75 1.05 549.76 508.21 0.16

 HUB 7.95 1.20 6.37 580.97 1.06 546.58 509.09 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.85 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 30.88 27.53 23.50 4.03 0.92 0.37 1.62

 HUB 36.79 10.56 6.50 4.06 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 668.5364 310.2620 592.1810 1135.8341 0.5886 -0.1791 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9002 6.2667 544.2309 508.7596 0.1807 27.6514 31.5000 3.8486

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 571.3192 124.6294 557.5599 1145.9039 0.4986 0.1034 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8775 6.6612 553.9162 508.6342 451.3937 0.0263 0.2939

 

NASA/TM—2013-218094 J–183
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 583.6649 0.0000 583.6649 1144.6910 0.5099 0.2000 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5934 552.7736 508.5872 0.0000 0.0600 0.0417 0.0548

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8743 7.8560 1.1839 580.1469 30.0022 249.3999 1.9333

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186694.641 0.438 598.512 531931.500 0.105822E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.988 EfDer = 0.999 SH = 0.107663E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.729 3775.949 7.856 580.147 1.000 1.000 0.980

 W Kg/sec = 25.786 Wdry = 56.723 WH2O = 0.006 lbm/sec H2O = 0.058g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 112.263 3570.387 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 101147.570 44510.887 1.562 513.330 328.658 395.845 1.204

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 472.90 -0.16 472.90 0.41 0.69 600.08

 MEAN 16.97 0.00 -0.02 472.90 -0.16 472.90 0.41 0.63

 HUB 14.32 0.00 -0.02 472.90 -0.16 472.90 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.32 46.36 6.96 634.64 791.59 7.01 562.18 508.54 0.12

 MEAN 49.79 43.80 5.99 559.21 732.48 7.01 562.18 508.54 0.12

 HUB 44.95 37.84 7.11 471.86 668.16 7.01 562.18 508.54 0.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 552.78 284.40 474.01 1176.59 0.47 2.16 1.89 8.34

 MEAN 16.57 564.63 295.58 481.09 1173.00 0.48 2.24 1.97 6.35

 HUB 13.89 611.25 367.16 488.69 1169.62 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.12 582.02 337.72 0.49 5372.59 0.92 0.91

 MEAN 546.13 542.42 250.56 0.46 4901.59 0.92 0.91 0.91 1.46

 HUB 457.69 497.01 90.54 0.42 5102.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.21 1.17 7.93 608.59 1.05 584.04 518.87 0.07

 MEAN 9.09 1.16 7.77 606.10 1.04 580.49 518.00 0.08

 HUB 9.14 1.16 7.60 607.16 1.05 577.14 518.39 0.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.96 35.47 31.50 3.97 0.93 0.39 1.40

 MEAN 31.57 27.51 23.50 4.01 0.92 0.38 1.62

 HUB 36.92 10.50 6.50 4.00 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 610.8989 297.2372 533.7111 1169.7341 0.5223 -0.1230 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1306 7.5993 577.3080 518.4047 0.0837 29.1145 32.4000 3.2855

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 528.5637 118.5414 515.0995 1177.3431 0.4489 0.1322 2.2705

 

NASA/TM—2013-218094 J–184
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1133 7.9502 584.8434 518.3301 432.2457 0.0225 0.3173

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 524.2517 0.0000 524.2517 1177.6812 0.4452 0.2269 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9468 585.2104 518.2707 0.0000 0.0600 0.0403 0.1297

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8768 9.0889 1.1569 607.2829 27.1376 251.3242 1.9482

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 168952.078 0.437 541.633 524904.125 0.109170E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.349 EfDer = 1.000 SH = 0.111976E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.729 3775.949 9.089 607.283 1.000 1.000 0.980

 W Kg/sec = 25.786 Wdry = 56.723 WH2O = 0.006 lbm/sec H2O = 0.068g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 99.278 3489.705 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89718.289 44510.813 1.753 509.668 290.665 384.739 1.324

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 422.48 -0.15 422.48 0.36 0.62 557.89

 MEAN 15.91 0.00 -0.02 422.48 -0.15 422.48 0.36 0.57

 HUB 13.07 0.00 -0.02 422.48 -0.15 422.48 0.36 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.02 47.36 7.66 603.67 736.94 8.33 592.95 518.25 0.06

 MEAN 51.15 44.80 6.35 524.36 673.49 8.33 592.95 518.25 0.06

 HUB 45.56 38.84 6.72 430.67 603.40 8.33 592.95 518.25 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 513.58 285.28 427.07 1205.48 0.43 2.05 1.78 7.43

 MEAN 15.50 518.68 283.83 434.12 1201.31 0.43 2.13 1.86 5.75

 HUB 12.59 553.35 333.48 441.57 1197.32 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 591.15 525.30 305.87 0.44 5120.54 0.92 0.91

 MEAN 510.67 489.81 226.83 0.41 4401.06 0.92 0.91 0.91 1.51

 HUB 414.86 449.01 81.38 0.38 4200.39 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.51 1.16 9.29 634.38 1.04 613.20 527.42 0.04

 MEAN 10.30 1.13 9.08 630.57 1.04 608.97 526.17 0.05

 HUB 10.24 1.13 8.86 629.51 1.04 604.92 525.83 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.74 35.61 31.50 4.11 0.93 0.42 1.40

 MEAN 33.18 27.59 23.50 4.09 0.93 0.40 1.64

 HUB 37.06 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 578.2930 289.0388 500.8787 1196.9791 0.4831 -0.2022 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3247 8.8189 604.6398 526.4333 0.0490 29.9877 33.0000 3.0123

 

NASA/TM—2013-218094 J–185
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 506.6764 115.7000 493.2895 1203.1389 0.4211 0.0414 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2978 9.1297 610.8771 526.3521 410.5396 0.0411 0.3323

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 490.6599 0.0000 490.6599 1204.3715 0.4074 0.2538 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2011 612.1613 526.3532 0.0000 0.0600 0.0397 0.0975

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8796 10.2996 1.1332 631.4853 24.2042 257.7965 1.9984

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 150772.984 0.431 483.353 532480.375 0.114172E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3213 Tt4 = 631.4853 T1 = 477.9181

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 955601.44 3063.5007 187.7015 2.4151 0.8569 4.3820 1.3213 37.3740

NASA/TM—2013-218094 J–186
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.713 EfDer = 0.996 SH = 0.954351E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.788 3744.103 4.265 477.918 1.000 1.000 0.980

 W Kg/sec = 25.358 Wdry = 55.782 WH2O = 0.005 lbm/sec H2O = 0.034g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 184.585 3900.570 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 151405.516 43772.148 1.539 831.557 540.317 619.754 1.147

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 436.98 -0.15 436.98 0.42 0.77 702.20

 MEAN 17.06 0.00 -0.02 436.98 -0.15 436.98 0.42 0.68

 HUB 12.51 0.00 -0.02 436.98 -0.15 436.98 0.42 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.05 50.47 6.58 674.05 803.43 3.79 462.56 460.83 2.31

 MEAN 51.91 47.20 4.71 557.41 708.40 3.79 462.56 460.83 2.31

 HUB 43.10 38.62 4.48 408.74 598.45 3.79 462.56 460.83 2.31

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 673.86 365.54 566.09 1068.03 0.63 7.29 6.52 16.04

 MEAN 18.04 712.01 411.12 581.33 1062.55 0.67 7.43 6.80 12.53

 HUB 15.00 825.65 551.21 614.70 1051.82 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 674.05 644.70 308.51 0.60 7544.23 0.92 0.91

 MEAN 589.30 608.02 178.18 0.57 7417.55 0.92 0.91 0.91 1.29

 HUB 490.10 617.73 61.11 0.59 8270.07 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.26 517.57 1.08 481.05 482.72 1.17

 MEAN 5.53 1.30 4.11 516.90 1.08 476.13 482.50 1.39

 HUB 5.69 1.33 3.80 521.38 1.09 466.56 485.08 1.98

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.85 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 35.27 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 41.88 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 757.2471 410.3220 636.4424 1058.4916 0.7154 -0.0827 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5752 3.9790 472.4993 483.4329 1.5922 32.8104 35.4000 2.5896

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 602.1732 147.3100 583.8770 1077.3073 0.5590 0.2865 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5448 4.4963 489.4547 482.9673 554.9116 0.0298 0.4033

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 598.5666 0.0000 598.5666 1077.6682 0.5554 0.3185 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4875 489.8061 482.8986 0.0000 0.0600 0.0462 0.2807

NASA/TM—2013-218094 J–187
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8668 5.5197 1.2943 518.6158 40.6987 225.1945 1.7457

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 253057.094 0.557 797.791 607014.063 0.992119E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.649 EfDer = 0.999 SH = 0.102830E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.788 3744.103 5.520 518.616 1.000 1.000 0.980

 W Kg/sec = 25.358 Wdry = 55.782 WH2O = 0.006 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 148.561 3744.407 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 131131.219 43772.020 1.358 590.487 434.878 468.502 1.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 532.98 -0.18 532.98 0.49 0.79 671.47

 MEAN 18.08 0.00 -0.02 532.98 -0.18 532.98 0.49 0.73

 HUB 15.21 0.00 -0.02 532.98 -0.18 532.98 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.57 46.36 5.21 671.44 857.40 4.69 495.78 482.83 0.74

 MEAN 47.95 42.30 5.65 590.68 795.73 4.69 495.78 482.83 0.74

 HUB 43.01 37.84 5.17 496.96 728.85 4.69 495.78 482.83 0.74

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 602.92 292.76 527.07 1111.25 0.54 2.33 2.04 9.02

 MEAN 18.01 619.56 309.93 536.47 1107.27 0.56 2.40 2.13 7.35

 HUB 15.22 675.34 396.67 546.57 1103.61 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.19 646.53 374.43 0.58 5981.93 0.92 0.91

 MEAN 588.45 604.46 278.52 0.55 5585.09 0.92 0.91 0.91 1.42

 HUB 497.39 555.77 100.71 0.50 6041.36 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.51 550.05 1.06 520.82 497.01 0.34

 MEAN 6.63 1.20 5.37 547.96 1.06 517.10 496.15 0.38

 HUB 6.72 1.22 5.24 550.36 1.06 513.69 497.22 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.05 35.39 31.50 3.89 0.93 0.37 1.40

 MEAN 30.02 27.44 23.50 3.94 0.92 0.36 1.63

 HUB 35.97 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 695.0513 310.7972 621.6924 1100.2803 0.6317 -0.1933 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6730 5.1165 510.6176 496.8402 0.4620 26.5614 30.6000 4.0386

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 586.2198 124.2828 572.8939 1112.2983 0.5270 0.1096 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6486 5.5151 521.8267 496.6447 491.5697 0.0285 0.2760

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 614.7243 0.0000 614.7243 1109.3397 0.5541 0.1771 0.5911

NASA/TM—2013-218094 J–188
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3921 519.0778 496.6137 0.0000 0.0600 0.0457 0.0160

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8696 6.6261 1.2004 549.4545 30.8395 257.9684 1.9998

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191829.969 0.431 604.766 546200.313 0.103929E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.900 EfDer = 0.999 SH = 0.105299E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.788 3744.103 6.626 549.454 1.000 1.000 0.980

 W Kg/sec = 25.358 Wdry = 55.782 WH2O = 0.006 lbm/sec H2O = 0.050g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 127.381 3637.810 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 113337.758 43771.980 1.463 545.479 372.896 424.468 1.138

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 498.66 -0.17 498.66 0.45 0.74 637.12

 MEAN 17.74 0.00 -0.02 498.66 -0.17 498.66 0.45 0.68 

 HUB 15.05 0.00 -0.02 498.66 -0.17 498.66 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.76 46.36 6.40 655.76 823.96 5.79 529.47 496.52 0.27 

 MEAN 49.30 43.40 5.90 579.58 764.71 5.79 529.47 496.52 0.27

 HUB 44.61 38.84 5.77 491.74 700.46 5.79 529.47 496.52 0.27

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 577.42 293.02 497.55 1145.16 0.50 2.26 1.98 8.75

 MEAN 17.51 592.20 308.77 505.34 1141.55 0.52 2.34 2.07 6.78

 HUB 14.85 644.76 389.59 513.74 1138.18 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.26 610.77 354.24 0.53 5808.14 0.92 0.91

 MEAN 572.00 569.78 263.23 0.50 5408.51 0.92 0.91 0.91 1.45

 HUB 485.20 522.56 95.61 0.46 5788.05 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.68 579.96 1.06 553.16 508.72 0.15

 MEAN 7.83 1.18 6.53 577.86 1.05 549.67 507.93 0.16

 HUB 7.92 1.20 6.39 579.86 1.06 546.44 508.72 0.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.49 35.45 31.50 3.95 0.93 0.38 1.40

 MEAN 31.43 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 37.17 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 657.8067 310.7941 579.7557 1136.0659 0.5790 -0.1747 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8816 6.2973 544.4531 508.4632 0.1814 28.1948 31.5000 3.3052

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 559.3256 122.0131 545.8552 1146.0768 0.4880 0.1164 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8611 6.6931 554.0847 508.3450 451.3937 0.0250 0.3016

 

NASA/TM—2013-218094 J–189
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 571.1782 0.0000 571.1782 1144.9354 0.4989 0.2091 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6285 553.0109 508.2993 0.0000 0.0600 0.0403 0.0689

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8768 7.8403 1.1832 579.2253 29.7720 246.1767 1.9083

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 185262.813 0.442 584.062 521475.000 0.106506E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.296 EfDer = 1.000 SH = 0.108471E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.788 3744.103 7.840 579.225 1.000 1.000 0.980

 W Kg/sec = 25.358 Wdry = 55.782 WH2O = 0.006 lbm/sec H2O = 0.059g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.533 3543.089 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99205.375 43771.922 1.586 513.330 323.593 395.845 1.223

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 463.82 -0.16 463.82 0.40 0.68 595.49

 MEAN 16.97 0.00 -0.02 463.82 -0.16 463.82 0.40 0.63

 HUB 14.32 0.00 -0.02 463.82 -0.16 463.82 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.61 46.36 7.25 629.29 781.88 7.02 561.94 508.25 0.12

 MEAN 50.10 43.80 6.30 554.49 723.03 7.02 561.94 508.25 0.12

 HUB 45.26 37.84 7.42 467.88 658.93 7.02 561.94 508.25 0.12

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 545.90 285.53 465.27 1176.15 0.46 2.16 1.89 8.34

 MEAN 16.57 557.19 295.71 472.24 1172.54 0.48 2.24 1.97 6.35

 HUB 13.89 602.83 365.07 479.72 1169.13 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 616.87 571.20 331.35 0.49 5393.87 0.92 0.91

 MEAN 541.53 532.39 245.81 0.45 4903.83 0.92 0.91 0.91 1.47

 HUB 453.83 487.86 88.77 0.42 5073.08 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.19 1.17 7.94 607.54 1.05 583.60 518.58 0.07

 MEAN 9.06 1.16 7.78 604.97 1.04 580.03 517.68 0.08

 HUB 9.10 1.16 7.61 605.86 1.05 576.66 518.01 0.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.54 35.46 31.50 3.96 0.93 0.40 1.40

 MEAN 32.05 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.27 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 602.0663 297.3763 523.4989 1169.4316 0.5148 -0.1205 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1033 7.6150 577.0082 518.0703 0.0852 29.5990 32.4000 2.8010

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 518.3566 116.2522 505.1524 1177.0397 0.4404 0.1430 2.2705

 

NASA/TM—2013-218094 J–190
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0877 7.9680 584.5416 517.9998 432.2457 0.0217 0.3242

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 514.1156 0.0000 514.1156 1177.3646 0.4367 0.2350 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9647 584.8954 517.9423 0.0000 0.0600 0.0393 0.1405

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8786 9.0641 1.1561 606.1227 26.8990 248.4414 1.9259

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 167465.750 0.440 527.955 515217.938 0.110081E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.617 EfDer = 1.000 SH = 0.113018E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.788 3744.103 9.064 606.122 1.000 1.000 0.980

 W Kg/sec = 25.358 Wdry = 55.781 WH2O = 0.006 lbm/sec H2O = 0.069g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.804 3463.583 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 88113.570 43771.844 1.780 509.668 286.350 384.739 1.344

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 414.92 -0.14 414.92 0.35 0.61 553.71

 MEAN 15.91 0.00 -0.02 414.92 -0.14 414.92 0.35 0.56

 HUB 13.07 0.00 -0.02 414.92 -0.14 414.92 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.28 47.36 7.92 598.58 728.44 8.34 592.30 517.92 0.06

 MEAN 51.42 44.80 6.62 519.93 665.31 8.34 592.30 517.92 0.06

 HUB 45.83 38.84 6.99 427.04 595.52 8.34 592.30 517.92 0.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 507.73 285.65 419.75 1204.62 0.42 2.05 1.78 7.43

 MEAN 15.50 512.27 283.53 426.65 1200.48 0.43 2.13 1.86 5.75

 HUB 12.59 546.05 331.47 433.94 1196.49 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 586.16 516.24 300.52 0.43 5127.11 0.92 0.91

 MEAN 506.36 481.34 222.83 0.40 4396.36 0.92 0.91 0.91 1.52

 HUB 411.36 441.23 79.89 0.37 4175.03 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.47 1.16 9.28 633.02 1.04 612.33 527.06 0.04

 MEAN 10.26 1.13 9.07 629.19 1.04 608.12 525.80 0.05

 HUB 10.20 1.13 8.86 628.03 1.04 604.09 525.42 0.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.24 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.61 27.58 23.50 4.08 0.93 0.41 1.64

 HUB 37.37 10.43 6.50 3.93 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 570.3395 288.7323 491.8545 1196.3169 0.4767 -0.1994 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2863 8.8218 603.9677 526.0556 0.0503 30.4141 33.0000 2.5859

 

NASA/TM—2013-218094 J–191
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 497.3902 113.5795 484.2486 1202.4943 0.4136 0.0532 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2618 9.1359 610.2202 525.9796 410.5396 0.0397 0.3383

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 481.8195 0.0000 481.8195 1203.6700 0.4003 0.2607 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2036 611.4459 525.9791 0.0000 0.0600 0.0389 0.1077

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8810 10.2629 1.1323 630.0800 23.9591 255.2690 1.9788

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 149244.734 0.434 470.511 523265.406 0.115329E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3184 Tt4 = 630.0800 T1 = 477.9180

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 946860.38 2985.0847 184.5854 2.4065 0.8609 4.7132 1.3184 37.3740

NASA/TM—2013-218094 J–192
 100μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.825 EfDer = 0.984 SH = 0.443884E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.105 3888.739 4.265 457.739 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.102 WH2O = 0.003 lbm/sec H2O = 0.016g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.336 4139.589 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 168221.516 49514.516 1.390 831.557 598.111 619.754 1.036

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 485.51 -0.17 485.51 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 485.51 -0.17 485.51 0.48 0.74

 HUB 12.51 0.00 -0.02 485.51 -0.17 485.51 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.27 50.47 4.80 700.09 852.11 3.66 438.78 448.38 3.34

 MEAN 50.02 47.20 2.82 578.95 755.71 3.66 438.78 448.38 3.34

 HUB 41.18 38.62 2.56 424.53 645.05 3.66 438.78 448.38 3.34

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 728.15 352.65 637.06 1038.53 0.70 7.29 6.52 16.04

 MEAN 18.04 773.29 411.15 654.94 1033.16 0.75 7.43 6.80 12.53

 HUB 15.00 914.43 580.07 706.89 1019.12 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 700.09 725.64 347.44 0.70 7278.69 0.92 0.90

 MEAN 612.06 685.06 200.92 0.66 7418.28 0.92 0.90 0.90 1.21

 HUB 509.03 710.45 71.03 0.70 8703.12 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 497.48 1.09 454.83 473.89 1.66

 MEAN 5.63 1.32 3.90 498.24 1.09 450.14 474.44 2.01

 HUB 5.89 1.38 3.51 505.25 1.10 437.99 478.89 3.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.97 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.12 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.37 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 836.5803 410.3469 729.0281 1026.1238 0.8153 -0.1085 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6891 3.6924 444.0253 475.7800 2.5821 29.3738 35.4000 6.0262

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 682.0183 166.8425 661.2961 1047.7080 0.6510 0.2262 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6275 4.2469 462.9077 475.1944 554.9116 0.0426 0.3572

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 684.4385 0.0000 684.4385 1047.3906 0.6535 0.2507 1.3089

NASA/TM—2013-218094 J–193
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.1929 462.6455 475.0654 0.0000 0.0600 0.0744 0.1976

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8211 5.5675 1.3055 500.3240 42.5848 238.3450 1.8476

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 264725.375 0.540 944.044 727643.000 0.445085E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.415 EfDer = 0.989 SH = 0.445085E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.105 3888.739 5.568 500.324 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.102 WH2O = 0.003 lbm/sec H2O = 0.018g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.640 3959.508 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 147273.047 49514.516 1.233 590.487 478.994 468.502 0.978

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 598.58 -0.21 598.58 0.57 0.87 710.05

 MEAN 18.08 0.00 -0.02 598.58 -0.21 598.58 0.57 0.81

 HUB 15.21 0.00 -0.02 598.58 -0.21 598.58 0.57 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.37 46.36 3.01 697.38 919.20 4.49 471.51 474.95 0.85

 MEAN 45.71 42.30 3.41 613.50 857.28 4.49 471.51 474.95 0.85

 HUB 40.78 37.84 2.94 516.16 790.53 4.49 471.51 474.95 0.85

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 648.44 273.76 587.82 1085.62 0.60 2.33 2.04 9.02

 MEAN 18.01 668.25 299.53 597.36 1082.15 0.62 2.40 2.13 7.35

 HUB 15.22 729.52 403.24 607.94 1079.05 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 692.97 721.99 419.21 0.67 5594.33 0.92 0.90

 MEAN 611.18 673.77 311.65 0.62 5398.31 0.92 0.90 0.90 1.37

 HUB 516.60 618.42 113.36 0.57 6141.63 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.21 5.33 530.86 1.06 497.04 490.41 0.35

 MEAN 6.72 1.21 5.21 529.79 1.06 493.88 489.93 0.39

 HUB 6.89 1.24 5.09 533.85 1.07 491.05 491.87 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 24.97 35.50 31.50 4.00 0.93 0.32 1.40

 MEAN 26.63 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.56 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 767.1641 300.3741 705.9150 1071.4438 0.7160 -0.2389 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7753 4.8329 484.1721 490.8008 0.5316 23.0503 30.6000 7.5497

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 663.8439 140.7396 648.7535 1084.5289 0.6121 0.0168 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7239 5.2368 496.0599 490.5658 491.5697 0.0425 0.2181

 

NASA/TM—2013-218094 J–194
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 707.5630 0.0000 707.5630 1079.2306 0.6556 0.0936 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0147 491.2417 490.4802 0.0000 0.0600 0.0762 -0.1236

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8212 6.6706 1.1981 531.5005 31.1769 281.7019 2.1837

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193870.453 0.404 691.367 658809.688 0.445085E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.772 EfDer = 0.991 SH = 0.445085E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.105 3888.739 6.671 531.500 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.102 WH2O = 0.003 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.770 3841.625 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 126856.406 49514.516 1.324 545.479 412.067 424.468 1.030

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 558.14 -0.19 558.14 0.51 0.80 672.82

 MEAN 17.74 0.00 -0.02 558.14 -0.19 558.14 0.51 0.75

 HUB 15.05 0.00 -0.02 558.14 -0.19 558.14 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.67 46.36 4.31 681.09 880.72 5.60 506.45 490.37 0.25

 MEAN 47.17 43.40 3.77 601.97 821.05 5.60 506.45 490.37 0.25

 HUB 42.47 38.84 3.63 510.73 756.68 5.60 506.45 490.37 0.25

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 618.97 276.65 553.70 1121.64 0.55 2.26 1.98 8.75

 MEAN 17.51 636.91 300.22 561.71 1118.42 0.57 2.34 2.07 6.78

 HUB 14.85 694.91 396.62 570.60 1115.50 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.27 680.51 395.62 0.61 5484.27 0.92 0.91

 MEAN 594.10 633.94 293.87 0.57 5259.27 0.92 0.91 0.91 1.39

 HUB 503.94 580.61 107.32 0.52 5892.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.99 1.20 6.51 561.43 1.06 530.62 503.48 0.12

 MEAN 7.93 1.19 6.38 560.20 1.05 527.58 502.98 0.14

 HUB 8.09 1.21 6.25 563.66 1.06 524.83 504.43 0.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.55 35.55 31.50 4.05 0.93 0.34 1.40

 MEAN 28.12 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.80 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 719.0923 302.1923 652.5133 1110.5192 0.6475 -0.2069 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9892 6.0468 520.1934 503.6337 0.1659 24.8498 31.5000 6.6502

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 629.6356 137.3508 614.4720 1120.8344 0.5618 0.0307 2.3726

 

NASA/TM—2013-218094 J–195
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9476 6.4317 529.8911 503.4904 451.3937 0.0356 0.2512

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 647.1346 0.0000 647.1346 1118.9131 0.5784 0.1404 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3195 528.0984 503.3997 0.0000 0.0600 0.0615 -0.0383

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8429 7.9057 1.1852 561.7632 30.2630 267.2842 2.0720

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 188246.234 0.417 671.310 622596.438 0.445085E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.347 EfDer = 0.994 SH = 0.445085E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.105 3888.739 7.906 561.763 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.102 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 122.113 3736.718 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110375.500 49514.516 1.436 513.330 357.471 395.845 1.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 516.04 -0.18 516.04 0.46 0.74 628.03

 MEAN 16.97 0.00 -0.02 516.04 -0.18 516.04 0.46 0.68

 HUB 14.32 0.00 -0.02 516.04 -0.18 516.04 0.46 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.72 46.36 5.36 653.60 832.90 6.87 540.36 503.36 0.09

 MEAN 48.15 43.80 4.35 575.91 773.42 6.87 540.36 503.36 0.09

 HUB 43.29 37.84 5.45 485.96 708.96 6.87 540.36 503.36 0.09

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 582.74 272.86 514.91 1154.85 0.50 2.16 1.89 8.34

 MEAN 16.57 597.26 289.50 522.40 1151.45 0.52 2.24 1.97 6.35

 HUB 13.89 648.17 372.33 530.56 1148.29 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 640.70 632.81 367.84 0.55 5155.07 0.92 0.91

 MEAN 562.45 589.41 272.95 0.51 4801.07 0.92 0.91 0.91 1.42

 HUB 471.37 539.72 99.03 0.47 5174.24 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.29 1.18 7.82 589.89 1.05 562.59 514.39 0.05

 MEAN 9.19 1.16 7.67 587.95 1.05 559.28 513.67 0.06

 HUB 9.30 1.18 7.51 589.99 1.05 556.22 514.45 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.92 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 28.99 27.59 23.50 4.09 0.92 0.35 1.62

 HUB 35.06 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 651.2548 291.1232 582.5634 1147.1807 0.5677 -0.1379 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2429 7.4475 555.1934 514.1461 0.0643 26.5526 32.4000 5.8474

 

NASA/TM—2013-218094 J–196
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 577.7452 129.5714 563.0283 1154.6599 0.5004 0.0717 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2122 7.7808 562.4527 514.0582 432.2457 0.0293 0.2811

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 573.1793 0.0000 573.1793 1155.0710 0.4962 0.1832 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7765 562.8777 513.9896 0.0000 0.0600 0.0481 0.0690

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8607 9.1821 1.1615 589.2758 27.5132 267.6995 2.0752

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171212.063 0.417 610.564 609620.375 0.445085E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 4.944 EfDer = 0.997 SH = 0.445085E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 63.105 3888.739 9.182 589.276 1.000 1.000 0.980

 W Kg/sec = 28.684 Wdry = 63.102 WH2O = 0.003 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.681 3648.443 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 97131.344 49514.516 1.617 509.668 315.243 384.739 1.220

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 457.39 -0.16 457.39 0.39 0.66 583.27

 MEAN 15.91 0.00 -0.02 457.39 -0.16 457.39 0.39 0.61

 HUB 13.07 0.00 -0.02 457.39 -0.16 457.39 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.66 47.36 6.30 621.70 771.95 8.27 572.47 513.97 0.04

 MEAN 49.74 44.80 4.94 540.02 707.81 8.27 572.47 513.97 0.04

 HUB 44.13 38.84 5.29 443.54 637.24 8.27 572.47 513.97 0.04

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 537.86 278.41 460.20 1185.82 0.45 2.05 1.78 7.43

 MEAN 15.50 545.77 280.70 468.05 1181.61 0.46 2.13 1.86 5.75

 HUB 12.59 584.63 338.93 476.36 1177.61 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 608.81 566.52 330.40 0.48 4997.50 0.92 0.91

 MEAN 525.92 528.40 245.22 0.45 4352.73 0.92 0.91 0.91 1.47

 HUB 427.25 484.48 88.32 0.41 4269.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.67 1.16 9.28 616.52 1.05 593.28 523.82 0.03

 MEAN 10.47 1.14 9.06 613.01 1.04 589.08 522.59 0.03

 HUB 10.44 1.14 8.84 612.55 1.04 585.09 522.44 0.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.17 35.68 31.50 4.18 0.93 0.39 1.40

 MEAN 30.95 27.65 23.50 4.15 0.92 0.37 1.64

 HUB 35.43 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 613.5728 285.8502 542.9191 1176.2455 0.5216 -0.2187 2.0437

 

NASA/TM—2013-218094 J–197
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4942 8.7380 583.7910 522.8988 0.0330 27.7671 33.0000 5.2329

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 550.4866 125.7041 535.9422 1182.1780 0.4657 -0.0247 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4485 9.0229 589.6885 522.7907 410.5396 0.0513 0.3017

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 531.8795 0.0000 531.8795 1183.7756 0.4493 0.2175 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1199 591.3085 522.8050 0.0000 0.0600 0.0459 0.0416

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8684 10.4564 1.1388 614.0286 24.7535 271.7440 2.1065

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 154114.000 0.416 549.590 613702.688 0.445090E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3414 Tt4 = 614.0286 T1 = 457.7394

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 972168.13 3466.8740 204.3360 2.4518 0.8224 2.8245 1.3414 37.3740

NASA/TM—2013-218094 J–198
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.054 EfDer = 0.993 SH = 0.444985E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.953 3728.445 4.265 457.739 1.000 1.000 0.980

 W Kg/sec = 26.797 Wdry = 58.951 WH2O = 0.003 lbm/sec H2O = 0.016g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 190.892 3968.956 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154378.781 46256.785 1.488 831.557 558.760 619.754 1.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.56 -0.15 445.56 0.44 0.79 714.51

 MEAN 17.06 0.00 -0.02 445.56 -0.15 445.56 0.44 0.70

 HUB 12.51 0.00 -0.02 445.56 -0.15 445.56 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.43 50.47 5.96 671.23 805.78 3.75 441.77 448.34 2.94

 MEAN 51.25 47.20 4.05 555.08 711.91 3.75 441.77 448.34 2.94

 HUB 42.42 38.62 3.80 407.04 603.60 3.75 441.77 448.34 2.94

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 679.65 355.41 579.31 1043.25 0.65 7.29 6.52 16.04

 MEAN 18.04 719.42 404.37 595.02 1037.92 0.69 7.43 6.80 12.53

 HUB 15.00 838.64 551.01 632.21 1026.59 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 671.23 659.81 315.83 0.63 7335.25 0.92 0.91

 MEAN 586.84 622.37 182.47 0.60 7295.77 0.92 0.91 0.91 1.26

 HUB 488.05 635.34 62.96 0.62 8267.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.20 496.14 1.08 458.98 473.07 1.42

 MEAN 5.56 1.30 4.04 495.93 1.08 454.30 473.03 1.71

 HUB 5.75 1.35 3.72 501.01 1.09 444.44 476.23 2.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.53 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.20 17.05 12.70 4.35 0.92 0.26 2.22

 HUB 41.07 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 768.5572 403.5804 654.0665 1033.2010 0.7439 -0.0897 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6060 3.8981 450.1783 474.1157 2.0096 31.6759 35.4000 3.7241

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 617.0998 150.9614 598.3500 1052.3896 0.5864 0.2666 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5685 4.4242 467.0609 473.7354 554.9116 0.0329 0.3882

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 614.4968 0.0000 614.4968 1052.6633 0.5838 0.2980 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4070 467.3215 473.6611 0.0000 0.0600 0.0530 0.2561

NASA/TM—2013-218094 J–199
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8557 5.5357 1.2981 497.6919 39.9530 229.6383 1.7801

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 248374.625 0.551 827.460 667766.375 0.446285E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.908 EfDer = 0.997 SH = 0.446285E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.953 3728.445 5.536 497.692 1.000 1.000 0.980

 W Kg/sec = 26.797 Wdry = 58.951 WH2O = 0.003 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 153.345 3806.323 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 134017.313 46256.781 1.316 590.487 448.863 468.502 1.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 544.71 -0.19 544.71 0.51 0.81 682.58

 MEAN 18.08 0.00 -0.02 544.71 -0.19 544.71 0.51 0.76

 HUB 15.21 0.00 -0.02 544.71 -0.19 544.71 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.84 46.36 4.48 668.63 862.57 4.63 473.83 473.59 0.80

 MEAN 47.21 42.30 4.91 588.21 801.82 4.63 473.83 473.59 0.80

 HUB 42.27 37.84 4.43 494.89 736.07 4.63 473.83 473.59 0.80

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 607.12 282.00 537.65 1086.88 0.56 2.33 2.04 9.02

 MEAN 18.01 624.62 301.59 546.99 1083.11 0.58 2.40 2.13 7.35

 HUB 15.22 681.33 392.27 557.08 1079.68 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 664.40 659.77 382.40 0.61 5762.26 0.92 0.91

 MEAN 585.99 616.51 284.40 0.57 5434.94 0.92 0.91 0.91 1.40

 HUB 495.31 566.52 103.03 0.52 5974.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.46 527.85 1.06 498.20 489.17 0.34

 MEAN 6.65 1.20 5.33 526.14 1.06 494.76 488.36 0.38

 HUB 6.77 1.22 5.20 528.96 1.06 491.62 489.75 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.68 35.42 31.50 3.92 0.93 0.35 1.40

 MEAN 28.87 27.47 23.50 3.97 0.92 0.35 1.63

 HUB 35.15 10.48 6.50 3.98 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 705.1912 302.4327 637.0471 1075.2902 0.6558 -0.2059 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7041 5.0390 487.6577 489.1227 0.4810 25.3956 30.6000 5.2044

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 600.3220 127.2725 586.6756 1087.3662 0.5521 0.0808 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6732 5.4383 498.6663 488.9637 491.5697 0.0322 0.2579

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 631.7783 0.0000 631.7783 1083.9473 0.5828 0.1524 0.5911

NASA/TM—2013-218094 J–200
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2928 495.5522 488.9169 0.0000 0.0600 0.0533 -0.0237

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8583 6.6438 1.2002 527.6478 29.9562 265.4798 2.0580

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186282.938 0.422 620.601 601618.438 0.446285E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.203 EfDer = 0.998 SH = 0.446285E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.953 3728.445 6.644 527.648 1.000 1.000 0.980

 W Kg/sec = 26.797 Wdry = 58.951 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 131.559 3696.697 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115671.336 46256.781 1.416 545.479 385.106 424.468 1.102

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 508.93 -0.18 508.93 0.46 0.76 647.43

 MEAN 17.74 0.00 -0.02 508.93 -0.18 508.93 0.46 0.70

 HUB 15.05 0.00 -0.02 508.93 -0.18 508.93 0.46 0.64

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.08 46.36 5.72 653.01 828.05 5.74 506.82 488.85 0.26

 MEAN 48.60 43.40 5.20 577.15 769.62 5.74 506.82 488.85 0.26

 HUB 43.91 38.84 5.07 489.68 706.38 5.74 506.82 488.85 0.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 580.71 283.21 506.96 1120.87 0.52 2.26 1.98 8.75

 MEAN 17.51 596.34 301.14 514.72 1117.43 0.53 2.34 2.07 6.78

 HUB 14.85 649.85 385.51 523.15 1114.25 0.58 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 644.55 622.56 361.34 0.56 5613.92 0.92 0.91

 MEAN 569.61 580.53 268.46 0.52 5275.08 0.92 0.91 0.91 1.43

 HUB 483.17 532.18 97.66 0.48 5727.45 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.95 1.20 6.64 557.02 1.06 529.91 502.02 0.13

 MEAN 7.87 1.18 6.50 555.25 1.05 526.65 501.28 0.14

 HUB 7.98 1.20 6.35 557.62 1.06 523.66 502.30 0.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.19 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.33 27.55 23.50 4.05 0.92 0.37 1.62

 HUB 36.39 10.57 6.50 4.07 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 665.5081 303.1187 592.4695 1111.4030 0.5988 -0.1839 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9178 6.2313 521.0226 501.8591 0.1665 27.0951 31.5000 4.4049

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 571.6203 124.6951 557.8538 1121.3236 0.5098 0.0897 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8923 6.6242 530.3593 501.7603 451.3937 0.0277 0.2857

 

NASA/TM—2013-218094 J–201
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 584.4315 0.0000 584.4315 1120.0437 0.5218 0.1892 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5504 529.1714 501.7095 0.0000 0.0600 0.0445 0.0383

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8701 7.8683 1.1843 556.6277 28.9803 252.7865 1.9596

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 180268.500 0.434 600.564 572638.500 0.446285E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.664 EfDer = 0.999 SH = 0.446285E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.953 3728.445 7.868 556.628 1.000 1.000 0.980

 W Kg/sec = 26.797 Wdry = 58.951 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.096 3599.179 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 101025.945 46256.781 1.537 513.330 334.002 395.845 1.185

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 472.33 -0.16 472.33 0.42 0.69 604.91

 MEAN 16.97 0.00 -0.02 472.33 -0.16 472.33 0.42 0.64

 HUB 14.32 0.00 -0.02 472.33 -0.16 472.33 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.00 46.36 6.64 626.66 784.86 6.99 538.70 501.68 0.10

 MEAN 49.46 43.80 5.66 552.17 726.75 6.99 538.70 501.68 0.10

 HUB 44.62 37.84 6.78 465.93 663.58 6.99 538.70 501.68 0.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 548.25 277.07 473.08 1152.03 0.48 2.16 1.89 8.34

 MEAN 16.57 560.41 289.06 480.11 1148.53 0.49 2.24 1.97 6.35

 HUB 13.89 607.03 361.47 487.67 1145.25 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 614.30 580.97 337.22 0.50 5234.30 0.92 0.91

 MEAN 539.26 541.39 250.20 0.47 4793.63 0.92 0.91 0.91 1.45

 HUB 451.94 495.99 90.47 0.43 5023.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.23 1.17 7.92 584.00 1.05 559.85 512.70 0.06

 MEAN 9.11 1.16 7.75 581.70 1.05 556.46 511.81 0.06

 HUB 9.17 1.17 7.59 582.90 1.05 553.28 512.28 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.36 35.48 31.50 3.98 0.93 0.38 1.40

 MEAN 31.05 27.53 23.50 4.03 0.92 0.38 1.62

 HUB 36.55 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 607.1824 290.6874 533.0773 1145.1675 0.5302 -0.1256 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1538 7.5767 553.2418 512.2413 0.0697 28.6037 32.4000 3.7963

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 528.0648 118.4295 514.6133 1152.6138 0.4581 0.1205 2.2705

 

NASA/TM—2013-218094 J–202
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1346 7.9245 560.4595 512.1803 432.2457 0.0236 0.3100

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 523.7771 0.0000 523.7771 1152.9640 0.4543 0.2184 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9211 560.8241 512.1234 0.0000 0.0600 0.0415 0.1181

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8745 9.1093 1.1577 582.8680 26.2409 254.4345 1.9724

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 163290.781 0.433 544.003 564287.438 0.446285E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.066 EfDer = 0.999 SH = 0.446285E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.953 3728.445 9.109 582.868 1.000 1.000 0.980

 W Kg/sec = 26.797 Wdry = 58.951 WH2O = 0.003 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 100.848 3517.230 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 89490.234 46256.781 1.726 509.668 295.238 384.739 1.303

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 421.40 -0.15 421.40 0.36 0.63 562.29

 MEAN 15.91 0.00 -0.02 421.40 -0.15 421.40 0.36 0.58

 HUB 13.07 0.00 -0.02 421.40 -0.15 421.40 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.75 47.36 7.39 596.07 730.11 8.33 568.60 512.11 0.05

 MEAN 50.87 44.80 6.07 517.76 667.69 8.33 568.60 512.11 0.05

 HUB 45.27 38.84 6.43 425.26 598.79 8.33 568.60 512.11 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 508.78 278.71 425.66 1180.76 0.43 2.05 1.78 7.43

 MEAN 15.50 514.34 278.03 432.72 1176.67 0.44 2.13 1.86 5.75

 HUB 12.59 549.18 328.39 440.18 1172.74 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 583.71 523.65 305.01 0.44 5002.63 0.92 0.91

 MEAN 504.24 488.29 226.22 0.41 4311.07 0.92 0.91 0.91 1.50

 HUB 409.64 447.62 81.25 0.38 4136.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.54 1.16 9.29 609.02 1.04 588.22 521.81 0.03

 MEAN 10.33 1.13 9.08 605.41 1.04 584.15 520.51 0.03

 HUB 10.28 1.13 8.86 604.49 1.04 580.26 520.19 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.22 35.62 31.50 4.12 0.93 0.42 1.40

 MEAN 32.72 27.60 23.50 4.10 0.93 0.39 1.64

 HUB 36.72 10.46 6.50 3.96 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 574.3493 283.1256 499.7170 1172.2422 0.4900 -0.2053 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3579 8.8083 579.8094 520.7915 0.0372 29.5347 33.0000 3.4653

 

NASA/TM—2013-218094 J–203
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 505.7049 115.4781 492.3436 1178.2490 0.4292 0.0286 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3282 9.1146 585.7643 520.7181 410.5396 0.0427 0.3260

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 489.5446 0.0000 489.5446 1179.5245 0.4150 0.2464 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1901 587.0581 520.7215 0.0000 0.0600 0.0407 0.0864

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8780 10.3309 1.1341 606.3063 23.4391 260.5441 2.0197

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 145920.641 0.428 486.134 571708.250 0.446290E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3246 Tt4 = 606.3063 T1 = 457.7392

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 924137.50 3078.7629 190.8920 2.4224 0.8520 4.0540 1.3246 37.3740

NASA/TM—2013-218094 J–204
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.489 EfDer = 0.995 SH = 0.445307E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.632 3683.296 4.265 457.739 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.629 WH2O = 0.003 lbm/sec H2O = 0.016g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 186.614 3920.895 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 150148.797 45220.121 1.522 831.557 546.238 619.754 1.135

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 433.35 -0.15 433.35 0.42 0.77 705.86

 MEAN 17.06 0.00 -0.02 433.35 -0.15 433.35 0.42 0.68

 HUB 12.51 0.00 -0.02 433.35 -0.15 433.35 0.42 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.84 50.47 6.37 663.11 792.28 3.78 442.63 448.32 2.84

 MEAN 51.69 47.20 4.49 548.36 699.04 3.78 442.63 448.32 2.84

 HUB 42.87 38.62 4.25 402.11 591.27 3.78 442.63 448.32 2.84

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 665.75 356.75 562.10 1044.59 0.64 7.29 6.52 16.04

 MEAN 18.04 703.86 402.76 577.24 1039.25 0.68 7.43 6.80 12.53

 HUB 15.00 817.54 542.93 611.23 1028.51 0.79 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 663.11 640.16 306.36 0.61 7362.73 0.92 0.91

 MEAN 579.73 603.76 176.97 0.58 7266.81 0.92 0.91 0.91 1.28

 HUB 482.14 614.24 60.79 0.60 8145.81 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.24 495.81 1.08 460.16 472.87 1.35

 MEAN 5.54 1.30 4.09 495.32 1.08 455.46 472.66 1.63

 HUB 5.71 1.34 3.78 499.86 1.09 446.10 475.52 2.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.40 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 34.91 17.04 12.70 4.34 0.92 0.27 2.22

 HUB 41.61 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 749.6251 401.9818 632.7310 1035.0525 0.7242 -0.0849 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5838 3.9534 451.7950 473.6829 1.8842 32.4283 35.4000 2.9717

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 598.1996 146.3379 580.0241 1053.6848 0.5677 0.2797 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5514 4.4727 468.2130 473.3440 554.9116 0.0308 0.3981

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 594.9142 0.0000 594.9142 1054.0227 0.5644 0.3117 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4615 468.5308 473.2813 0.0000 0.0600 0.0482 0.2726

NASA/TM—2013-218094 J–205
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8635 5.5240 1.2953 496.9961 39.2573 226.6933 1.7573

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 244052.203 0.555 794.838 649469.438 0.446627E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.396 EfDer = 0.998 SH = 0.446627E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.632 3683.296 5.524 496.996 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.629 WH2O = 0.003 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.122 3762.862 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 130151.828 45220.121 1.344 590.487 439.428 468.502 1.066

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 528.99 -0.18 528.99 0.50 0.80 674.78

 MEAN 18.08 0.00 -0.02 528.99 -0.18 528.99 0.50 0.74

 HUB 15.21 0.00 -0.02 528.99 -0.18 528.99 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.32 46.36 4.96 660.54 846.39 4.67 474.49 473.22 0.78

 MEAN 47.70 42.30 5.40 581.09 785.94 4.67 474.49 473.22 0.78

 HUB 42.75 37.84 4.91 488.89 720.44 4.67 474.49 473.22 0.78

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 595.40 284.75 522.90 1087.27 0.55 2.33 2.04 9.02

 MEAN 18.01 612.10 302.50 532.13 1083.43 0.56 2.40 2.13 7.35

 HUB 15.22 667.38 389.31 542.06 1079.90 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 656.36 641.49 371.61 0.59 5818.34 0.92 0.91 

 MEAN 578.89 599.63 276.39 0.55 5451.23 0.92 0.91 0.91 1.42

 HUB 489.31 551.21 100.00 0.51 5929.28 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.49 527.08 1.06 498.57 488.83 0.34

 MEAN 6.63 1.20 5.35 525.18 1.06 495.05 487.93 0.38

 HUB 6.74 1.22 5.22 527.65 1.06 491.83 489.16 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.57 35.40 31.50 3.90 0.93 0.36 1.40

 MEAN 29.62 27.45 23.50 3.95 0.92 0.36 1.63

 HUB 35.69 10.45 6.50 3.95 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 688.0851 303.3448 617.6107 1076.2865 0.6393 -0.1973 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6807 5.0906 488.5627 488.6660 0.4686 26.1584 30.6000 4.4416

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 582.3045 123.4527 569.0676 1088.1294 0.5351 0.0997 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6544 5.4887 499.3682 488.5233 491.5697 0.0297 0.2697

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 611.2794 0.0000 611.2794 1085.0793 0.5633 0.1687 0.5911

NASA/TM—2013-218094 J–206
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3589 496.5897 488.4849 0.0000 0.0600 0.0480 0.0028

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8662 6.6298 1.2002 526.6359 29.6402 260.5184 2.0195

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 184318.453 0.428 600.295 584458.000 0.446627E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.657 EfDer = 0.999 SH = 0.446627E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.632 3683.296 6.630 526.636 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.629 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 128.760 3655.439 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112458.344 45220.121 1.447 545.479 376.911 424.468 1.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 494.79 -0.17 494.79 0.45 0.74 640.21

 MEAN 17.74 0.00 -0.02 494.79 -0.17 494.79 0.45 0.69

 HUB 15.05 0.00 -0.02 494.79 -0.17 494.79 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.52 46.36 6.16 645.11 813.14 5.78 506.95 488.43 0.26

 MEAN 49.06 43.40 5.66 570.16 755.05 5.78 506.95 488.43 0.26

 HUB 44.36 38.84 5.52 483.75 692.10 5.78 506.95 488.43 0.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 570.01 285.26 493.50 1120.69 0.51 2.26 1.98 8.75

 MEAN 17.51 584.88 301.55 501.15 1117.19 0.52 2.34 2.07 6.78

 HUB 14.85 636.98 382.40 509.42 1113.95 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 636.75 605.88 351.49 0.54 5654.35 0.92 0.91

 MEAN 562.71 565.12 261.16 0.51 5282.07 0.92 0.91 0.91 1.44

 HUB 477.32 518.19 94.92 0.47 5681.27 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.66 555.86 1.06 529.74 501.61 0.13

 MEAN 7.84 1.18 6.52 553.94 1.05 526.43 500.79 0.14

 HUB 7.94 1.20 6.38 556.00 1.06 523.38 501.69 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.03 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 31.04 27.53 23.50 4.03 0.92 0.37 1.62

 HUB 36.89 10.55 6.50 4.05 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 650.6865 303.5256 575.5563 1111.6241 0.5853 -0.1778 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8892 6.2732 521.2301 501.3577 0.1665 27.8054 31.5000 3.6946

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 555.3265 121.1407 541.9524 1121.4445 0.4952 0.1070 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8672 6.6672 530.4749 501.2684 451.3937 0.0259 0.2960

 

NASA/TM—2013-218094 J–207
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 567.2536 0.0000 567.2536 1120.2856 0.5063 0.2025 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6004 529.4011 501.2236 0.0000 0.0600 0.0413 0.0588

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8751 7.8459 1.1834 555.2670 28.6314 248.4798 1.9262

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 178098.109 0.439 580.036 557417.438 0.446627E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.072 EfDer = 0.999 SH = 0.446627E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.632 3683.296 7.846 555.267 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.629 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 111.719 3559.950 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 98374.984 45220.121 1.570 513.330 327.045 395.845 1.210 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 459.94 -0.16 459.94 0.41 0.68 598.32

 MEAN 16.97 0.00 -0.02 459.94 -0.16 459.94 0.41 0.63

 HUB 14.32 0.00 -0.02 459.94 -0.16 459.94 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.40 46.36 7.04 619.07 771.35 7.01 538.26 501.19 0.10

 MEAN 49.87 43.80 6.07 545.49 713.63 7.01 538.26 501.19 0.10

 HUB 45.03 37.84 7.19 460.29 650.81 7.01 538.26 501.19 0.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 538.67 278.30 461.21 1151.27 0.47 2.16 1.89 8.34

 MEAN 16.57 550.10 288.99 468.08 1147.76 0.48 2.24 1.97 6.35

 HUB 13.89 595.43 358.42 475.46 1144.45 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 606.86 566.27 328.55 0.49 5257.44 0.92 0.91

 MEAN 532.73 527.74 243.74 0.46 4792.40 0.92 0.91 0.91 1.47

 HUB 446.46 483.55 88.04 0.42 4980.76 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.19 1.17 7.93 582.43 1.05 559.11 512.20 0.06

 MEAN 9.07 1.16 7.76 580.03 1.04 555.71 511.27 0.07

 HUB 9.12 1.16 7.60 581.00 1.05 552.51 511.66 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.11 35.47 31.50 3.97 0.93 0.39 1.40

 MEAN 31.69 27.51 23.50 4.01 0.93 0.38 1.62

 HUB 37.01 10.49 6.50 3.99 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 594.9626 290.6171 519.1553 1144.6168 0.5198 -0.1223 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1141 7.5982 552.7083 511.6854 0.0711 29.2396 32.4000 3.1604

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 514.1615 115.3114 501.0642 1152.0494 0.4463 0.1349 2.2705

 

NASA/TM—2013-218094 J–208
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0974 7.9486 559.9101 511.6302 432.2457 0.0223 0.3190

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 509.9658 0.0000 509.9658 1152.3822 0.4425 0.2289 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9452 560.2574 511.5760 0.0000 0.0600 0.0400 0.1325

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8773 9.0732 1.1564 581.1542 25.8879 250.5675 1.9424

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161092.875 0.437 524.653 550260.813 0.446627E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.414 EfDer = 1.000 SH = 0.446627E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 57.632 3683.296 9.073 581.154 1.000 1.000 0.980

 W Kg/sec = 26.196 Wdry = 57.629 WH2O = 0.003 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 98.834 3479.759 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 87313.414 45220.121 1.761 509.668 289.342 384.739 1.330

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 411.15 -0.14 411.15 0.35 0.62 556.30

 MEAN 15.91 0.00 -0.02 411.15 -0.14 411.15 0.35 0.57

 HUB 13.07 0.00 -0.02 411.15 -0.14 411.15 0.35 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.08 47.36 7.72 588.86 718.31 8.33 567.57 511.56 0.05

 MEAN 51.21 44.80 6.41 511.49 656.36 8.33 567.57 511.56 0.05

 HUB 45.63 38.84 6.79 420.11 587.93 8.33 567.57 511.56 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 500.65 278.88 415.78 1179.41 0.42 2.05 1.78 7.43

 MEAN 15.50 505.50 277.34 422.62 1175.34 0.43 2.13 1.86 5.75

 HUB 12.59 539.17 325.49 429.85 1171.44 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 576.64 511.41 297.76 0.43 5005.68 0.92 0.91

 MEAN 498.14 476.82 220.80 0.41 4300.39 0.92 0.91 0.91 1.51

 HUB 404.68 437.08 79.19 0.37 4099.71 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.49 1.16 9.28 607.01 1.04 586.87 521.21 0.03

 MEAN 10.28 1.13 9.06 603.36 1.04 582.83 519.90 0.04

 HUB 10.22 1.13 8.85 602.33 1.04 578.97 519.53 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.85 35.61 31.50 4.11 0.93 0.43 1.40

 MEAN 33.27 27.58 23.50 4.08 0.93 0.40 1.64

 HUB 37.13 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 563.3907 282.4274 487.4872 1171.1617 0.4811 -0.2015 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3016 8.8106 578.7369 520.1708 0.0384 30.0860 33.0000 2.9140

 

NASA/TM—2013-218094 J–209
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 493.1234 112.6051 480.0945 1177.1814 0.4189 0.0442 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2755 9.1211 584.7000 520.1050 410.5396 0.0407 0.3336

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 477.5830 0.0000 477.5830 1178.3774 0.4053 0.2553 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1912 585.9135 520.1062 0.0000 0.0600 0.0395 0.0998

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 10.2770 1.1327 604.2328 23.0793 257.2093 1.9939

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 143678.422 0.432 467.937 558447.875 0.446627E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3200 Tt4 = 604.2328 T1 = 457.7392

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 911240.06 2967.7598 186.6139 2.4098 0.8583 4.4894 1.3200 37.3740

NASA/TM—2013-218094 J–210
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.818 EfDer = 0.996 SH = 0.445566E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.680 3652.568 4.265 457.739 1.000 1.000 0.980

 W Kg/sec = 25.764 Wdry = 56.678 WH2O = 0.003 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 183.532 3888.184 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 147147.531 44473.305 1.548 831.557 537.217 619.754 1.154

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 424.69 -0.15 424.69 0.41 0.76 699.97

 MEAN 17.06 0.00 -0.02 424.69 -0.15 424.69 0.41 0.67

 HUB 12.51 0.00 -0.02 424.69 -0.15 424.69 0.41 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.15 50.47 6.68 657.57 782.92 3.80 443.23 448.32 2.77

 MEAN 52.02 47.20 4.82 543.79 690.09 3.80 443.23 448.32 2.77

 HUB 43.21 38.62 4.59 398.75 582.65 3.80 443.23 448.32 2.77

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 656.16 357.87 549.98 1045.52 0.63 7.29 6.52 16.04

 MEAN 18.04 693.10 401.82 564.74 1040.17 0.67 7.43 6.80 12.53

 HUB 15.00 803.06 537.44 596.71 1029.79 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 657.57 626.34 299.70 0.60 7385.92 0.92 0.91

 MEAN 574.89 590.66 173.07 0.57 7249.73 0.92 0.91 0.91 1.29

 HUB 478.12 599.65 59.32 0.58 8063.36 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.27 495.61 1.08 460.98 472.75 1.31

 MEAN 5.52 1.30 4.11 494.91 1.08 456.27 472.42 1.58

 HUB 5.68 1.33 3.82 499.09 1.09 447.21 475.05 2.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.05 28.59 24.20 4.39 0.93 0.33 1.80

 MEAN 35.43 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 42.01 -5.68 -9.30 3.62 0.92 0.14 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 736.6521 401.0393 617.9189 1036.3025 0.7108 -0.0818 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5691 3.9909 452.8881 473.3983 1.8046 32.9842 35.4000 2.4158

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 584.9686 143.1012 567.1951 1054.5845 0.5547 0.2893 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5397 4.5060 469.0141 473.0845 554.9116 0.0294 0.4055

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 581.3394 0.0000 581.3394 1054.9503 0.5511 0.3214 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4982 469.3570 473.0289 0.0000 0.0600 0.0453 0.2842

NASA/TM—2013-218094 J–211
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8683 5.5156 1.2933 496.5379 38.7992 224.5107 1.7404

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 241205.828 0.558 772.594 636487.313 0.446919E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.757 EfDer = 0.999 SH = 0.446919E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.680 3652.568 5.516 496.538 1.000 1.000 0.980

 W Kg/sec = 25.764 Wdry = 56.678 WH2O = 0.003 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 147.800 3733.191 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 127439.328 44473.305 1.365 590.487 432.633 468.502 1.083 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 517.97 -0.18 517.97 0.49 0.79 669.46

 MEAN 18.08 0.00 -0.02 517.97 -0.18 517.97 0.49 0.73

 HUB 15.21 0.00 -0.02 517.97 -0.18 517.97 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.67 46.36 5.31 655.02 835.21 4.70 474.96 472.98 0.77

 MEAN 48.06 42.30 5.76 576.24 774.95 4.70 474.96 472.98 0.77

 HUB 43.12 37.84 5.28 484.81 709.58 4.70 474.96 472.98 0.77

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 587.32 286.87 512.49 1087.58 0.54 2.33 2.04 9.02

 MEAN 18.01 603.41 303.30 521.64 1083.68 0.56 2.40 2.13 7.35

 HUB 15.22 657.64 387.34 531.47 1080.09 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 650.88 628.61 364.01 0.58 5861.65 0.92 0.91

 MEAN 574.06 587.72 270.76 0.54 5465.70 0.92 0.91 0.91 1.43

 HUB 485.23 540.41 97.89 0.50 5899.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.70 1.22 5.51 526.59 1.06 498.85 488.62 0.34

 MEAN 6.62 1.20 5.37 524.56 1.06 495.28 487.65 0.38

 HUB 6.71 1.22 5.24 526.78 1.06 492.00 488.76 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.24 35.38 31.50 3.88 0.93 0.37 1.40

 MEAN 30.18 27.43 23.50 3.93 0.92 0.36 1.63

 HUB 36.09 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 676.3335 304.1543 604.0837 1076.9810 0.6280 -0.1916 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6645 5.1252 489.1938 488.3652 0.4600 26.7251 30.6000 3.8749

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 569.7307 120.7869 556.7796 1088.6799 0.5233 0.1134 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6410 5.5228 499.8750 488.2326 491.5697 0.0281 0.2784

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 597.1569 0.0000 597.1569 1085.8579 0.5499 0.1803 0.5911

NASA/TM—2013-218094 J–212
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4028 497.3038 488.1991 0.0000 0.0600 0.0447 0.0213

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8710 6.6193 1.2001 525.9776 29.4401 256.9404 1.9918

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 183074.469 0.432 586.397 572326.500 0.446919E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.993 EfDer = 0.999 SH = 0.446919E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.680 3652.568 6.619 525.978 1.000 1.000 0.980

 W Kg/sec = 25.764 Wdry = 56.678 WH2O = 0.003 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 126.754 3627.211 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 110204.938 44473.305 1.470 545.479 371.040 424.468 1.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 484.88 -0.17 484.88 0.44 0.73 635.26

 MEAN 17.74 0.00 -0.02 484.88 -0.17 484.88 0.44 0.68

 HUB 15.05 0.00 -0.02 484.88 -0.17 484.88 0.44 0.62

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.85 46.36 6.49 639.72 802.85 5.80 507.07 488.14 0.26

 MEAN 49.39 43.40 5.99 565.41 744.97 5.80 507.07 488.14 0.26

 HUB 44.70 38.84 5.86 479.71 682.20 5.80 507.07 488.14 0.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 562.65 286.88 484.02 1120.62 0.50 2.26 1.98 8.75

 MEAN 17.51 576.94 302.00 491.59 1117.08 0.52 2.34 2.07 6.78

 HUB 14.85 628.04 380.36 499.76 1113.79 0.56 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 631.44 594.14 344.56 0.53 5686.40 0.92 0.91

 MEAN 558.02 554.26 256.02 0.50 5289.93 0.92 0.91 0.91 1.45

 HUB 473.34 508.34 92.98 0.46 5650.79 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.92 1.20 6.68 555.12 1.06 529.67 501.34 0.13

 MEAN 7.82 1.18 6.53 553.09 1.05 526.33 500.48 0.15

 HUB 7.91 1.19 6.39 554.94 1.06 523.23 501.29 0.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.66 35.45 31.50 3.95 0.93 0.39 1.40

 MEAN 31.56 27.51 23.50 4.01 0.92 0.38 1.62

 HUB 37.27 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 640.4722 303.9812 563.7376 1111.8149 0.5761 -0.1736 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8690 6.3011 521.4092 501.0269 0.1663 28.3346 31.5000 3.1654

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 543.9290 118.6544 530.8294 1121.5768 0.4850 0.1196 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8492 6.6961 530.6010 500.9436 451.3937 0.0247 0.3036

 

NASA/TM—2013-218094 J–213
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 555.3951 0.0000 555.3951 1120.4846 0.4957 0.2113 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6324 529.5901 500.9001 0.0000 0.0600 0.0400 0.0724

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8775 7.8286 1.1827 554.3857 28.4086 245.3591 1.9020

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 176712.109 0.443 566.018 546577.813 0.446919E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.371 EfDer = 1.000 SH = 0.446919E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.680 3652.568 7.829 554.386 1.000 1.000 0.980

 W Kg/sec = 25.764 Wdry = 56.678 WH2O = 0.003 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.031 3533.055 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 96525.078 44473.305 1.594 513.330 322.102 395.845 1.229

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 451.29 -0.16 451.29 0.40 0.67 593.80

 MEAN 16.97 0.00 -0.02 451.29 -0.16 451.29 0.40 0.62

 HUB 14.32 0.00 -0.02 451.29 -0.16 451.29 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.69 46.36 7.33 613.91 762.06 7.02 538.02 500.87 0.11

 MEAN 50.17 43.80 6.37 540.94 704.59 7.02 538.02 500.87 0.11

 HUB 45.34 37.84 7.50 456.45 641.99 7.02 538.02 500.87 0.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 532.10 279.32 452.89 1150.81 0.46 2.16 1.89 8.34

 MEAN 16.57 543.00 289.07 459.66 1147.29 0.47 2.24 1.97 6.35

 HUB 13.89 587.39 356.38 466.92 1143.96 0.51 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 601.79 555.97 322.47 0.48 5276.54 0.92 0.91

 MEAN 528.29 518.18 239.22 0.45 4793.64 0.92 0.91 0.91 1.48

 HUB 442.74 474.84 86.36 0.42 4952.36 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.17 1.17 7.93 581.42 1.05 558.67 511.87 0.06

 MEAN 9.04 1.15 7.77 578.95 1.04 555.25 510.91 0.07

 HUB 9.08 1.16 7.60 579.76 1.05 552.03 511.23 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.66 35.45 31.50 3.95 0.93 0.40 1.40

 MEAN 32.16 27.49 23.50 3.99 0.93 0.39 1.62

 HUB 37.35 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 586.5465 290.6950 509.4440 1144.2947 0.5126 -0.1199 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0848 7.6109 552.3964 511.3145 0.0720 29.7096 32.4000 2.6904

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 504.4651 113.1368 491.6147 1151.7234 0.4380 0.1454 2.2705

 

NASA/TM—2013-218094 J–214
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0696 7.9631 559.5928 511.2627 432.2457 0.0215 0.3257

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 500.3376 0.0000 500.3376 1152.0437 0.4343 0.2367 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9597 559.9280 511.2103 0.0000 0.0600 0.0391 0.1429

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8790 9.0462 1.1555 580.0432 25.6581 247.7817 1.9208

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 159662.609 0.441 511.407 540208.938 0.446919E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.673 EfDer = 1.000 SH = 0.446919E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.680 3652.568 9.046 580.043 1.000 1.000 0.980

 W Kg/sec = 25.764 Wdry = 56.678 WH2O = 0.003 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.399 3454.032 1.381 0.249 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 85786.469 44473.305 1.787 509.668 285.141 384.739 1.349

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 403.96 -0.14 403.96 0.35 0.61 552.19

 MEAN 15.91 0.00 -0.02 403.96 -0.14 403.96 0.35 0.56

 HUB 13.07 0.00 -0.02 403.96 -0.14 403.96 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.33 47.36 7.97 583.94 710.17 8.33 566.93 511.20 0.05

 MEAN 51.47 44.80 6.67 507.22 648.54 8.33 566.93 511.20 0.05

 HUB 45.89 38.84 7.05 416.60 580.40 8.33 566.93 511.20 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 495.05 279.16 408.83 1178.55 0.42 2.05 1.78 7.43

 MEAN 15.50 499.38 277.00 415.52 1174.51 0.43 2.13 1.86 5.75

 HUB 12.59 532.20 323.52 422.58 1170.62 0.45 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 571.83 502.79 292.67 0.43 5010.74 0.92 0.91

 MEAN 493.98 468.76 216.98 0.40 4295.03 0.92 0.91 0.91 1.52

 HUB 401.30 429.68 77.78 0.37 4074.97 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.45 1.15 9.27 605.71 1.04 586.02 520.82 0.03

 MEAN 10.24 1.13 9.05 602.04 1.04 582.00 519.49 0.04

 HUB 10.17 1.12 8.84 600.91 1.04 578.16 519.08 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.33 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.69 27.57 23.50 4.07 0.93 0.41 1.64

 HUB 37.44 10.43 6.50 3.93 0.93 0.40 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 555.8102 282.0776 478.9126 1170.4913 0.4749 -0.1988 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2607 8.8101 578.0720 519.7556 0.0391 30.4979 33.0000 2.5021

 

NASA/TM—2013-218094 J–215
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 484.3105 110.5927 471.5145 1176.5245 0.4116 0.0555 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2368 9.1235 584.0456 519.6945 410.5396 0.0394 0.3394

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 469.1897 0.0000 469.1897 1177.6672 0.3984 0.2619 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1900 585.2054 519.6943 0.0000 0.0600 0.0388 0.1096

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8812 10.2377 1.1317 602.8867 22.8442 254.7746 1.9750

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 142213.109 0.435 455.516 548870.375 0.446935E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3171 Tt4 = 602.8867 T1 = 457.7391

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 902868.19 2891.9312 183.5320 2.4006 0.8620 4.8181 1.3171 37.3740

NASA/TM—2013-218094 J–216
 100μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 100% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 2.843 EfDer = 0.984 SH = 0.880315E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.724 3973.534 4.265 477.920 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.718 WH2O = 0.005 lbm/sec H2O = 0.030g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 204.226 4139.589 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 171776.547 48429.875 1.391 831.557 597.805 619.754 1.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 495.77 -0.17 495.77 0.48 0.84 745.23

 MEAN 17.06 0.00 -0.02 495.77 -0.17 495.77 0.48 0.74

 HUB 12.51 0.00 -0.02 495.77 -0.17 495.77 0.48 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.28 50.47 4.81 715.36 870.50 3.66 458.15 460.87 2.53

 MEAN 50.04 47.20 2.84 591.57 771.98 3.66 458.15 460.87 2.53

 HUB 41.20 38.62 2.58 433.79 658.87 3.66 458.15 460.87 2.53

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 743.62 360.69 650.29 1061.26 0.70 7.29 6.52 16.04

 MEAN 18.04 789.72 420.31 668.57 1055.77 0.75 7.43 6.80 12.53

 HUB 15.00 933.71 592.64 721.52 1041.45 0.90 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 715.36 740.72 354.67 0.70 7444.56 0.92 0.90

 MEAN 625.41 699.33 205.10 0.66 7583.70 0.92 0.90 0.90 1.21

 HUB 520.13 725.15 72.50 0.70 8891.72 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.60 1.31 4.05 519.44 1.09 474.97 483.69 1.31

 MEAN 5.63 1.32 3.90 520.22 1.09 470.06 484.22 1.57

 HUB 5.89 1.38 3.52 527.52 1.10 457.40 488.45 2.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.02 28.61 24.20 4.41 0.93 0.26 1.80

 MEAN 32.16 17.05 12.70 4.35 0.91 0.22 2.22

 HUB 39.40 -5.74 -9.30 3.56 0.91 0.06 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 854.1772 419.4975 744.0702 1048.6151 0.8146 -0.1082 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6898 3.6955 463.7095 485.5049 1.9823 29.4138 35.4000 5.9862

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 696.0285 170.2698 674.8806 1070.6714 0.6501 0.2272 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6286 4.2509 483.4301 484.7450 554.9116 0.0424 0.3580

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 698.3840 0.0000 698.3840 1070.3573 0.6525 0.2518 1.3089

NASA/TM—2013-218094 J–217
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.1976 483.1710 484.5894 0.0000 0.0600 0.0740 0.1990

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8217 5.5691 1.3059 522.3939 44.4745 238.1942 1.8465

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 276508.125 0.540 964.479 688685.438 0.885364E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.448 EfDer = 0.989 SH = 0.885602E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.724 3973.534 5.569 522.394 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.718 WH2O = 0.005 lbm/sec H2O = 0.035g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 163.502 3959.461 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 150306.984 48429.859 1.234 590.487 478.608 468.502 0.979

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 610.91 -0.21 610.91 0.57 0.87 710.04

 MEAN 18.08 0.00 -0.02 610.91 -0.21 610.91 0.57 0.81

 HUB 15.21 0.00 -0.02 610.91 -0.21 610.91 0.57 0.75

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.40 46.36 3.04 712.58 938.77 4.49 492.38 484.44 0.70

 MEAN 45.75 42.30 3.45 626.87 875.47 4.49 492.38 484.44 0.70

 HUB 40.82 37.84 2.98 527.42 807.22 4.49 492.38 484.44 0.70

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 662.05 280.35 599.76 1109.42 0.60 2.33 2.04 9.02

 MEAN 18.01 682.29 306.51 609.57 1105.86 0.62 2.40 2.13 7.35

 HUB 15.22 744.87 412.21 620.42 1102.66 0.68 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 708.08 736.66 427.72 0.66 5729.15 0.92 0.90

 MEAN 624.51 687.53 318.00 0.62 5524.03 0.92 0.90 0.90 1.37

 HUB 527.87 631.10 115.66 0.57 6278.26 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.77 1.22 5.34 554.34 1.06 519.10 498.49 0.30

 MEAN 6.72 1.21 5.22 553.20 1.06 515.77 498.04 0.33

 HUB 6.89 1.24 5.10 557.41 1.07 512.79 499.84 0.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 25.05 35.49 31.50 3.99 0.93 0.32 1.40

 MEAN 26.69 27.55 23.50 4.05 0.92 0.32 1.63

 HUB 33.60 10.56 6.50 4.06 0.92 0.35 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 782.9727 307.3702 720.1179 1094.9711 0.7151 -0.2381 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7793 4.8400 505.6950 498.8881 0.4501 23.1144 30.6000 7.4856

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 677.1002 143.5500 661.7084 1108.3567 0.6109 0.0188 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7284 5.2454 518.1204 498.5925 491.5697 0.0422 0.2194

 

NASA/TM—2013-218094 J–218
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 721.4407 0.0000 721.4407 1102.9910 0.6541 0.0955 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0252 513.1395 498.5056 0.0000 0.0600 0.0756 -0.1206

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8223 6.6758 1.1987 554.9827 32.5891 281.2424 2.1802

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 202699.109 0.404 707.028 623730.750 0.886136E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 3.820 EfDer = 0.991 SH = 0.886136E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.724 3973.534 6.676 554.983 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.718 WH2O = 0.005 lbm/sec H2O = 0.041g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 140.589 3841.452 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 129409.117 48429.855 1.325 545.479 411.555 424.468 1.031

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 569.37 -0.20 569.37 0.51 0.80 672.79

 MEAN 17.74 0.00 -0.02 569.37 -0.20 569.37 0.51 0.75

 HUB 15.05 0.00 -0.02 569.37 -0.20 569.37 0.51 0.69

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.72 46.36 4.36 695.94 899.33 5.61 528.92 498.36 0.23

 MEAN 47.22 43.40 3.82 615.09 838.31 5.61 528.92 498.36 0.23

 HUB 42.52 38.84 3.68 521.87 772.49 5.61 528.92 498.36 0.23

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 631.84 283.47 564.68 1146.26 0.55 2.26 1.98 8.75

 MEAN 17.51 650.14 307.32 572.91 1142.95 0.57 2.34 2.07 6.78

 HUB 14.85 709.36 405.50 582.03 1139.94 0.62 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 686.92 694.00 403.45 0.61 5619.47 0.92 0.91

 MEAN 607.05 646.58 299.73 0.57 5383.61 0.92 0.91 0.91 1.40

 HUB 514.93 592.23 109.44 0.52 6024.58 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.00 1.20 6.52 586.31 1.06 554.22 510.53 0.12

 MEAN 7.94 1.19 6.39 584.99 1.05 551.02 510.05 0.13

 HUB 8.10 1.21 6.26 588.57 1.06 548.12 511.41 0.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 26.66 35.55 31.50 4.05 0.93 0.34 1.40

 MEAN 28.21 27.62 23.50 4.12 0.92 0.34 1.62

 HUB 34.86 10.65 6.50 4.15 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 733.7472 309.3376 665.3534 1134.9240 0.6465 -0.2060 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9981 6.0587 543.3569 510.6733 0.1512 24.9348 31.5000 6.5652

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 641.8940 140.0248 626.4352 1145.4926 0.5604 0.0332 2.3726

 

NASA/TM—2013-218094 J–219
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9570 6.4460 553.5093 510.5007 451.3937 0.0353 0.2527

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 659.6068 0.0000 659.6068 1143.5475 0.5768 0.1425 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3351 551.6613 510.4047 0.0000 0.0600 0.0608 -0.0352

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8441 7.9157 1.1857 586.6240 31.6417 266.7160 2.0676

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 196887.391 0.417 686.757 589520.125 0.886657E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 4.406 EfDer = 0.995 SH = 0.886657E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.724 3973.534 7.916 586.624 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.718 WH2O = 0.005 lbm/sec H2O = 0.047g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 121.900 3736.416 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 112548.188 48429.859 1.438 513.330 356.868 395.845 1.109 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 526.20 -0.18 526.20 0.45 0.74 627.98

 MEAN 16.97 0.00 -0.02 526.20 -0.18 526.20 0.45 0.68

 HUB 14.32 0.00 -0.02 526.20 -0.18 526.20 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.77 46.36 5.41 667.85 850.39 6.88 564.38 510.34 0.09

 MEAN 48.21 43.80 4.41 588.47 789.56 6.88 564.38 510.34 0.09

 HUB 43.35 37.84 5.51 496.56 723.63 6.88 564.38 510.34 0.09

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 594.78 279.70 524.91 1180.22 0.50 2.16 1.89 8.34

 MEAN 16.57 609.54 296.44 532.60 1176.72 0.52 2.24 1.97 6.35

 HUB 13.89 661.49 380.70 540.96 1173.47 0.56 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 654.68 645.08 374.97 0.55 5284.26 0.92 0.91

 MEAN 574.71 600.91 278.26 0.51 4916.31 0.92 0.91 0.91 1.42

 HUB 481.64 550.29 100.94 0.47 5290.54 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.31 1.18 7.84 616.07 1.05 587.64 520.75 0.05

 MEAN 9.20 1.16 7.68 614.02 1.05 584.17 520.06 0.06

 HUB 9.31 1.18 7.52 616.10 1.05 580.95 520.79 0.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.05 35.54 31.50 4.04 0.93 0.36 1.40

 MEAN 29.10 27.59 23.50 4.09 0.92 0.35 1.62

 HUB 35.14 10.57 6.50 4.07 0.92 0.37 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 664.4677 298.1116 593.8407 1172.3827 0.5668 -0.1373 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2576 7.4648 579.9320 520.5096 0.0624 26.6569 32.4000 5.7431

 

NASA/TM—2013-218094 J–220
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 588.7925 132.0490 573.7941 1180.0614 0.4990 0.0744 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.2275 7.8011 587.5493 520.4080 432.2457 0.0290 0.2827

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 584.1212 0.0000 584.1212 1180.4749 0.4948 0.1853 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7970 587.9929 520.3339 0.0000 0.0600 0.0477 0.0718

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8615 9.1977 1.1620 615.3956 28.7723 267.0109 2.0699

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 179126.703 0.418 624.806 577248.375 0.887061E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 5.011 EfDer = 0.997 SH = 0.887061E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 61.724 3973.534 9.198 615.395 1.000 1.000 0.980

 W Kg/sec = 28.056 Wdry = 61.718 WH2O = 0.005 lbm/sec H2O = 0.053g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 107.451 3648.026 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99014.805 48429.859 1.620 509.668 314.595 384.739 1.223

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 466.26 -0.16 466.26 0.39 0.66 583.20

 MEAN 15.91 0.00 -0.02 466.26 -0.16 466.26 0.39 0.61

 HUB 13.07 0.00 -0.02 466.26 -0.16 466.26 0.39 0.55

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.73 47.36 6.37 635.26 788.13 8.29 597.94 520.30 0.04

 MEAN 49.81 44.80 5.01 551.79 722.53 8.29 597.94 520.30 0.04

 HUB 44.20 38.84 5.36 453.21 650.34 8.29 597.94 520.30 0.04

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 549.02 285.38 469.02 1211.86 0.45 2.05 1.78 7.43

 MEAN 15.50 556.99 287.48 477.06 1207.54 0.46 2.13 1.86 5.75

 HUB 12.59 596.56 346.56 485.56 1203.43 0.50 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.08 577.36 336.70 0.48 5122.69 0.92 0.91

 MEAN 537.39 538.56 249.91 0.45 4457.80 0.92 0.91 0.91 1.47

 HUB 436.57 493.84 90.00 0.41 4365.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.69 1.16 9.30 643.92 1.05 619.72 529.70 0.03

 MEAN 10.49 1.14 9.08 640.22 1.04 615.31 528.52 0.03

 HUB 10.46 1.14 8.86 639.70 1.04 611.13 528.36 0.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.32 35.67 31.50 4.17 0.93 0.40 1.40

 MEAN 31.07 27.65 23.50 4.15 0.92 0.37 1.64

 HUB 35.52 10.50 6.50 4.00 0.92 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 625.9498 292.7509 553.2722 1202.0835 0.5207 -0.2179 2.0437

 

NASA/TM—2013-218094 J–221
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5150 8.7611 609.8292 528.8074 0.0335 27.8845 33.0000 5.1155

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 560.8207 128.0639 546.0032 1208.1897 0.4642 -0.0210 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4701 9.0500 616.0329 528.6889 410.5396 0.0507 0.3034

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 541.9097 0.0000 541.9097 1209.8011 0.4479 0.2196 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.1463 617.7100 528.7025 0.0000 0.0600 0.0455 0.0448

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8691 10.4778 1.1392 641.2812 25.8864 270.9812 2.1006

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 161257.984 0.417 562.479 581103.375 0.887589E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3418 Tt4 = 641.2812 T1 = 477.9197

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 1016479.31 3545.5488 204.2262 2.4569 0.8233 2.8431 1.3418 37.3740

NASA/TM—2013-218094 J–222
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 84.0% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 3.952 EfDer = 0.992 SH = 0.882326E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.027 3823.044 4.265 477.920 1.000 1.000 0.980

 W Kg/sec = 26.376 Wdry = 58.022 WH2O = 0.005 lbm/sec H2O = 0.031g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 191.994 3982.810 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 158876.781 45529.117 1.480 831.557 562.001 619.754 1.103

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 458.54 -0.16 458.54 0.44 0.79 717.01

 MEAN 17.06 0.00 -0.02 458.54 -0.16 458.54 0.44 0.70

 HUB 12.51 0.00 -0.02 458.54 -0.16 458.54 0.44 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.33 50.47 5.86 688.27 827.16 3.74 461.01 460.82 2.27

 MEAN 51.15 47.20 3.95 569.17 731.02 3.74 461.01 460.82 2.27

 HUB 42.32 38.62 3.70 417.36 620.15 3.74 461.01 460.82 2.27

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 698.29 363.05 596.49 1065.66 0.66 7.29 6.52 16.04

 MEAN 18.04 739.37 413.81 612.72 1060.20 0.70 7.43 6.80 12.53

 HUB 15.00 862.74 565.37 651.68 1048.46 0.82 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 688.27 679.39 325.22 0.64 7492.91 0.92 0.91

 MEAN 601.72 640.89 187.92 0.60 7466.12 0.92 0.91 0.91 1.26

 HUB 500.44 654.90 64.93 0.62 8482.52 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.57 1.31 4.19 518.13 1.08 478.91 482.97 1.15

 MEAN 5.56 1.30 4.03 517.99 1.08 474.02 483.02 1.36

 HUB 5.76 1.35 3.71 523.44 1.10 463.58 486.12 2.01

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.33 28.60 24.20 4.40 0.93 0.30 1.80

 MEAN 34.03 17.05 12.70 4.35 0.92 0.25 2.22

 HUB 40.94 -5.69 -9.30 3.61 0.92 0.11 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 790.5140 413.0029 674.0482 1055.2361 0.7491 -0.0909 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6129 3.8837 469.5922 484.0446 1.5996 31.4966 35.4000 3.9034

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 635.5350 155.4713 616.2251 1075.0151 0.5912 0.2636 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5739 4.4123 487.3688 483.5244 554.9116 0.0336 0.3859

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 633.0973 0.0000 633.0973 1075.2677 0.5888 0.2947 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.3933 487.6213 483.4289 0.0000 0.0600 0.0543 0.2521

NASA/TM—2013-218094 J–223
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8535 5.5396 1.2990 519.8525 41.9333 230.3351 1.7855

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 260721.453 0.550 854.944 636967.750 0.888243E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.796 EfDer = 0.996 SH = 0.889214E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.027 3823.044 5.540 519.852 1.000 1.000 0.980

 W Kg/sec = 26.376 Wdry = 58.022 WH2O = 0.005 lbm/sec H2O = 0.036g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 154.152 3818.804 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 137956.547 45529.102 1.309 590.487 451.239 468.502 1.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 560.72 -0.19 560.72 0.52 0.82 684.82

 MEAN 18.08 0.00 -0.02 560.72 -0.19 560.72 0.52 0.76

 HUB 15.21 0.00 -0.02 560.72 -0.19 560.72 0.52 0.70

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.73 46.36 4.37 685.60 885.84 4.62 494.57 483.33 0.66

 MEAN 47.10 42.30 4.80 603.13 823.65 4.62 494.57 483.33 0.66

 HUB 42.16 37.84 4.32 507.44 756.37 4.62 494.57 483.33 0.66

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 623.52 287.76 553.15 1110.53 0.56 2.33 2.04 9.02

 MEAN 18.01 641.61 308.19 562.74 1106.69 0.58 2.40 2.13 7.35

 HUB 15.22 699.94 401.82 573.11 1103.20 0.63 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 681.26 678.84 393.50 0.61 5879.93 0.92 0.91

 MEAN 600.85 634.29 292.66 0.57 5554.00 0.92 0.91 0.91 1.40

 HUB 507.88 582.84 106.05 0.53 6119.90 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.22 5.45 551.40 1.06 520.14 497.46 0.30

 MEAN 6.66 1.20 5.32 549.65 1.06 516.55 496.74 0.33

 HUB 6.78 1.22 5.19 552.69 1.06 513.29 498.08 0.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.48 35.43 31.50 3.93 0.93 0.35 1.40

 MEAN 28.71 27.48 23.50 3.98 0.92 0.34 1.63

 HUB 35.04 10.48 6.50 3.98 0.92 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 725.1463 309.0564 655.9888 1098.5085 0.6601 -0.2079 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7125 5.0273 508.9706 497.4782 0.4150 25.2266 30.6000 5.3734

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 618.0314 131.0271 603.9824 1110.9290 0.5563 0.0766 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6805 5.4277 520.5363 497.2666 491.5697 0.0328 0.2553

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 650.8602 0.0000 650.8602 1107.3284 0.5878 0.1487 0.5911

NASA/TM—2013-218094 J–224
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.2778 517.1910 497.2161 0.0000 0.0600 0.0546 -0.0300

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8562 6.6497 1.2004 551.2462 31.3940 266.5990 2.0667

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 195269.063 0.421 640.316 574311.000 0.889736E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.105 EfDer = 0.997 SH = 0.889736E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.027 3823.044 6.650 551.246 1.000 1.000 0.980

 W Kg/sec = 26.376 Wdry = 58.022 WH2O = 0.005 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 132.238 3708.469 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 119014.297 45529.102 1.409 545.479 387.110 424.468 1.097

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 523.64 -0.18 523.64 0.47 0.76 649.50

 MEAN 17.74 0.00 -0.02 523.64 -0.18 523.64 0.47 0.71

 HUB 15.05 0.00 -0.02 523.64 -0.18 523.64 0.47 0.65

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.98 46.36 5.62 669.58 850.17 5.74 529.21 497.12 0.23

 MEAN 48.51 43.40 5.11 591.80 790.34 5.74 529.21 497.12 0.23

 HUB 43.81 38.84 4.97 502.10 725.59 5.74 529.21 497.12 0.23

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 596.22 289.24 521.36 1145.44 0.52 2.26 1.98 8.75

 MEAN 17.51 612.38 307.91 529.34 1141.92 0.54 2.34 2.07 6.78

 HUB 14.85 667.39 394.93 538.00 1138.68 0.59 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 660.91 640.28 371.67 0.56 5733.45 0.92 0.91

 MEAN 584.06 597.04 276.15 0.52 5393.56 0.92 0.91 0.91 1.43

 HUB 495.43 547.31 100.50 0.48 5867.39 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.96 1.20 6.63 582.00 1.06 553.42 509.30 0.12

 MEAN 7.88 1.18 6.49 580.17 1.05 550.03 508.63 0.13

 HUB 7.99 1.20 6.35 582.72 1.06 546.91 509.61 0.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.02 35.48 31.50 3.98 0.93 0.37 1.40

 MEAN 30.19 27.55 23.50 4.05 0.92 0.36 1.62

 HUB 36.28 10.58 6.50 4.08 0.92 0.38 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 683.8945 309.9259 609.6373 1135.6392 0.6022 -0.1853 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.9295 6.2242 544.0416 509.1829 0.1526 26.9478 31.5000 4.5522

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 588.1247 128.2954 573.9608 1145.8196 0.5133 0.0861 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.9032 6.6178 553.8305 509.0562 451.3937 0.0282 0.2835

 

NASA/TM—2013-218094 J–225
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 601.4703 0.0000 601.4703 1144.4724 0.5255 0.1863 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5419 552.5585 508.9991 0.0000 0.0600 0.0454 0.0338

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8686 7.8781 1.1847 581.6290 30.3832 253.6985 1.9667

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 189056.719 0.433 619.945 546440.375 0.890247E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.583 EfDer = 0.999 SH = 0.890247E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.027 3823.044 7.878 581.629 1.000 1.000 0.980

 W Kg/sec = 26.376 Wdry = 58.022 WH2O = 0.005 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 114.654 3610.309 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 103886.906 45529.102 1.529 513.330 335.654 395.845 1.179

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 485.71 -0.17 485.71 0.42 0.70 606.79

 MEAN 16.97 0.00 -0.02 485.71 -0.17 485.71 0.42 0.65

 HUB 14.32 0.00 -0.02 485.71 -0.17 485.71 0.42 0.59

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.92 46.36 6.56 642.56 805.61 6.99 562.67 508.95 0.10

 MEAN 49.38 43.80 5.58 566.18 746.10 6.99 562.67 508.95 0.10

 HUB 44.54 37.84 6.70 477.75 681.41 6.99 562.67 508.95 0.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 562.72 283.21 486.26 1177.43 0.48 2.16 1.89 8.34

 MEAN 16.57 575.32 295.73 493.50 1173.86 0.49 2.24 1.97 6.35

 HUB 13.89 623.27 370.36 501.29 1170.50 0.53 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 629.88 597.18 346.67 0.51 5350.24 0.92 0.91

 MEAN 552.94 556.51 257.22 0.47 4904.20 0.92 0.91 0.91 1.45

 HUB 463.40 509.85 93.04 0.44 5146.75 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.24 1.17 7.92 610.31 1.05 584.87 519.31 0.06

 MEAN 9.12 1.16 7.76 607.92 1.05 581.33 518.48 0.06

 HUB 9.19 1.17 7.59 609.22 1.05 578.01 518.95 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.22 35.49 31.50 3.99 0.93 0.38 1.40

 MEAN 30.93 27.53 23.50 4.03 0.92 0.38 1.62

 HUB 36.46 10.51 6.50 4.01 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 623.5739 297.3911 548.0901 1170.3517 0.5328 -0.1263 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1706 7.5771 577.9167 518.8914 0.0673 28.4840 32.4000 3.9160

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 542.9168 121.7604 529.0870 1177.9797 0.4609 0.1178 2.2705

 

NASA/TM—2013-218094 J–226
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1508 7.9254 585.4741 518.8162 432.2457 0.0239 0.3084

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 538.5124 0.0000 538.5124 1178.3361 0.4570 0.2164 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9220 585.8596 518.7531 0.0000 0.0600 0.0418 0.1154

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8738 9.1251 1.1583 609.1505 27.5222 255.1836 1.9782

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 171337.969 0.432 561.842 538244.813 0.890714E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.004 EfDer = 0.999 SH = 0.890714E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 58.027 3823.044 9.125 609.150 1.000 1.000 0.980

 W Kg/sec = 26.376 Wdry = 58.022 WH2O = 0.005 lbm/sec H2O = 0.054g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 101.300 3527.810 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 91962.125 45529.102 1.718 509.668 296.583 384.739 1.297

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 433.04 -0.15 433.04 0.36 0.63 563.98

 MEAN 15.91 0.00 -0.02 433.04 -0.15 433.04 0.36 0.58

 HUB 13.07 0.00 -0.02 433.04 -0.15 433.04 0.36 0.52

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 54.69 47.36 7.33 611.20 749.18 8.33 594.09 518.73 0.05

 MEAN 50.80 44.80 6.00 530.90 685.23 8.33 594.09 518.73 0.05

 HUB 45.21 38.84 6.37 436.05 614.65 8.33 594.09 518.73 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 522.02 285.19 437.23 1206.95 0.43 2.05 1.78 7.43

 MEAN 15.50 527.84 284.64 444.52 1202.75 0.44 2.13 1.86 5.75

 HUB 12.59 563.70 336.54 452.22 1198.72 0.47 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 598.52 537.91 313.33 0.45 5119.01 0.92 0.91

 MEAN 517.04 501.61 232.40 0.42 4413.54 0.92 0.91 0.91 1.50

 HUB 420.03 459.86 83.49 0.38 4239.00 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.56 1.16 9.30 636.58 1.05 614.70 527.96 0.03

 MEAN 10.36 1.13 9.09 632.80 1.04 610.42 526.72 0.03

 HUB 10.31 1.13 8.87 631.86 1.04 606.35 526.42 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.11 35.63 31.50 4.13 0.93 0.42 1.40

 MEAN 32.63 27.60 23.50 4.10 0.93 0.39 1.64

 HUB 36.66 10.46 6.50 3.96 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 589.6406 289.8546 513.4786 1198.1595 0.4921 -0.2061 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3818 8.8165 605.8345 526.9896 0.0374 29.4444 33.0000 3.5556

 

NASA/TM—2013-218094 J–227
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 519.6331 118.6587 505.9039 1204.3114 0.4315 0.0260 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3513 9.1233 612.0685 526.9042 410.5396 0.0432 0.3248

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 502.9742 0.0000 502.9742 1205.6270 0.4172 0.2450 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2001 613.4387 526.9076 0.0000 0.0600 0.0409 0.0842

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8776 10.3542 1.1347 633.7458 24.5961 261.1004 2.0240

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 153207.250 0.428 502.389 545052.313 0.891302E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3261 Tt4 = 633.7458 T1 = 477.9195

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 969592.50 3179.4365 191.9939 2.4279 0.8502 3.9515 1.3261 37.3740

NASA/TM—2013-218094 J–228
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 79.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.381 EfDer = 0.994 SH = 0.883078E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.732 3775.939 4.265 477.919 1.000 1.000 0.980

 W Kg/sec = 25.787 Wdry = 56.727 WH2O = 0.005 lbm/sec H2O = 0.031g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 187.708 3933.736 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 154526.594 44512.871 1.513 831.557 549.457 619.754 1.128

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 445.99 -0.15 445.99 0.43 0.78 708.17

 MEAN 17.06 0.00 -0.02 445.99 -0.15 445.99 0.43 0.69

 HUB 12.51 0.00 -0.02 445.99 -0.15 445.99 0.43 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.74 50.47 6.27 679.79 813.15 3.77 461.92 460.80 2.19

 MEAN 51.58 47.20 4.38 562.15 717.70 3.77 461.92 460.80 2.19

 HUB 42.76 38.62 4.14 412.22 607.42 3.77 461.92 460.80 2.19

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 683.88 364.31 578.76 1067.04 0.64 7.29 6.52 16.04

 MEAN 18.04 723.26 412.06 594.39 1061.58 0.68 7.43 6.80 12.53

 HUB 15.00 840.83 556.95 629.93 1050.46 0.80 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 679.79 659.16 315.47 0.62 7518.95 0.92 0.91

 MEAN 594.31 621.70 182.25 0.59 7434.62 0.92 0.91 0.91 1.27

 HUB 494.27 633.04 62.68 0.60 8356.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.56 1.30 4.23 517.77 1.08 480.16 482.77 1.10

 MEAN 5.54 1.30 4.08 517.33 1.08 475.25 482.66 1.31

 HUB 5.72 1.34 3.77 522.21 1.09 465.35 485.44 1.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.19 28.59 24.20 4.39 0.93 0.31 1.80

 MEAN 34.73 17.05 12.70 4.35 0.92 0.27 2.22

 HUB 41.48 -5.68 -9.30 3.62 0.92 0.12 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 770.8469 411.2641 651.9715 1057.1647 0.7292 -0.0860 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5900 3.9400 471.3127 483.6244 1.5048 32.2438 35.4000 3.1562

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 616.0394 150.7020 597.3219 1076.3492 0.5723 0.2766 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5563 4.4614 488.5816 483.1593 554.9116 0.0313 0.3957

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 612.8322 0.0000 612.8322 1076.6766 0.5692 0.3084 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4489 488.9021 483.0787 0.0000 0.0600 0.0493 0.2687

NASA/TM—2013-218094 J–229
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8616 5.5277 1.2962 519.1025 41.1834 227.4156 1.7629

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 256062.484 0.554 820.925 619527.125 0.889487E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.279 EfDer = 0.998 SH = 0.890501E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.732 3775.939 5.528 519.102 1.000 1.000 0.980

 W Kg/sec = 25.787 Wdry = 56.727 WH2O = 0.005 lbm/sec H2O = 0.036g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 150.926 3774.475 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 133971.781 44512.863 1.337 590.487 441.797 468.502 1.060

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 544.52 -0.19 544.52 0.50 0.80 676.87

 MEAN 18.08 0.00 -0.02 544.52 -0.19 544.52 0.50 0.74

 HUB 15.21 0.00 -0.02 544.52 -0.19 544.52 0.50 0.68

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.20 46.36 4.84 677.15 869.07 4.66 495.26 482.99 0.65

 MEAN 47.58 42.30 5.28 595.70 807.21 4.66 495.26 482.99 0.65

 HUB 42.64 37.84 4.80 501.19 740.19 4.66 495.26 482.99 0.65

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 611.39 290.46 537.99 1110.91 0.55 2.33 2.04 9.02

 MEAN 18.01 628.65 309.01 547.46 1106.99 0.57 2.40 2.13 7.35

 HUB 15.22 685.51 398.66 557.67 1103.41 0.62 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 672.87 660.05 382.40 0.59 5935.08 0.92 0.91

 MEAN 593.45 616.95 284.44 0.56 5568.68 0.92 0.91 0.91 1.41

 HUB 501.62 567.09 102.96 0.51 6071.64 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.22 5.48 550.55 1.06 520.50 497.15 0.30

 MEAN 6.64 1.20 5.35 548.61 1.06 516.83 496.35 0.33

 HUB 6.75 1.22 5.22 551.28 1.06 513.49 497.53 0.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.36 35.41 31.50 3.91 0.93 0.36 1.40

 MEAN 29.44 27.45 23.50 3.95 0.92 0.35 1.63

 HUB 35.56 10.46 6.50 3.96 0.92 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 707.4097 309.8794 635.9271 1099.5260 0.6434 -0.1993 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6884 5.0795 509.9147 497.0485 0.4054 25.9794 30.6000 4.6206

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 599.4633 127.0905 585.8363 1111.6935 0.5392 0.0954 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6610 5.4785 521.2553 496.8576 491.5697 0.0302 0.2670

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 629.6513 0.0000 629.6513 1108.4867 0.5680 0.1650 0.5911

NASA/TM—2013-218094 J–230
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3450 518.2758 496.8160 0.0000 0.0600 0.0492 -0.0032

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8644 6.6353 1.2004 550.1473 31.0451 261.6668 2.0284

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 193099.625 0.427 619.069 557930.375 0.891096E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.553 EfDer = 0.999 SH = 0.891096E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.732 3775.939 6.635 550.147 1.000 1.000 0.980

 W Kg/sec = 25.787 Wdry = 56.727 WH2O = 0.005 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 129.438 3666.432 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 115707.914 44512.863 1.440 545.479 378.913 424.468 1.120

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 509.09 -0.18 509.09 0.45 0.75 642.13

 MEAN 17.74 0.00 -0.02 509.09 -0.18 509.09 0.45 0.69

 HUB 15.05 0.00 -0.02 509.09 -0.18 509.09 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.42 46.36 6.06 661.33 834.73 5.77 529.31 496.73 0.23

 MEAN 48.95 43.40 5.55 584.51 775.26 5.77 529.31 496.73 0.23

 HUB 44.26 38.84 5.42 495.92 710.83 5.77 529.31 496.73 0.23

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 585.15 291.21 507.54 1145.21 0.51 2.26 1.98 8.75

 MEAN 17.51 600.53 308.22 515.40 1141.64 0.53 2.34 2.07 6.78

 HUB 14.85 654.13 391.68 523.91 1138.33 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 652.76 623.16 361.56 0.54 5772.35 0.92 0.91

 MEAN 576.86 581.22 268.65 0.51 5398.91 0.92 0.91 0.91 1.44

 HUB 489.33 532.93 97.65 0.47 5819.09 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.94 1.20 6.66 580.73 1.06 553.20 508.91 0.12

 MEAN 7.85 1.18 6.52 578.75 1.05 549.76 508.17 0.13

 HUB 7.95 1.20 6.37 580.97 1.06 546.58 509.05 0.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.85 35.46 31.50 3.96 0.93 0.38 1.40

 MEAN 30.88 27.53 23.50 4.03 0.92 0.37 1.62

 HUB 36.78 10.56 6.50 4.06 0.92 0.39 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 668.5695 310.2385 592.2308 1135.8326 0.5886 -0.1791 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8999 6.2663 544.2267 508.7105 0.1530 27.6477 31.5000 3.8523

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 571.3699 124.6405 557.6095 1145.9020 0.4986 0.1033 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8772 6.6608 553.9115 508.5952 451.3937 0.0263 0.2938

 

NASA/TM—2013-218094 J–231
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 583.7200 0.0000 583.7200 1144.6887 0.5099 0.1999 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.5929 552.7686 508.5463 0.0000 0.0600 0.0417 0.0547

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8743 7.8557 1.1839 580.1484 30.0016 249.4211 1.9335

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 186681.766 0.438 598.493 531953.063 0.891627E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 5.986 EfDer = 0.999 SH = 0.891627E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.732 3775.939 7.856 580.148 1.000 1.000 0.980

 W Kg/sec = 25.787 Wdry = 56.727 WH2O = 0.005 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 112.272 3570.373 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 101155.953 44512.859 1.562 513.330 328.681 395.845 1.204

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 472.94 -0.16 472.94 0.41 0.69 600.07

 MEAN 16.97 0.00 -0.02 472.94 -0.16 472.94 0.41 0.63

 HUB 14.32 0.00 -0.02 472.94 -0.16 472.94 0.41 0.58

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.31 46.36 6.95 634.64 791.61 7.01 562.18 508.50 0.10

 MEAN 49.79 43.80 5.99 559.21 732.51 7.01 562.18 508.50 0.10

 HUB 44.94 37.84 7.10 471.86 668.19 7.01 562.18 508.50 0.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 552.80 284.37 474.05 1176.59 0.47 2.16 1.89 8.34

 MEAN 16.57 564.65 295.55 481.13 1173.00 0.48 2.24 1.97 6.35

 HUB 13.89 611.27 367.15 488.73 1169.62 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 622.12 582.07 337.75 0.49 5371.96 0.92 0.91

 MEAN 546.13 542.47 250.58 0.46 4901.17 0.92 0.91 0.91 1.46

 HUB 457.69 497.05 90.55 0.42 5102.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.21 1.17 7.93 608.59 1.05 584.04 518.83 0.06

 MEAN 9.08 1.16 7.77 606.10 1.04 580.48 517.97 0.06

 HUB 9.14 1.16 7.60 607.16 1.05 577.14 518.35 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.96 35.47 31.50 3.97 0.93 0.39 1.40

 MEAN 31.56 27.51 23.50 4.01 0.92 0.38 1.62

 HUB 36.91 10.50 6.50 4.00 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 610.9291 297.2119 533.7598 1169.7344 0.5223 -0.1230 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1301 7.5988 577.3047 518.3642 0.0688 29.1102 32.4000 3.2898

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 528.6149 118.5529 515.1494 1177.3425 0.4490 0.1321 2.2705

 

NASA/TM—2013-218094 J–232
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1129 7.9495 584.8394 518.2952 432.2457 0.0226 0.3172

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 524.3044 0.0000 524.3044 1177.6809 0.4452 0.2269 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9462 585.2067 518.2352 0.0000 0.0600 0.0403 0.1296

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8767 9.0884 1.1569 607.2849 27.1372 251.3478 1.9484

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 168939.688 0.436 541.613 524924.063 0.892143E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.346 EfDer = 1.000 SH = 0.892143E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 56.732 3775.939 9.088 607.285 1.000 1.000 0.980

 W Kg/sec = 25.787 Wdry = 56.727 WH2O = 0.005 lbm/sec H2O = 0.054g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 99.287 3489.690 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 89726.383 44512.859 1.753 509.668 290.688 384.739 1.324

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 422.52 -0.15 422.52 0.36 0.62 557.89

 MEAN 15.91 0.00 -0.02 422.52 -0.15 422.52 0.36 0.57

 HUB 13.07 0.00 -0.02 422.52 -0.15 422.52 0.36 0.51

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.02 47.36 7.66 603.67 736.96 8.33 592.95 518.21 0.05

 MEAN 51.15 44.80 6.35 524.35 673.51 8.33 592.95 518.21 0.05

 HUB 45.56 38.84 6.72 430.67 603.43 8.33 592.95 518.21 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 513.60 285.25 427.11 1205.48 0.43 2.05 1.78 7.43

 MEAN 15.50 518.70 283.81 434.17 1201.32 0.43 2.13 1.86 5.75

 HUB 12.59 553.38 333.47 441.61 1197.32 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 591.15 525.35 305.90 0.44 5119.96 0.92 0.91

 MEAN 510.67 489.86 226.86 0.41 4400.70 0.92 0.91 0.91 1.51

 HUB 414.86 449.05 81.39 0.38 4200.28 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.51 1.16 9.29 634.38 1.04 613.20 527.39 0.03

 MEAN 10.30 1.13 9.08 630.57 1.04 608.97 526.13 0.04

 HUB 10.24 1.13 8.86 629.51 1.04 604.92 525.79 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.74 35.61 31.50 4.11 0.93 0.42 1.40

 MEAN 33.17 27.59 23.50 4.09 0.93 0.40 1.64

 HUB 37.06 10.44 6.50 3.94 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 578.3240 289.0150 500.9282 1196.9812 0.4832 -0.2022 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3240 8.8182 604.6375 526.3936 0.0386 29.9832 33.0000 3.0168

 

NASA/TM—2013-218094 J–233
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 506.7296 115.7121 493.3412 1203.1403 0.4212 0.0413 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2971 9.1289 610.8739 526.3164 410.5396 0.0411 0.3323

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 490.7122 0.0000 490.7122 1204.3737 0.4074 0.2537 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2002 612.1589 526.3174 0.0000 0.0600 0.0397 0.0974

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8796 10.2989 1.1332 631.4884 24.2042 257.8208 1.9986

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 150762.609 0.431 483.338 532497.438 0.892853E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3213 Tt4 = 631.4884 T1 = 477.9195

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 955546.19 3063.4370 187.7085 2.4150 0.8569 4.3807 1.3213 37.3740

NASA/TM—2013-218094 J–234
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 76.8% 07-05-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 4.712 EfDer = 0.996 SH = 0.883566E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.789 3744.068 4.265 477.919 1.000 1.000 0.980

 W Kg/sec = 25.359 Wdry = 55.784 WH2O = 0.005 lbm/sec H2O = 0.031g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 184.591 3900.533 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 151410.797 43773.602 1.539 831.557 540.332 619.754 1.147

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 436.99 -0.15 436.99 0.42 0.77 702.20

 MEAN 17.06 0.00 -0.02 436.99 -0.15 436.99 0.42 0.68

 HUB 12.51 0.00 -0.02 436.99 -0.15 436.99 0.42 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.05 50.47 6.58 674.05 803.43 3.79 462.56 460.79 2.14

 MEAN 51.91 47.20 4.71 557.41 708.40 3.79 462.56 460.79 2.14

 HUB 43.10 38.62 4.48 408.74 598.46 3.79 462.56 460.79 2.14

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 673.87 365.52 566.12 1068.02 0.63 7.29 6.52 16.04

 MEAN 18.04 712.02 411.09 581.36 1062.55 0.67 7.43 6.80 12.53

 HUB 15.00 825.67 551.21 614.73 1051.81 0.78 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 674.05 644.73 308.53 0.60 7543.80 0.92 0.91

 MEAN 589.29 608.06 178.20 0.57 7417.01 0.92 0.91 0.91 1.29

 HUB 490.10 617.76 61.11 0.59 8270.04 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.55 1.30 4.26 517.57 1.08 481.04 482.66 1.07

 MEAN 5.53 1.30 4.11 516.90 1.08 476.13 482.43 1.27

 HUB 5.69 1.33 3.80 521.38 1.09 466.55 484.98 1.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.85 28.59 24.20 4.39 0.93 0.32 1.80

 MEAN 35.26 17.04 12.70 4.34 0.92 0.28 2.22

 HUB 41.88 -5.68 -9.30 3.62 0.92 0.13 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 757.2552 410.2925 636.4711 1058.4908 0.7154 -0.0827 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.5751 3.9789 472.4975 483.3521 1.4430 32.8073 35.4000 2.5927

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 602.2075 147.3183 583.9102 1077.3047 0.5590 0.2864 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.5447 4.4961 489.4510 482.9207 554.9116 0.0298 0.4032

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 598.6039 0.0000 598.6039 1077.6659 0.5555 0.3185 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.4873 489.8024 482.8493 0.0000 0.0600 0.0462 0.2807

NASA/TM—2013-218094 J–235
 

 STAGE EXIT CONDITIONS, STAGE 1 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8668 5.5196 1.2943 518.6165 40.6975 225.2056 1.7458

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 253043.281 0.557 797.772 607035.188 0.890178E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 5.647 EfDer = 0.999 SH = 0.891327E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.789 3744.068 5.520 518.616 1.000 1.000 0.980

 W Kg/sec = 25.359 Wdry = 55.784 WH2O = 0.005 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 148.568 3744.369 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 131138.234 43773.582 1.358 590.487 434.896 468.502 1.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 533.00 -0.18 533.00 0.49 0.79 671.47

 MEAN 18.08 0.00 -0.02 533.00 -0.18 533.00 0.49 0.73

 HUB 15.21 0.00 -0.02 533.00 -0.18 533.00 0.49 0.67

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.56 46.36 5.20 671.43 857.42 4.69 495.77 482.77 0.64

 MEAN 47.95 42.30 5.65 590.67 795.74 4.69 495.77 482.77 0.64

 HUB 43.01 37.84 5.17 496.96 728.86 4.69 495.77 482.77 0.64

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 602.93 292.73 527.10 1111.25 0.54 2.33 2.04 9.02

 MEAN 18.01 619.58 309.90 536.50 1107.27 0.56 2.40 2.13 7.35

 HUB 15.22 675.36 396.66 546.60 1103.61 0.61 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 667.19 646.57 374.46 0.58 5981.30 0.92 0.91

 MEAN 588.44 604.50 278.54 0.55 5584.69 0.92 0.91 0.91 1.42

 HUB 497.38 555.80 100.72 0.50 6041.18 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.71 1.22 5.51 550.04 1.06 520.81 496.96 0.30

 MEAN 6.63 1.20 5.37 547.96 1.06 517.09 496.09 0.33

 HUB 6.72 1.22 5.24 550.36 1.06 513.68 497.16 0.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 29.05 35.39 31.50 3.89 0.93 0.37 1.40

 MEAN 30.01 27.44 23.50 3.94 0.92 0.36 1.63

 HUB 35.97 10.44 6.50 3.94 0.92 0.38 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 695.0789 310.7745 621.7346 1100.2775 0.6317 -0.1933 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6728 5.1162 510.6126 496.7747 0.3983 26.5582 30.6000 4.0418

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 586.2628 124.2919 572.9360 1112.2950 0.5271 0.1095 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6484 5.5148 521.8214 496.5969 491.5697 0.0285 0.2759

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 614.7739 0.0000 614.7739 1109.3358 0.5542 0.1770 0.5911

NASA/TM—2013-218094 J–236
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3917 519.0717 496.5608 0.0000 0.0600 0.0457 0.0159

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8696 6.6259 1.2004 549.4547 30.8385 257.9878 1.9999

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 191815.234 0.431 604.738 546218.875 0.891912E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 5.898 EfDer = 0.999 SH = 0.891912E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.789 3744.068 6.626 549.455 1.000 1.000 0.980

 W Kg/sec = 25.359 Wdry = 55.784 WH2O = 0.005 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 127.389 3637.776 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 113345.523 43773.586 1.463 545.479 372.917 424.468 1.138

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 498.70 -0.17 498.70 0.45 0.74 637.11

 MEAN 17.74 0.00 -0.02 498.70 -0.17 498.70 0.45 0.68

 HUB 15.05 0.00 -0.02 498.70 -0.17 498.70 0.45 0.63

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 52.75 46.36 6.39 655.75 823.97 5.79 529.46 496.48 0.23

 MEAN 49.30 43.40 5.90 579.57 764.72 5.79 529.46 496.48 0.23

 HUB 44.61 38.84 5.77 491.73 700.48 5.79 529.46 496.48 0.23

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 577.44 292.98 497.59 1145.16 0.50 2.26 1.98 8.75

 MEAN 17.51 592.22 308.74 505.37 1141.54 0.52 2.34 2.07 6.78

 HUB 14.85 644.78 389.58 513.78 1138.18 0.57 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 647.26 610.82 354.27 0.53 5807.45 0.92 0.91 

 MEAN 571.99 569.83 263.25 0.50 5408.06 0.92 0.91 0.91 1.45

 HUB 485.20 522.60 95.62 0.46 5787.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.93 1.20 6.68 579.96 1.06 553.16 508.68 0.12

 MEAN 7.83 1.18 6.53 577.86 1.05 549.67 507.89 0.13

 HUB 7.92 1.20 6.39 579.86 1.06 546.44 508.68 0.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 30.49 35.45 31.50 3.95 0.93 0.38 1.40

 MEAN 31.42 27.52 23.50 4.02 0.92 0.38 1.62

 HUB 37.17 10.54 6.50 4.04 0.92 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 657.8361 310.7680 579.8030 1136.0631 0.5790 -0.1747 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8812 6.2968 544.4477 508.4127 0.1528 28.1908 31.5000 3.3092

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 559.3740 122.0237 545.9024 1146.0735 0.4881 0.1163 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8607 6.6926 554.0786 508.3047 451.3937 0.0250 0.3016

 

NASA/TM—2013-218094 J–237
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 571.2308 0.0000 571.2308 1144.9320 0.4989 0.2090 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6280 553.0046 508.2571 0.0000 0.0600 0.0404 0.0688

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8768 7.8399 1.1832 579.2253 29.7711 246.1982 1.9085

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 185247.438 0.442 584.031 521492.688 0.892440E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 6.294 EfDer = 1.000 SH = 0.892440E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.789 3744.068 7.840 579.225 1.000 1.000 0.980

 W Kg/sec = 25.359 Wdry = 55.784 WH2O = 0.005 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 110.541 3543.057 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 99213.461 43773.582 1.586 513.330 323.615 395.845 1.223

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 463.86 -0.16 463.86 0.40 0.68 595.48

 MEAN 16.97 0.00 -0.02 463.86 -0.16 463.86 0.40 0.63

 HUB 14.32 0.00 -0.02 463.86 -0.16 463.86 0.40 0.57

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.61 46.36 7.25 629.29 781.90 7.02 561.94 508.22 0.10

 MEAN 50.09 43.80 6.29 554.49 723.05 7.02 561.94 508.22 0.10

 HUB 45.26 37.84 7.42 467.88 658.96 7.02 561.94 508.22 0.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 545.92 285.49 465.31 1176.15 0.46 2.16 1.89 8.34

 MEAN 16.57 557.21 295.69 472.28 1172.54 0.48 2.24 1.97 6.35

 HUB 13.89 602.86 365.06 479.76 1169.14 0.52 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 616.87 571.25 331.38 0.49 5393.19 0.92 0.91

 MEAN 541.52 532.43 245.83 0.45 4903.37 0.92 0.91 0.91 1.47

 HUB 453.83 487.90 88.77 0.42 5072.92 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.19 1.17 7.94 607.54 1.05 583.60 518.54 0.06

 MEAN 9.06 1.16 7.78 604.97 1.04 580.02 517.64 0.07

 HUB 9.10 1.16 7.61 605.86 1.05 576.66 517.97 0.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.53 35.46 31.50 3.96 0.93 0.40 1.40

 MEAN 32.05 27.50 23.50 4.00 0.93 0.39 1.62

 HUB 37.27 10.48 6.50 3.98 0.93 0.40 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 602.0938 297.3487 523.5463 1169.4303 0.5149 -0.1205 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1028 7.6144 577.0034 518.0279 0.0696 29.5945 32.4000 2.8055

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 518.4066 116.2635 505.2012 1177.0375 0.4404 0.1429 2.2705

 

NASA/TM—2013-218094 J–238
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0871 7.9673 584.5358 517.9631 432.2457 0.0217 0.3241

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 514.1668 0.0000 514.1668 1177.3629 0.4367 0.2349 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9640 584.8900 517.9051 0.0000 0.0600 0.0393 0.1404

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8786 9.0635 1.1561 606.1228 26.8983 248.4655 1.9261

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 167451.156 0.440 527.925 515234.469 0.893025E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.614 EfDer = 1.000 SH = 0.893025E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 55.789 3744.068 9.063 606.123 1.000 1.000 0.980

 W Kg/sec = 25.359 Wdry = 55.784 WH2O = 0.005 lbm/sec H2O = 0.054g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 97.813 3463.551 1.381 0.249 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 88121.492 43773.582 1.780 509.668 286.372 384.739 1.343 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 414.96 -0.14 414.96 0.35 0.61 553.71

 MEAN 15.91 0.00 -0.02 414.96 -0.14 414.96 0.35 0.56

 HUB 13.07 0.00 -0.02 414.96 -0.14 414.96 0.35 0.50

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.27 47.36 7.91 598.57 728.46 8.34 592.30 517.88 0.05

 MEAN 51.41 44.80 6.61 519.93 665.33 8.34 592.30 517.88 0.05

 HUB 45.83 38.84 6.99 427.04 595.55 8.34 592.30 517.88 0.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 507.74 285.61 419.79 1204.62 0.42 2.05 1.78 7.43

 MEAN 15.50 512.29 283.51 426.69 1200.48 0.43 2.13 1.86 5.75

 HUB 12.59 546.07 331.45 433.98 1196.49 0.46 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 586.16 516.29 300.55 0.43 5126.47 0.92 0.91

 MEAN 506.36 481.38 222.85 0.40 4395.93 0.92 0.91 0.91 1.52

 HUB 411.36 441.27 79.90 0.37 4174.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.47 1.16 9.28 633.02 1.04 612.32 527.02 0.03

 MEAN 10.26 1.13 9.07 629.19 1.04 608.12 525.76 0.04

 HUB 10.20 1.13 8.86 628.03 1.04 604.08 525.38 0.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.23 35.60 31.50 4.10 0.93 0.43 1.40

 MEAN 33.60 27.58 23.50 4.08 0.93 0.40 1.64

 HUB 37.37 10.43 6.50 3.93 0.93 0.39 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 570.3671 288.7042 491.9029 1196.3171 0.4768 -0.1994 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.2856 8.8210 603.9633 526.0136 0.0393 30.4092 33.0000 2.5908

 

NASA/TM—2013-218094 J–239
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 497.4424 113.5914 484.2994 1202.4937 0.4137 0.0531 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2610 9.1350 610.2148 525.9418 410.5396 0.0397 0.3383

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 481.8709 0.0000 481.8709 1203.6702 0.4003 0.2606 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.2026 611.4413 525.9412 0.0000 0.0600 0.0389 0.1076

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8809 10.2621 1.1322 630.0807 23.9587 255.2953 1.9790

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 149231.328 0.434 470.483 523279.656 0.893774E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.3184 Tt4 = 630.0807 T1 = 477.9194

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 946788.44 2984.9492 184.5910 2.4063 0.8608 4.7120 1.3184 37.3740

NASA/TM—2013-218094 J–240
Appendix K: NPSS cycle analysis for the descent conditions 

 5μm, 2 g/m3, ISA +18R

************************************************************************************************************************************ 

Date:05/10/13 Time:11:02:24 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 463.46 Stator 1 exit: 470.96 Stator 2 inlet: 480.37 Stator 2 exit: 485.22 

 Stator 3 inlet: 494.89 Stator 3 exit: 499.30 Stator 4 inlet: 508.32 Stator 4 exit: 512.06 

 Stator 5 inlet: 519.46 Stator 5 exit: 522.70 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.76 

Fan Bypass Relative Humidity 1.23 

LPC Inlet Relative Humidity 1.13 

LPC Exit Relative Humidity 0.10 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 186.05 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 454.86 

Additional Water at LPC Exit 0.0051221 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 257.43 631.1 1.1046 697.06 8.6926 772.64 9.498 0.736 10.000 1711.4 1618.8 1126.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.43 4.267 457.74 -20.96 0.0000 832.95 2.854 407.97 2541.1 0.7800 1.40084 0.0000295 257.42 0.008 0.0000

FS1 Inlet.Fl_O 257.43 4.267 457.74 -20.96 0.0000 832.95 3.892 445.87 4168.2 0.3645 1.40084 0.0000295 257.42 0.008 0.0000

FS12 Splitter.Fl_02 230.87 4.265 457.74 -20.96 0.0000 747.39 3.839 444.17 3531.8 0.3904 1.40084 0.0000295 230.86 0.007 0.0000

FS2 Splitter.Fl_01 26.56 4.265 457.74 -20.96 0.0000 85.98 4.171 454.86 830.5 0.1779 1.40084 0.0000295 26.56 0.001 0.0000

FS14 Fan.Fl_O 230.87 4.820 475.75 -16.64 0.0000 674.18 4.044 452.46 2606.7 0.5068 1.40070 0.0000295 230.86 0.007 0.0000

FS23 LPC.Fl_O 26.56 6.666 532.40 -3.05 0.0000 59.33 6.378 525.73 412.6 0.2518 1.40004 0.0000295 26.56 0.001 0.0000

FS24 VaporIN.Fl_O 26.70 6.666 539.36 -30.78 0.0000 60.02 6.370 532.42 412.6 0.2555 1.39923 0.0051516 26.56 0.137 0.0051

FS25 Bleed2.Fl_O 24.03 6.666 539.36 -30.78 0.0000 54.02 6.428 533.81 412.6 0.2282 1.39923 0.0051516 23.90 0.123 0.0051

FS3 HPC.Fl_O 22.86 40.527 976.91 76.09 0.0000 11.38 35.644 942.82 49.7 0.4347 1.38133 0.0051516 22.74 0.117 0.0051

FS36 Bleed3.Fl_O 17.72 40.527 976.91 76.09 0.0000 8.82 37.725 957.76 49.3 0.3235 1.38133 0.0051516 17.63 0.091 0.0051

FS4 Burner.Fl_O 17.91 39.594 1711.35 63.90 0.0110 12.08 37.383 1687.04 74.6 0.2947 1.33108 0.0051516 17.63 0.091 0.0184

FS45 HPT.Fl_O 23.94 9.499 1130.07 -39.67 0.0082 54.67 8.601 1100.35 265.4 0.3835 1.36604 0.0051516 23.62 0.122 0.0151

FS49 LPT.Fl_O 24.22 3.261 885.66 -99.71 0.0081 142.62 3.070 871.00 860.2 0.2969 1.38136 0.0051516 23.90 0.123 0.0150

FS5 TEGV.Fl_O 24.22 3.261 885.73 -99.71 0.0081 142.63 3.070 871.07 860.2 0.2969 1.38136 0.0051516 23.90 0.123 0.0150

FS8 Core_Nozz.Fl_O 24.22 3.261 885.80 -99.71 0.0081 142.64 2.854 853.73 613.5 0.4432 1.38135 0.0051516 23.90 0.123 0.0150

FS17 FanDuctLkg.Fl_O 230.87 4.820 475.75 -16.64 0.0000 674.18 4.044 452.46 2606.7 0.5068 1.40070 0.0000295 230.86 0.007 0.0000

FS171 Bleed15.Fl_O 233.54 4.820 476.48 -16.80 0.0000 682.50 3.910 448.81 2481.9 0.5546 1.40069 0.0000877 233.52 0.020 0.0001

FS172 FanDuct.Fl_O 233.54 4.820 476.48 -16.80 0.0000 682.50 3.910 448.81 2481.9 0.5546 1.40069 0.0000877 233.52 0.020 0.0001

FS173 Byp_Nozz.Fl_O 233.54 4.820 476.48 -16.80 0.0000 682.50 2.854 410.12 2006.9 0.8984 1.40069 0.0000877 233.52 0.020 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 747.39 1.130 0.9056 2571.761 1.0393 0.9073 -1409.8 1585.81 54.78

LPC 85.98 1.563 0.8352 2571.761 1.1631 0.8452 -672.7 6.98 3.75

HPC 54.02 6.080 0.8183 8958.397 1.8112 0.8570 -3544.8 61.41 58.06

HPT 12.08 4.168 0.8749 220.829 1.3651 0.8525 3544.8 

LPT 54.67 2.913 0.8525 71.869 1.2742 0.8326 2082.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 868.39 1.127 0.9075 2547.239 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 74.06 1.524 0.7801 0.679 0.0000 1.1609 1.0752 1.0706 0.0003

HPC 49.13 5.841 0.8268 8719.572 10.9737 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.081 0.8749 1.327 4.0806 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.439 0.8589 0.808 2.4386 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–1
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2541.05 6182.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8842 759.97 22.65 9.499

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2811 759.97 22.65 3.261

TEGV 0.0000 0.2969 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.04 17.31 14.115

FanDuct 0.0000 0.5546 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 873.36 50.44 27.660

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.04 17.31 14.115

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 976.91 76.09 40.527

Splitter 8.6926 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.04 17.31 14.115

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9135.3 2038.0 3544.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6696 539.36 -30.78 6.666

LP_Shaft 2416.0 4527.0 2082.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7433 976.91 76.09 39.594

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4004 976.91 76.09 22.379

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.91 76.09 40.527

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.91 76.09 40.527

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.91 76.09 40.527

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.75 -16.64 4.820

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.75 -16.64 4.820

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.75 -16.64 4.820

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.75 -16.64 4.820

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1711.30 0.9995 0.0230 0.19363 0.01099 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.443 619.3 466.2

Byp_Nozz 1.689 0.9800 1.0000 0.9800 2006.86 0.898 874.4 6346.9

NASA/TM—2013-218094 K–2
************************************************************************************************************************************ 

Date:05/10/13 Time:11:03:04 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 59/ 3/13 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.93 Stator 1 exit: 463.94 Stator 2 inlet: 472.74 Stator 2 exit: 477.26 

 Stator 3 inlet: 486.30 Stator 3 exit: 490.39 Stator 4 inlet: 498.82 Stator 4 exit: 502.29 

 Stator 5 inlet: 509.20 Stator 5 exit: 512.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.24 

Fan Bypass Relative Humidity 1.60 

LPC Inlet Relative Humidity 1.44 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 723.11 Fan/LPC Inlet Flow Velocity 179.78 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 448.87 

Additional Water at LPC Exit 0.0042001 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 18.00 250.47 617.3 1.0753 663.74 8.7698 723.11 9.219 0.763 10.000 1682.4 1590.5 1108.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 250.47 4.201 451.57 -22.43 0.0000 817.49 2.947 407.97 2558.5 0.7300 1.40089 0.0000285 250.47 0.007 0.0000

FS1 Inlet.Fl_O 250.47 4.201 451.57 -22.43 0.0000 817.49 3.848 440.34 4168.2 0.3565 1.40089 0.0000285 250.47 0.007 0.0000

FS12 Splitter.Fl_02 224.84 4.199 451.57 -22.43 0.0000 734.18 3.797 438.72 3531.8 0.3821 1.40089 0.0000285 224.83 0.006 0.0000

FS2 Splitter.Fl_01 25.64 4.199 451.57 -22.43 0.0000 83.72 4.112 448.87 830.5 0.1730 1.40089 0.0000285 25.64 0.001 0.0000

FS14 Fan.Fl_O 224.84 4.713 468.33 -18.41 0.0000 666.15 3.977 446.12 2606.7 0.4983 1.40077 0.0000285 224.83 0.006 0.0000

FS23 LPC.Fl_O 25.64 6.423 521.36 -5.70 0.0000 58.81 6.151 514.95 412.6 0.2494 1.40020 0.0000285 25.64 0.001 0.0000

FS24 VaporIN.Fl_O 25.75 6.423 527.16 -28.44 0.0000 59.38 6.145 520.53 412.6 0.2525 1.39954 0.0042286 25.64 0.108 0.0042

FS25 Bleed2.Fl_O 23.17 6.423 527.16 -28.44 0.0000 53.45 6.200 521.86 412.6 0.2255 1.39954 0.0042286 23.07 0.098 0.0042

FS3 HPC.Fl_O 22.05 38.732 953.52 75.46 0.0000 11.34 34.103 920.44 49.7 0.4326 1.38287 0.0042286 21.95 0.093 0.0042

FS36 Bleed3.Fl_O 17.09 38.732 953.52 75.46 0.0000 8.79 36.074 934.91 49.3 0.3221 1.38287 0.0042286 17.01 0.072 0.0042

FS4 Burner.Fl_O 17.27 37.840 1682.41 63.43 0.0108 12.08 35.728 1658.42 74.6 0.2946 1.33269 0.0042286 17.01 0.072 0.0173

FS45 HPT.Fl_O 23.08 9.192 1112.08 -37.23 0.0081 54.04 8.346 1083.56 265.4 0.3779 1.36742 0.0042286 22.80 0.096 0.0140

FS49 LPT.Fl_O 23.35 3.311 881.94 -93.56 0.0080 135.17 3.138 868.95 860.2 0.2796 1.38177 0.0042286 23.07 0.098 0.0139

FS5 TEGV.Fl_O 23.35 3.311 882.01 -93.56 0.0080 135.17 3.138 869.02 860.2 0.2796 1.38177 0.0042286 23.07 0.098 0.0139

FS8 Core_Nozz.Fl_O 23.35 3.311 882.08 -93.56 0.0080 135.18 2.947 854.07 613.4 0.4139 1.38176 0.0042286 23.07 0.098 0.0139

FS17 FanDuctLkg.Fl_O 224.84 4.713 468.33 -18.41 0.0000 666.15 3.977 446.12 2606.7 0.4983 1.40077 0.0000285 224.83 0.006 0.0000

FS171 Bleed15.Fl_O 227.41 4.713 469.00 -18.53 0.0000 674.26 3.852 442.69 2481.9 0.5445 1.40076 0.0000759 227.39 0.017 0.0001

FS172 FanDuct.Fl_O 227.41 4.713 469.00 -18.53 0.0000 674.26 3.852 442.69 2481.9 0.5445 1.40076 0.0000759 227.39 0.017 0.0001

FS173 Byp_Nozz.Fl_O 227.41 4.713 469.00 -18.53 0.0000 674.26 2.947 410.01 2006.9 0.8471 1.40076 0.0000759 227.39 0.017 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 734.18 1.122 0.9048 2506.966 1.0371 0.9064 -1277.8 2157.02 54.66

LPC 83.72 1.530 0.8363 2506.966 1.1546 0.8458 -606.9 6.78 3.35

HPC 53.45 6.030 0.8176 8940.025 1.8088 0.8563 -3323.8 61.25 57.86

HPT 12.08 4.117 0.8735 219.735 1.3620 0.8510 3323.8 

LPT 54.04 2.776 0.8468 70.145 1.2590 0.8271 1884.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 853.04 1.120 0.9066 2483.062 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 71.25 1.495 0.7770 0.662 0.0000 1.1749 1.0707 1.0762 0.0003

HPC 48.61 5.793 0.8261 8701.690 10.9899 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.030 0.8735 1.321 4.0303 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.336 0.8531 0.789 2.3358 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–3
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2558.49 5629.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8527 741.99 23.51 9.192

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2711 741.99 23.51 3.311

TEGV 0.0000 0.2796 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.63 18.31 13.531

FanDuct 0.0000 0.5445 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 852.52 50.52 26.455

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.63 18.31 13.531

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 953.52 75.46 38.732

Splitter 8.7698 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.63 18.31 13.531

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9012.9 1936.9 3323.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5745 527.16 -28.44 6.423

LP_Shaft 2339.2 4231.5 1884.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6456 953.52 75.46 37.840

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3150 953.52 75.46 21.454

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 953.52 75.46 38.732

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 953.52 75.46 38.732

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 953.52 75.46 38.732

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 468.33 -18.41 4.713

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 468.33 -18.41 4.713

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 468.33 -18.41 4.713

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 468.33 -18.41 4.713

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1682.35 0.9995 0.0230 0.18437 0.01084 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.414 578.4 419.9

Byp_Nozz 1.599 0.9800 1.0000 0.9800 2006.86 0.847 824.4 5826.8

NASA/TM—2013-218094 K–4
************************************************************************************************************************************ 

Date:05/10/13 Time:11:03:21 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 454.91 Stator 1 exit: 461.74 Stator 2 inlet: 470.30 Stator 2 exit: 474.69 

 Stator 3 inlet: 483.50 Stator 3 exit: 487.47 Stator 4 inlet: 495.68 Stator 4 exit: 499.04 

 Stator 5 inlet: 505.77 Stator 5 exit: 508.68 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.40 

Fan Bypass Relative Humidity 1.74 

LPC Inlet Relative Humidity 1.56 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 707.26 Fan/LPC Inlet Flow Velocity 177.40 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 447.05 

Additional Water at LPC Exit 0.0037136 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 18.00 257.21 630.5 1.0705 675.00 8.7997 707.26 9.100 0.772 10.000 1670.8 1579.3 1100.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.21 4.339 449.68 -22.87 0.0000 811.10 3.088 407.97 2563.0 0.7140 1.40090 0.0000272 257.21 0.007 0.0000

FS1 Inlet.Fl_O 257.21 4.339 449.68 -22.87 0.0000 811.10 3.980 438.70 4168.2 0.3533 1.40090 0.0000272 257.21 0.007 0.0000

FS12 Splitter.Fl_02 230.97 4.337 449.68 -22.87 0.0000 728.70 3.928 437.11 3531.8 0.3787 1.40090 0.0000272 230.96 0.006 0.0000

FS2 Splitter.Fl_01 26.25 4.337 449.68 -22.87 0.0000 82.81 4.249 447.05 830.5 0.1711 1.40090 0.0000272 26.25 0.001 0.0000

FS14 Fan.Fl_O 230.97 4.855 465.97 -18.97 0.0000 662.71 4.106 444.18 2606.7 0.4947 1.40079 0.0000272 230.96 0.006 0.0000

FS23 LPC.Fl_O 26.25 6.577 517.63 -6.59 0.0000 58.59 6.300 511.31 412.6 0.2484 1.40024 0.0000272 26.25 0.001 0.0000

FS24 VaporIN.Fl_O 26.34 6.577 522.79 -26.70 0.0000 59.10 6.294 516.28 412.6 0.2511 1.39967 0.0037408 26.25 0.098 0.0037

FS25 Bleed2.Fl_O 23.71 6.577 522.79 -26.70 0.0000 53.19 6.350 517.58 412.6 0.2243 1.39967 0.0037408 23.62 0.088 0.0037

FS3 HPC.Fl_O 22.56 39.490 944.85 76.06 0.0000 11.33 34.782 912.13 49.7 0.4319 1.38345 0.0037408 22.48 0.084 0.0037

FS36 Bleed3.Fl_O 17.48 39.490 944.85 76.06 0.0000 8.78 36.786 926.44 49.3 0.3217 1.38345 0.0037408 17.42 0.065 0.0037

FS4 Burner.Fl_O 17.67 38.580 1670.79 64.10 0.0108 12.08 36.427 1646.92 74.6 0.2945 1.33337 0.0037408 17.42 0.065 0.0168

FS45 HPT.Fl_O 23.62 9.412 1104.81 -35.44 0.0080 53.83 8.554 1076.71 265.4 0.3760 1.36800 0.0037408 23.35 0.087 0.0135

FS49 LPT.Fl_O 23.90 3.451 880.02 -90.37 0.0079 132.54 3.279 867.60 860.2 0.2736 1.38198 0.0037408 23.62 0.088 0.0134

FS5 TEGV.Fl_O 23.90 3.451 880.09 -90.37 0.0079 132.55 3.279 867.67 860.2 0.2736 1.38198 0.0037408 23.62 0.088 0.0134

FS8 Core_Nozz.Fl_O 23.90 3.451 880.16 -90.37 0.0079 132.55 3.088 853.50 613.4 0.4039 1.38197 0.0037408 23.62 0.088 0.0134

FS17 FanDuctLkg.Fl_O 230.97 4.855 465.97 -18.97 0.0000 662.71 4.106 444.18 2606.7 0.4947 1.40079 0.0000272 230.96 0.006 0.0000

FS171 Bleed15.Fl_O 233.60 4.855 466.62 -19.06 0.0000 670.74 3.980 440.83 2481.9 0.5402 1.40078 0.0000689 233.59 0.016 0.0001

FS172 FanDuct.Fl_O 233.60 4.855 466.62 -19.06 0.0000 670.74 3.980 440.83 2481.9 0.5402 1.40078 0.0000689 233.59 0.016 0.0001

FS173 Byp_Nozz.Fl_O 233.60 4.855 466.62 -19.06 0.0000 670.74 3.088 409.96 2006.9 0.8302 1.40078 0.0000689 233.59 0.016 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 728.70 1.119 0.9044 2480.486 1.0362 0.9059 -1276.0 2532.49 54.59

LPC 82.81 1.516 0.8368 2480.486 1.1511 0.8461 -604.9 6.70 3.28

HPC 53.19 6.005 0.8172 8931.793 1.8073 0.8560 -3363.9 61.28 57.86

HPT 12.08 4.099 0.8729 219.379 1.3610 0.8503 3363.9 

LPT 53.83 2.727 0.8445 69.486 1.2534 0.8250 1880.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 846.67 1.117 0.9063 2456.835 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.11 1.483 0.7758 0.655 0.0000 1.1812 1.0695 1.0787 0.0003

HPC 48.38 5.769 0.8256 8693.677 10.9915 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.013 0.8728 1.318 4.0134 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.299 0.8508 0.782 2.2988 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–5
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2562.99 5654.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8725 735.41 24.68 9.412

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2774 735.41 24.68 3.451

TEGV 0.0000 0.2736 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 714.26 19.54 13.818

FanDuct 0.0000 0.5402 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 844.84 51.40 26.983 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 714.26 19.54 13.818

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 944.85 76.06 39.490

Splitter 8.7997 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 714.26 19.54 13.818

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8967.2 1970.2 3363.9 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6345 522.79 -26.70 6.577

LP_Shaft 2309.6 4277.1 1880.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7072 944.85 76.06 38.580

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3689 944.85 76.06 21.896

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.85 76.06 39.490

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.85 76.06 39.490

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.85 76.06 39.490

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 465.97 -18.97 4.855

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 465.97 -18.97 4.855

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 465.97 -18.97 4.855

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 465.97 -18.97 4.855

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1670.72 0.9995 0.0230 0.18750 0.01076 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.404 564.2 419.0

Byp_Nozz 1.572 0.9800 1.0000 0.9800 2006.86 0.830 807.9 5865.7

NASA/TM—2013-218094 K–6
************************************************************************************************************************************ 

Date:05/10/13 Time:11:03:37 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.54 Stator 1 exit: 462.95 Stator 2 inlet: 470.98 Stator 2 exit: 475.09 

 Stator 3 inlet: 483.34 Stator 3 exit: 487.03 Stator 4 inlet: 494.73 Stator 4 exit: 497.84 

 Stator 5 inlet: 504.13 Stator 5 exit: 506.82 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.00 

Fan Bypass Relative Humidity 2.25 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.22 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 667.90 Fan/LPC Inlet Flow Velocity 171.93 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 414.42 Fan/LPC Inlet Static Temperature 449.15 

Additional Water at LPC Exit 0.0033426 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 18.00 278.75 685.0 1.0571 724.12 8.8754 667.90 8.765 0.795 10.000 1662.7 1571.2 1097.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 278.75 4.831 451.61 -22.45 0.0000 791.22 3.578 414.42 2579.0 0.6690 1.40088 0.0000348 278.74 0.010 0.0000

FS1 Inlet.Fl_O 278.75 4.831 451.61 -22.45 0.0000 791.22 4.453 441.19 4168.2 0.3432 1.40088 0.0000348 278.74 0.010 0.0000

FS12 Splitter.Fl_02 250.52 4.829 451.61 -22.45 0.0000 711.46 4.397 439.67 3531.8 0.3680 1.40088 0.0000348 250.51 0.009 0.0000

FS2 Splitter.Fl_01 28.23 4.829 451.61 -22.45 0.0000 80.16 4.737 449.15 830.5 0.1654 1.40088 0.0000348 28.23 0.001 0.0000

FS14 Fan.Fl_O 250.52 5.366 466.93 -18.78 0.0000 650.98 4.575 446.09 2606.7 0.4827 1.40078 0.0000348 250.51 0.009 0.0000

FS23 LPC.Fl_O 28.23 7.140 515.39 -7.17 0.0000 57.91 6.847 509.25 412.6 0.2453 1.40027 0.0000348 28.23 0.001 0.0000

FS24 VaporIN.Fl_O 28.32 7.140 520.06 -25.28 0.0000 58.37 6.842 513.75 412.6 0.2477 1.39975 0.0033774 28.23 0.095 0.0034

FS25 Bleed2.Fl_O 25.49 7.140 520.06 -25.28 0.0000 52.53 6.901 515.01 412.6 0.2213 1.39975 0.0033774 25.40 0.086 0.0034

FS3 HPC.Fl_O 24.25 42.344 937.10 76.19 0.0000 11.31 37.316 904.75 49.7 0.4309 1.38397 0.0033774 24.17 0.082 0.0034

FS36 Bleed3.Fl_O 18.80 42.344 937.10 76.19 0.0000 8.77 39.456 918.89 49.3 0.3210 1.38397 0.0033774 18.73 0.063 0.0034

FS4 Burner.Fl_O 19.00 41.369 1662.68 64.25 0.0107 12.08 39.060 1638.90 74.6 0.2944 1.33383 0.0033774 18.73 0.063 0.0164

FS45 HPT.Fl_O 25.39 10.201 1101.30 -34.01 0.0080 53.30 9.291 1073.91 265.4 0.3715 1.36830 0.0033774 25.11 0.085 0.0131

FS49 LPT.Fl_O 25.69 3.943 888.52 -85.91 0.0079 125.31 3.768 877.42 860.2 0.2574 1.38156 0.0033774 25.40 0.086 0.0130

FS5 TEGV.Fl_O 25.69 3.943 888.59 -85.91 0.0079 125.32 3.768 877.49 860.2 0.2574 1.38156 0.0033774 25.40 0.086 0.0130

FS8 Core_Nozz.Fl_O 25.69 3.943 888.66 -85.91 0.0079 125.32 3.578 865.10 613.3 0.3774 1.38155 0.0033774 25.40 0.086 0.0130

FS17 FanDuctLkg.Fl_O 250.52 5.366 466.93 -18.78 0.0000 650.98 4.575 446.09 2606.7 0.4827 1.40078 0.0000348 250.51 0.009 0.0000

FS171 Bleed15.Fl_O 253.35 5.366 467.53 -18.86 0.0000 658.76 4.444 442.96 2481.9 0.5260 1.40077 0.0000720 253.33 0.018 0.0001

FS172 FanDuct.Fl_O 253.35 5.366 467.53 -18.86 0.0000 658.76 4.444 442.96 2481.9 0.5260 1.40077 0.0000720 253.33 0.018 0.0001

FS173 Byp_Nozz.Fl_O 253.35 5.366 467.53 -18.86 0.0000 658.76 3.578 416.33 2006.9 0.7832 1.40077 0.0000720 253.33 0.018 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 711.46 1.111 0.9036 2402.972 1.0339 0.9050 -1301.2 5205.99 54.13

LPC 80.16 1.479 0.8382 2402.972 1.1412 0.8469 -610.6 6.43 3.07

HPC 52.53 5.931 0.8159 8910.155 1.8019 0.8548 -3570.6 61.54 58.05

HPT 12.08 4.056 0.8723 218.806 1.3580 0.8499 3570.6 

LPT 53.30 2.587 0.8398 67.567 1.2372 0.8209 1911.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 826.64 1.109 0.9054 2380.060 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.75 1.448 0.7722 0.635 0.0000 1.2009 1.0681 1.0856 0.0003

HPC 47.78 5.698 0.8244 8672.616 10.9836 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.971 0.8723 1.315 3.9709 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.194 0.8460 0.760 2.1936 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–7
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2578.96 5786.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9380 730.10 25.46 10.201

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2982 730.10 25.46 3.943

TEGV 0.0000 0.2574 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 709.20 20.38 14.885

FanDuct 0.0000 0.5260 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 838.24 51.84 28.967

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 709.20 20.38 14.885

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 937.10 76.19 42.344

Splitter 8.8754 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 709.20 20.38 14.885

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8922.0 2101.9 3570.6 WB17Y Bleed> 0.1000 1.0000 1.0000 2.8321 520.06 -25.28 7.140

LP_Shaft 2242.3 4477.7 1911.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.9103 937.10 76.19 41.369

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5466 937.10 76.19 23.541

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 937.10 76.19 42.344

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 937.10 76.19 42.344

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 937.10 76.19 42.344

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 466.93 -18.78 5.366

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 466.93 -18.78 5.366

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 466.93 -18.78 5.366

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 466.93 -18.78 5.366

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1662.62 0.9995 0.0230 0.20114 0.01074 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.377 530.6 423.6

Byp_Nozz 1.500 0.9800 1.0000 0.9800 2006.86 0.783 768.0 6047.9

NASA/TM—2013-218094 K–8
************************************************************************************************************************************ 

Date:05/10/13 Time:11:04:04 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 45/ 2/14 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.17 Stator 1 exit: 470.74 Stator 2 inlet: 477.63 Stator 2 exit: 480.97 

 Stator 3 inlet: 488.14 Stator 3 exit: 491.08 Stator 4 inlet: 497.81 Stator 4 exit: 500.24 

 Stator 5 inlet: 505.66 Stator 5 exit: 507.72 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.96 

Fan Bypass Relative Humidity 3.10 

LPC Inlet Relative Humidity 2.83 

LPC Exit Relative Humidity 0.46 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 617.99 Fan/LPC Inlet Flow Velocity 173.93 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 429.58 Fan/LPC Inlet Static Temperature 458.90 

Additional Water at LPC Exit 0.0034488 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 18.00 305.33 746.5 1.0593 790.75 8.4334 617.99 8.209 0.828 10.000 1667.2 1575.1 1102.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 305.33 5.595 461.42 -20.30 0.0000 756.40 4.358 429.58 2598.1 0.6080 1.40081 0.0000681 305.31 0.021 0.0001

FS1 Inlet.Fl_O 305.33 5.595 461.42 -20.30 0.0000 756.40 5.198 451.80 4168.2 0.3259 1.40081 0.0000681 305.31 0.021 0.0001

FS12 Splitter.Fl_02 272.96 5.592 461.42 -20.30 0.0000 676.55 5.146 450.55 3531.8 0.3469 1.40081 0.0000681 272.94 0.019 0.0001

FS2 Splitter.Fl_01 32.37 5.592 461.42 -20.30 0.0000 80.22 5.486 458.90 830.5 0.1656 1.40081 0.0000681 32.36 0.002 0.0001

FS14 Fan.Fl_O 272.96 6.146 475.40 -16.95 0.0000 624.92 5.325 456.30 2606.7 0.4570 1.40070 0.0000681 272.94 0.019 0.0001

FS23 LPC.Fl_O 32.37 7.851 516.54 -7.08 0.0000 60.46 7.498 509.80 412.6 0.2570 1.40025 0.0000681 32.36 0.002 0.0001

FS24 VaporIN.Fl_O 32.48 7.851 521.34 -25.77 0.0000 60.95 7.491 514.41 412.6 0.2596 1.39972 0.0035169 32.36 0.114 0.0035

FS25 Bleed2.Fl_O 27.61 7.851 521.34 -25.77 0.0000 51.81 7.595 516.43 412.6 0.2181 1.39972 0.0035169 27.51 0.097 0.0035

FS3 HPC.Fl_O 26.27 45.928 936.05 75.15 0.0000 11.29 40.499 903.89 49.7 0.4298 1.38401 0.0035169 26.18 0.092 0.0035

FS36 Bleed3.Fl_O 20.36 45.928 936.05 75.15 0.0000 8.75 42.808 917.94 49.3 0.3203 1.38401 0.0035169 20.29 0.071 0.0035

FS4 Burner.Fl_O 20.58 44.870 1667.23 63.12 0.0108 12.08 42.365 1643.41 74.6 0.2945 1.33353 0.0035169 20.29 0.071 0.0166

FS45 HPT.Fl_O 27.50 11.217 1107.02 -34.56 0.0081 52.64 10.244 1080.30 265.4 0.3662 1.36786 0.0035169 27.19 0.096 0.0133

FS49 LPT.Fl_O 27.83 4.719 911.84 -82.11 0.0080 114.91 4.544 902.40 860.2 0.2346 1.38014 0.0035169 27.51 0.097 0.0132

FS5 TEGV.Fl_O 27.83 4.719 911.92 -82.11 0.0080 114.91 4.544 902.47 860.2 0.2346 1.38014 0.0035169 27.51 0.097 0.0132

FS8 Core_Nozz.Fl_O 27.83 4.719 911.99 -82.11 0.0080 114.92 4.358 892.23 613.4 0.3410 1.38014 0.0035169 27.51 0.097 0.0132

FS17 FanDuctLkg.Fl_O 272.96 6.146 475.40 -16.95 0.0000 624.92 5.325 456.30 2606.7 0.4570 1.40070 0.0000681 272.94 0.019 0.0001

FS171 Bleed15.Fl_O 277.83 6.146 476.21 -17.10 0.0000 636.61 5.177 453.41 2481.9 0.5010 1.40069 0.0001284 277.80 0.036 0.0001

FS172 FanDuct.Fl_O 277.83 6.146 476.21 -17.10 0.0000 636.61 5.177 453.41 2481.9 0.5010 1.40069 0.0001284 277.80 0.036 0.0001

FS173 Byp_Nozz.Fl_O 277.83 6.146 476.21 -17.10 0.0000 636.61 4.358 431.61 2006.9 0.7180 1.40069 0.0001284 277.80 0.036 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 676.55 1.099 0.9026 2257.238 1.0303 0.9039 -1294.1 -----.-- 52.66

LPC 80.22 1.404 0.8528 2257.238 1.1195 0.8597 -605.1 5.94 2.65

HPC 51.81 5.850 0.8145 8886.483 1.7955 0.8534 -3846.1 61.83 58.24

HPT 12.08 4.000 0.8725 218.196 1.3538 0.8503 3846.1 

LPT 52.64 2.377 0.8317 63.988 1.2115 0.8139 1899.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 786.09 1.097 0.9044 2235.715 0.0417 0.8607 1.0235 0.9980 0.9905

LPC 60.58 1.385 0.7657 0.596 0.0000 1.3242 1.0502 1.1138 0.0003

HPC 47.12 5.622 0.8229 8649.575 10.9757 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.917 0.8725 1.311 3.9172 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.036 0.8379 0.720 2.0357 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–9
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2598.14 5864.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0159 730.21 24.69 11.217

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3230 730.21 24.69 4.719

TEGV 0.0000 0.2346 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 709.43 19.64 16.228

FanDuct 0.0000 0.5010 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 837.74 50.93 31.459

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 709.43 19.64 16.228

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 936.05 75.15 45.928

Splitter 8.4334 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 709.43 19.64 16.228

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8909.3 2267.3 3846.1 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8717 521.34 -25.77 7.851

LP_Shaft 2129.0 4685.2 1899.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1521 936.05 75.15 44.870

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7582 936.05 75.15 25.620

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 936.05 75.15 45.928

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 936.05 75.15 45.928

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 936.05 75.15 45.928

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.40 -16.95 6.146

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.40 -16.95 6.146

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.40 -16.95 6.146

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.40 -16.95 6.146

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1667.17 0.9995 0.0230 0.21965 0.01083 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.083 0.9801 1.0000 0.9800 613.40 0.341 486.5 420.8

Byp_Nozz 1.410 0.9800 1.0000 0.9800 2006.86 0.718 716.9 6190.3

NASA/TM—2013-218094 K–10
************************************************************************************************************************************ 

Date:05/10/13 Time:11:04:33 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 48/ 2/17 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.22 Stator 1 exit: 477.33 Stator 2 inlet: 482.00 Stator 2 exit: 483.85 

 Stator 3 inlet: 489.04 Stator 3 exit: 490.47 Stator 4 inlet: 495.44 Stator 4 exit: 496.48 

 Stator 5 inlet: 500.12 Stator 5 exit: 500.87 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.82 

Fan Bypass Relative Humidity 3.93 

LPC Inlet Relative Humidity 3.82 

LPC Exit Relative Humidity 1.17 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 571.13 Fan/LPC Inlet Flow Velocity 193.70 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.36 

Ambient Static Temperature 445.14 Fan/LPC Inlet Static Temperature 469.20 

Additional Water at LPC Exit 0.0031166 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 18.00 330.79 766.2 1.1014 843.96 7.0896 571.13 7.351 0.859 10.000 1676.5 1582.1 1112.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 330.79 6.516 472.33 -18.03 0.0000 711.91 5.297 445.14 2597.0 0.5520 1.40072 0.0001274 330.75 0.042 0.0001

FS1 Inlet.Fl_O 330.79 6.516 472.33 -18.03 0.0000 711.91 6.111 463.72 4168.2 0.3043 1.40072 0.0001274 330.75 0.042 0.0001

FS12 Splitter.Fl_02 289.90 6.513 472.33 -18.03 0.0000 624.22 6.077 463.04 3531.8 0.3163 1.40072 0.0001274 289.86 0.037 0.0001

FS2 Splitter.Fl_01 40.89 6.513 472.33 -18.03 0.0000 88.05 6.364 469.20 830.5 0.1824 1.40072 0.0001274 40.89 0.005 0.0001

FS14 Fan.Fl_O 289.90 7.063 484.59 -15.09 0.0000 583.04 6.262 468.19 2606.7 0.4181 1.40061 0.0001274 289.86 0.037 0.0001

FS23 LPC.Fl_O 40.89 8.237 512.12 -8.48 0.0000 72.49 7.692 502.20 412.6 0.3142 1.40030 0.0001274 40.89 0.005 0.0001

FS24 VaporIN.Fl_O 41.02 8.237 516.49 -25.37 0.0000 73.03 7.682 506.31 412.6 0.3172 1.39982 0.0032440 40.89 0.133 0.0032

FS25 Bleed2.Fl_O 28.71 8.237 516.49 -25.37 0.0000 51.12 7.976 511.76 412.6 0.2150 1.39982 0.0032440 28.62 0.093 0.0032

FS3 HPC.Fl_O 27.32 47.900 926.25 74.26 0.0000 11.20 42.344 895.01 49.7 0.4253 1.38462 0.0032440 27.23 0.088 0.0032

FS36 Bleed3.Fl_O 21.17 47.900 926.25 74.26 0.0000 8.68 44.703 908.63 49.3 0.3173 1.38462 0.0032440 21.10 0.068 0.0032

FS4 Burner.Fl_O 21.41 46.797 1676.50 61.93 0.0111 12.09 44.183 1652.57 74.6 0.2946 1.33294 0.0032440 21.10 0.068 0.0167

FS45 HPT.Fl_O 28.61 12.051 1117.30 -34.37 0.0083 51.21 11.068 1092.03 265.4 0.3545 1.36708 0.0032440 28.28 0.092 0.0133

FS49 LPT.Fl_O 28.95 5.628 943.48 -76.59 0.0082 101.94 5.465 935.92 860.2 0.2068 1.37816 0.0032440 28.62 0.093 0.0132

FS5 TEGV.Fl_O 28.95 5.628 943.55 -76.59 0.0082 101.95 5.465 935.99 860.2 0.2068 1.37816 0.0032440 28.62 0.093 0.0132

FS8 Core_Nozz.Fl_O 28.95 5.628 943.62 -76.59 0.0082 101.95 5.297 928.03 613.4 0.2979 1.37815 0.0032440 28.62 0.093 0.0132

FS17 FanDuctLkg.Fl_O 289.90 7.063 484.59 -15.09 0.0000 583.04 6.262 468.19 2606.7 0.4181 1.40061 0.0001274 289.86 0.037 0.0001

FS171 Bleed15.Fl_O 302.20 7.063 485.89 -15.51 0.0000 608.61 6.067 465.21 2481.9 0.4710 1.40058 0.0002539 302.13 0.077 0.0003

FS172 FanDuct.Fl_O 302.20 7.063 485.89 -15.51 0.0000 608.61 6.067 465.21 2481.9 0.4710 1.40058 0.0002539 302.13 0.077 0.0003

FS173 Byp_Nozz.Fl_O 302.20 7.063 485.89 -15.51 0.0000 608.61 5.297 447.50 2006.9 0.6543 1.40058 0.0002539 302.13 0.077 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 624.22 1.084 0.9036 2051.291 1.0260 0.9047 -1205.4 -2829.56 49.84

LPC 88.05 1.265 0.8244 2051.291 1.0843 0.8301 -552.0 6.37 2.41

HPC 51.12 5.815 0.8137 8864.996 1.7933 0.8527 -3949.3 60.93 57.30

HPT 12.09 3.883 0.8738 216.055 1.3452 0.8524 3949.3 

LPT 51.21 2.141 0.8223 58.562 1.1813 0.8061 1757.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 725.28 1.082 0.9055 2031.732 0.0426 0.8607 1.0235 0.9980 0.9905

LPC 53.69 1.313 0.7609 0.542 0.0000 1.6397 0.8445 1.0834 0.0003

HPC 46.49 5.588 0.8222 8628.661 11.0393 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.803 0.8738 1.298 3.8034 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.858 0.8284 0.659 1.8583 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–11
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.96 5871.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0566 722.81 24.45 12.051

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3359 722.81 24.45 5.628

TEGV 0.0000 0.2068 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.28 19.46 16.963

FanDuct 0.0000 0.4710 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 829.07 50.35 32.828

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.28 19.46 16.963

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 926.25 74.26 47.900

Splitter 7.0896 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.28 19.46 16.963

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8846.4 2344.7 3949.3 WB17Y Bleed> 0.3000 1.0000 1.0000 12.3054 516.49 -25.37 8.237

LP_Shaft 1957.5 4715.4 1757.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2784 926.25 74.26 46.797

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8687 926.25 74.26 26.922

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 926.25 74.26 47.900

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 926.25 74.26 47.900

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 926.25 74.26 47.900

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 484.59 -15.09 7.063

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 484.59 -15.09 7.063

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 484.59 -15.09 7.063

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 484.59 -15.09 7.063

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1676.44 0.9995 0.0230 0.23443 0.01111 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.063 0.9801 1.0000 0.9800 613.40 0.298 433.1 389.6

Byp_Nozz 1.333 0.9800 1.0000 0.9800 2006.86 0.654 665.2 6248.5

NASA/TM—2013-218094 K–12
************************************************************************************************************************************ 

Date:05/10/13 Time:11:05:11 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 35/ 63/ 2/32 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 486.38 Stator 1 exit: 489.37 Stator 2 inlet: 492.19 Stator 2 exit: 492.99 

 Stator 3 inlet: 496.39 Stator 3 exit: 496.76 Stator 4 inlet: 500.06 Stator 4 exit: 500.13 

 Stator 5 inlet: 502.04 Stator 5 exit: 501.92 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.86 

Fan Bypass Relative Humidity 4.90 

LPC Inlet Relative Humidity 5.02 

LPC Exit Relative Humidity 2.57 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 518.26 Fan/LPC Inlet Flow Velocity 203.53 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.74 

Ambient Static Temperature 465.18 Fan/LPC Inlet Static Temperature 484.11 

Additional Water at LPC Exit 0.0034795 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 18.00 368.47 853.8 1.1023 941.09 6.2711 518.26 6.475 0.890 10.000 1710.7 1612.2 1144.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 368.47 7.943 487.56 -15.16 0.0000 660.94 6.740 465.18 2618.3 0.4900 1.40057 0.0002627 368.37 0.097 0.0003

FS1 Inlet.Fl_O 368.47 7.943 487.56 -15.16 0.0000 660.94 7.522 480.01 4168.2 0.2802 1.40057 0.0002627 368.37 0.097 0.0003

FS12 Splitter.Fl_02 317.79 7.939 487.56 -15.16 0.0000 570.33 7.501 479.70 3531.8 0.2859 1.40057 0.0002627 317.71 0.083 0.0003

FS2 Splitter.Fl_01 50.68 7.939 487.56 -15.16 0.0000 90.94 7.745 484.11 830.5 0.1886 1.40057 0.0002627 50.66 0.013 0.0003

FS14 Fan.Fl_O 317.79 8.519 498.52 -12.53 0.0000 537.45 7.717 484.62 2606.7 0.3784 1.40045 0.0002627 317.71 0.083 0.0003

FS23 LPC.Fl_O 50.68 9.114 515.69 -8.41 0.0000 81.48 8.335 502.69 412.6 0.3595 1.40024 0.0002627 50.66 0.013 0.0003

FS24 VaporIN.Fl_O 50.85 9.114 520.54 -27.25 0.0000 82.15 8.319 507.15 412.6 0.3635 1.39970 0.0037423 50.66 0.190 0.0037

FS25 Bleed2.Fl_O 30.51 9.114 520.54 -27.25 0.0000 49.29 8.846 516.13 412.6 0.2069 1.39970 0.0037423 30.40 0.114 0.0037

FS3 HPC.Fl_O 29.03 51.433 926.42 71.49 0.0000 11.09 45.607 895.95 49.7 0.4200 1.38453 0.0037423 28.92 0.108 0.0037

FS36 Bleed3.Fl_O 22.50 51.433 926.42 71.49 0.0000 8.59 48.075 909.19 49.3 0.3137 1.38453 0.0037423 22.42 0.084 0.0037

FS4 Burner.Fl_O 22.76 50.248 1710.66 58.59 0.0117 12.09 47.438 1686.33 74.6 0.2950 1.33086 0.0037423 22.42 0.084 0.0178

FS45 HPT.Fl_O 30.42 13.583 1149.03 -36.64 0.0087 48.98 12.579 1125.65 265.4 0.3371 1.36468 0.0037423 30.04 0.112 0.0143

FS49 LPT.Fl_O 30.77 7.050 994.22 -74.21 0.0086 88.81 6.896 988.27 860.2 0.1793 1.37471 0.0037423 30.40 0.114 0.0142

FS5 TEGV.Fl_O 30.77 7.050 994.29 -74.21 0.0086 88.82 6.896 988.34 860.2 0.1793 1.37470 0.0037423 30.40 0.114 0.0142

FS8 Core_Nozz.Fl_O 30.77 7.050 994.36 -74.21 0.0086 88.82 6.740 982.25 613.4 0.2564 1.37470 0.0037423 30.40 0.114 0.0142

FS17 FanDuctLkg.Fl_O 317.79 8.519 498.52 -12.53 0.0000 537.45 7.717 484.62 2606.7 0.3784 1.40045 0.0002627 317.71 0.083 0.0003

FS171 Bleed15.Fl_O 338.13 8.519 499.85 -13.42 0.0000 572.61 7.480 481.60 2481.9 0.4350 1.40040 0.0004714 337.97 0.159 0.0005

FS172 FanDuct.Fl_O 338.13 8.519 499.85 -13.42 0.0000 572.61 7.480 481.60 2481.9 0.4350 1.40040 0.0004714 337.97 0.159 0.0005

FS173 Byp_Nozz.Fl_O 338.13 8.519 499.85 -13.42 0.0000 572.61 6.740 467.46 2006.9 0.5881 1.40040 0.0004714 337.97 0.159 0.0005

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 570.33 1.073 0.9058 1856.126 1.0225 0.9067 -1181.7 -1892.99 46.38

LPC 90.94 1.148 0.6971 1856.126 1.0577 0.7030 -483.8 6.94 2.22

HPC 49.29 5.643 0.8099 8805.853 1.7797 0.8490 -4159.2 60.74 56.91

HPT 12.09 3.699 0.8761 213.291 1.3305 0.8559 4159.2 

LPT 48.98 1.927 0.8155 53.090 1.1524 0.8012 1665.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 662.66 1.071 0.9076 1838.428 0.0439 0.8607 1.0235 0.9980 0.9905

LPC 47.26 1.249 0.7560 0.490 0.0000 1.9242 0.5939 0.9220 0.0003

HPC 44.83 5.425 0.8182 8571.094 11.0764 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.625 0.8761 1.282 3.6246 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.697 0.8216 0.597 1.6970 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–13
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2618.26 5935.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.1228 724.91 22.12 13.583

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3570 724.91 22.12 7.050

TEGV 0.0000 0.1793 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.57 17.18 18.424

FanDuct 0.0000 0.4350 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 830.16 47.79 35.351

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.57 17.18 18.424

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 926.42 71.49 51.433

Splitter 6.2711 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.57 17.18 18.424

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8821.7 2476.2 4159.2 WB17Y Bleed> 0.4000 1.0000 1.0000 20.3407 520.54 -27.25 9.114

LP_Shaft 1799.6 4860.9 1665.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4837 926.42 71.49 50.248

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 3.0484 926.42 71.49 29.276

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 926.42 71.49 51.433

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 926.42 71.49 51.433

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 926.42 71.49 51.433

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 498.52 -12.53 8.519

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 498.52 -12.53 8.519

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 498.52 -12.53 8.519

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 498.52 -12.53 8.519

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1710.60 0.9995 0.0230 0.26141 0.01166 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.046 0.9801 1.0000 0.9800 613.40 0.256 383.1 366.4

Byp_Nozz 1.264 0.9800 1.0000 0.9800 2006.86 0.588 611.1 6422.6

NASA/TM—2013-218094 K–14
************************************************************************************************************************************ 

Date:05/10/13 Time:11:05:49 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 42/ 70/ 2/39 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 500.38 Stator 1 exit: 502.78 Stator 2 inlet: 505.16 Stator 2 exit: 505.91 

 Stator 3 inlet: 508.66 Stator 3 exit: 509.07 Stator 4 inlet: 511.70 Stator 4 exit: 511.88 

 Stator 5 inlet: 513.53 Stator 5 exit: 513.57 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.54 

Fan Bypass Relative Humidity 5.94 

LPC Inlet Relative Humidity 5.71 

LPC Exit Relative Humidity 3.35 

HPC Relative Humidity 0.12 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 479.99 Fan/LPC Inlet Flow Velocity 172.62 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.18 

Ambient Static Temperature 481.63 Fan/LPC Inlet Static Temperature 498.33 

Additional Water at LPC Exit 0.0046347 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 18.00 387.25 669.1 1.3373 894.73 6.8286 479.99 5.312 0.902 10.000 1665.1 1568.8 1136.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.25 9.342 500.81 -13.05 0.0000 598.60 8.149 481.63 2544.6 0.4460 1.40040 0.0004484 387.07 0.174 0.0004

FS1 Inlet.Fl_O 387.25 9.342 500.81 -13.05 0.0000 598.60 8.940 494.55 4168.2 0.2515 1.40040 0.0004484 387.07 0.174 0.0004

FS12 Splitter.Fl_02 337.78 9.337 500.81 -13.05 0.0000 522.40 8.909 494.14 3531.8 0.2597 1.40040 0.0004484 337.63 0.151 0.0004

FS2 Splitter.Fl_01 49.47 9.337 500.81 -13.05 0.0000 76.50 9.177 498.33 830.5 0.1577 1.40040 0.0004484 49.44 0.022 0.0004

FS14 Fan.Fl_O 337.78 9.823 508.93 -11.10 0.0000 500.60 9.033 496.89 2606.7 0.3480 1.40030 0.0004484 337.63 0.151 0.0004

FS23 LPC.Fl_O 49.47 10.469 523.60 -7.58 0.0000 69.77 9.831 514.28 412.6 0.3009 1.40011 0.0004484 49.44 0.022 0.0004

FS24 VaporIN.Fl_O 49.69 10.469 529.97 -32.65 0.0000 70.52 9.815 520.29 412.6 0.3051 1.39938 0.0050830 49.44 0.251 0.0051

FS25 Bleed2.Fl_O 29.82 10.469 529.97 -32.65 0.0000 42.31 10.244 526.69 412.6 0.1765 1.39938 0.0050830 29.67 0.151 0.0051

FS3 HPC.Fl_O 28.37 49.622 898.40 57.00 0.0000 11.06 44.030 868.94 49.7 0.4186 1.38593 0.0050830 28.23 0.143 0.0051

FS36 Bleed3.Fl_O 21.99 49.622 898.40 57.00 0.0000 8.57 46.398 881.74 49.3 0.3127 1.38593 0.0050830 21.88 0.111 0.0051

FS4 Burner.Fl_O 22.24 48.479 1665.12 44.60 0.0114 12.08 45.772 1641.35 74.6 0.2945 1.33304 0.0050830 21.88 0.111 0.0188

FS45 HPT.Fl_O 29.72 14.309 1141.07 -41.71 0.0085 45.27 13.417 1121.56 265.4 0.3083 1.36515 0.0050830 29.32 0.149 0.0153

FS49 LPT.Fl_O 30.07 8.399 1015.41 -71.97 0.0084 73.61 8.274 1011.29 860.2 0.1478 1.37332 0.0050830 29.67 0.151 0.0152

FS5 TEGV.Fl_O 30.07 8.399 1015.48 -71.97 0.0084 73.61 8.274 1011.36 860.2 0.1478 1.37331 0.0050830 29.67 0.151 0.0152

FS8 Core_Nozz.Fl_O 30.07 8.399 1015.55 -71.97 0.0084 73.61 8.149 1007.26 613.4 0.2100 1.37331 0.0050830 29.67 0.151 0.0152

FS17 FanDuctLkg.Fl_O 337.78 9.823 508.93 -11.10 0.0000 500.60 9.033 496.89 2606.7 0.3480 1.40030 0.0004484 337.63 0.151 0.0004

FS171 Bleed15.Fl_O 357.66 9.823 510.11 -12.30 0.0000 530.67 8.818 494.61 2481.9 0.3956 1.40025 0.0007048 357.41 0.252 0.0007

FS172 FanDuct.Fl_O 357.66 9.823 510.11 -12.30 0.0000 530.67 8.818 494.61 2481.9 0.3956 1.40025 0.0007048 357.41 0.252 0.0007

FS173 Byp_Nozz.Fl_O 357.66 9.823 510.11 -12.30 0.0000 530.67 8.149 483.58 2006.9 0.5234 1.40025 0.0007048 357.41 0.252 0.0007

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 522.40 1.052 0.8996 1618.857 1.0162 0.9004 -931.1 -1526.51 44.70

LPC 76.50 1.121 0.7304 1618.857 1.0455 0.7348 -382.6 8.21 1.95

HPC 42.31 4.740 0.7956 8544.066 1.6952 0.8340 -3690.6 68.43 63.22

HPT 12.08 3.388 0.8678 211.651 1.3031 0.8480 3690.5 

LPT 45.27 1.704 0.8023 47.092 1.1202 0.7901 1313.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 606.98 1.051 0.9015 1603.421 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 39.96 1.187 0.7483 0.428 0.0000 1.9142 0.6495 0.9761 0.0003

HPC 38.48 4.564 0.8038 8316.287 10.7481 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.322 0.8678 1.272 3.3218 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.529 0.8083 0.530 1.5293 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–15
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2544.56 5777.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0973 715.33 12.17 14.309

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3489 715.33 12.17 8.399

TEGV 0.0000 0.1478 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.87 7.69 19.083

FanDuct 0.0000 0.3956 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 810.90 35.48 34.744

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.87 7.69 19.083

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 898.40 57.00 49.622

Splitter 6.8286 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.87 7.69 19.083

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8636.6 2244.3 3690.5 WB17Y Bleed> 0.4000 1.0000 1.0000 19.8780 529.97 -32.65 10.469

LP_Shaft 1590.7 4337.7 1313.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4045 898.40 57.00 48.479

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9790 898.40 57.00 28.934

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 898.40 57.00 49.622

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 898.40 57.00 49.622

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 898.40 57.00 49.622

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 508.93 -11.10 9.823

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 508.93 -11.10 9.823

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 508.93 -11.10 9.823

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 508.93 -11.10 9.823

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1665.06 0.9995 0.0230 0.24854 0.01136 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.031 0.9801 1.0000 0.9800 613.40 0.210 317.7 296.9

Byp_Nozz 1.205 0.9800 1.0000 0.9800 2006.86 0.523 553.2 6149.3

NASA/TM—2013-218094 K–16
5μm, 4 g/m3

, ISA +18R

************************************************************************************************************************************ 

Date:07/05/13 Time:11:13:13 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 40/ 2/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 463.54 Stator 1 exit: 471.07 Stator 2 inlet: 480.53 Stator 2 exit: 485.41 

 Stator 3 inlet: 495.10 Stator 3 exit: 499.53 Stator 4 inlet: 508.56 Stator 4 exit: 512.31 

 Stator 5 inlet: 519.67 Stator 5 exit: 522.89 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.76 

Fan Bypass Relative Humidity 1.22 

LPC Inlet Relative Humidity 1.13 

LPC Exit Relative Humidity 0.09 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 185.27 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 454.88 

Additional Water at LPC Exit 0.0072598 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 257.50 640.6 1.0925 699.88 8.7350 772.64 9.501 0.736 10.000 1718.6 1625.8 1131.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.50 4.267 457.74 -20.96 0.0000 833.18 2.854 407.97 2541.8 0.7800 1.40084 0.0000295 257.50 0.008 0.0000

FS1 Inlet.Fl_O 257.50 4.267 457.74 -20.96 0.0000 833.18 3.892 445.86 4168.2 0.3646 1.40084 0.0000295 257.50 0.008 0.0000

FS12 Splitter.Fl_02 231.05 4.265 457.74 -20.96 0.0000 747.97 3.838 444.14 3531.8 0.3908 1.40084 0.0000295 231.05 0.007 0.0000

FS2 Splitter.Fl_01 26.45 4.265 457.74 -20.96 0.0000 85.63 4.172 454.88 830.5 0.1771 1.40084 0.0000295 26.45 0.001 0.0000

FS14 Fan.Fl_O 231.05 4.824 475.86 -16.61 0.0000 674.27 4.047 452.56 2606.7 0.5069 1.40070 0.0000295 231.05 0.007 0.0000

FS23 LPC.Fl_O 26.45 6.676 532.79 -2.96 0.0000 59.02 6.391 526.19 412.6 0.2504 1.40003 0.0000295 26.45 0.001 0.0000

FS24 VaporIN.Fl_O 26.64 6.676 542.60 -42.18 0.0000 59.99 6.379 535.62 412.6 0.2556 1.39889 0.0072892 26.45 0.193 0.0072

FS25 Bleed2.Fl_O 23.98 6.676 542.60 -42.18 0.0000 53.99 6.438 537.02 412.6 0.2282 1.39889 0.0072892 23.81 0.174 0.0072

FS3 HPC.Fl_O 22.82 40.539 981.98 65.37 0.0000 11.38 35.643 947.67 49.7 0.4353 1.38069 0.0072892 22.65 0.165 0.0072

FS36 Bleed3.Fl_O 17.68 40.539 981.98 65.37 0.0000 8.82 37.730 962.71 49.3 0.3240 1.38069 0.0072892 17.55 0.128 0.0072

FS4 Burner.Fl_O 17.88 39.605 1718.62 53.22 0.0111 12.07 37.392 1694.21 74.6 0.2950 1.33036 0.0072892 17.55 0.128 0.0206

FS45 HPT.Fl_O 23.89 9.502 1135.41 -51.03 0.0083 54.67 8.602 1105.53 265.4 0.3840 1.36535 0.0072892 23.53 0.171 0.0172

FS49 LPT.Fl_O 24.17 3.262 889.88 -111.50 0.0082 142.65 3.071 875.14 860.2 0.2972 1.38078 0.0072892 23.81 0.174 0.0171

FS5 TEGV.Fl_O 24.17 3.262 889.95 -111.50 0.0082 142.65 3.071 875.21 860.2 0.2972 1.38078 0.0072892 23.81 0.174 0.0171

FS8 Core_Nozz.Fl_O 24.17 3.262 890.02 -111.50 0.0082 142.66 2.854 857.76 613.4 0.4438 1.38077 0.0072892 23.81 0.174 0.0171

FS17 FanDuctLkg.Fl_O 231.05 4.824 475.86 -16.61 0.0000 674.27 4.047 452.56 2606.7 0.5069 1.40070 0.0000295 231.05 0.007 0.0000

FS171 Bleed15.Fl_O 233.72 4.824 476.63 -16.90 0.0000 682.59 3.913 448.94 2481.9 0.5547 1.40069 0.0001116 233.69 0.026 0.0001

FS172 FanDuct.Fl_O 233.72 4.824 476.63 -16.90 0.0000 682.59 3.913 448.94 2481.9 0.5547 1.40069 0.0001116 233.69 0.026 0.0001

FS173 Byp_Nozz.Fl_O 233.72 4.824 476.63 -16.90 0.0000 682.59 2.854 410.16 2006.9 0.8991 1.40069 0.0001116 233.69 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 747.97 1.131 0.9058 2576.390 1.0396 0.9075 -1419.8 1555.29 54.72

LPC 85.63 1.565 0.8338 2576.390 1.1640 0.8440 -673.4 7.00 3.79

HPC 53.99 6.073 0.8182 8957.455 1.8098 0.8568 -3560.4 61.54 58.19

HPT 12.07 4.168 0.8753 220.999 1.3647 0.8530 3560.4 

LPT 54.67 2.913 0.8533 71.829 1.2741 0.8335 2093.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 869.07 1.128 0.9077 2551.824 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 74.26 1.526 0.7803 0.680 0.0000 1.1531 1.0755 1.0686 0.0003

HPC 49.11 5.834 0.8266 8718.656 10.9660 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.080 0.8753 1.328 4.0804 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.439 0.8596 0.808 2.4387 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–17
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2541.77 6183.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8824 764.17 11.60 9.502

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2806 764.17 11.60 3.262

TEGV 0.0000 0.2972 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 742.15 6.22 14.126

FanDuct 0.0000 0.5547 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 878.02 39.56 27.671

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 742.15 6.22 14.126

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 981.98 65.37 40.539

Splitter 8.7350 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 742.15 6.22 14.126

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9161.8 2041.1 3560.4 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6643 542.60 -42.18 6.676

LP_Shaft 2420.3 4542.2 2093.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7379 981.98 65.37 39.605

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3957 981.98 65.37 22.386

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 981.98 65.37 40.539

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 981.98 65.37 40.539

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 981.98 65.37 40.539

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.86 -16.61 4.824

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.86 -16.61 4.824

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.86 -16.61 4.824

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.86 -16.61 4.824

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1718.56 0.9995 0.0230 0.19441 0.01107 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.444 621.9 467.3

Byp_Nozz 1.690 0.9800 1.0000 0.9800 2006.86 0.899 875.1 6357.1

NASA/TM—2013-218094 K–18
************************************************************************************************************************************ 

Date:07/05/13 Time:11:13:38 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 457.01 Stator 1 exit: 464.06 Stator 2 inlet: 472.90 Stator 2 exit: 477.45 

 Stator 3 inlet: 486.52 Stator 3 exit: 490.64 Stator 4 inlet: 499.08 Stator 4 exit: 502.57 

 Stator 5 inlet: 509.49 Stator 5 exit: 512.50 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.24 

Fan Bypass Relative Humidity 1.59 

LPC Inlet Relative Humidity 1.44 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 723.11 Fan/LPC Inlet Flow Velocity 179.03 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 448.89 

Additional Water at LPC Exit 0.0063349 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 18.00 250.56 626.4 1.0643 666.61 8.8127 723.11 9.223 0.763 10.000 1690.0 1597.9 1113.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 250.56 4.201 451.57 -22.43 0.0000 817.76 2.947 407.97 2559.3 0.7300 1.40089 0.0000285 250.55 0.007 0.0000

FS1 Inlet.Fl_O 250.56 4.201 451.57 -22.43 0.0000 817.76 3.847 440.34 4168.2 0.3567 1.40089 0.0000285 250.55 0.007 0.0000

FS12 Splitter.Fl_02 225.02 4.199 451.57 -22.43 0.0000 734.79 3.796 438.70 3531.8 0.3825 1.40089 0.0000285 225.02 0.006 0.0000

FS2 Splitter.Fl_01 25.53 4.199 451.57 -22.43 0.0000 83.38 4.113 448.89 830.5 0.1723 1.40089 0.0000285 25.53 0.001 0.0000

FS14 Fan.Fl_O 225.02 4.717 468.44 -18.39 0.0000 666.28 3.980 446.21 2606.7 0.4985 1.40077 0.0000285 225.02 0.006 0.0000

FS23 LPC.Fl_O 25.53 6.434 521.81 -5.59 0.0000 58.50 6.164 515.47 412.6 0.2480 1.40019 0.0000285 25.53 0.001 0.0000

FS24 VaporIN.Fl_O 25.70 6.434 530.51 -39.83 0.0000 59.36 6.155 523.84 412.6 0.2526 1.39920 0.0063634 25.53 0.162 0.0063

FS25 Bleed2.Fl_O 23.13 6.434 530.51 -39.83 0.0000 53.42 6.210 525.18 412.6 0.2256 1.39920 0.0063634 22.98 0.146 0.0063

FS3 HPC.Fl_O 22.00 38.751 958.82 64.78 0.0000 11.35 34.108 925.51 49.7 0.4333 1.38222 0.0063634 21.87 0.139 0.0063

FS36 Bleed3.Fl_O 17.05 38.751 958.82 64.78 0.0000 8.79 36.085 940.09 49.3 0.3226 1.38222 0.0063634 16.95 0.108 0.0063

FS4 Burner.Fl_O 17.24 37.858 1690.05 52.79 0.0109 12.08 35.742 1665.94 74.6 0.2949 1.33194 0.0063634 16.95 0.108 0.0195

FS45 HPT.Fl_O 23.04 9.196 1117.65 -48.58 0.0082 54.05 8.349 1088.97 265.4 0.3784 1.36670 0.0063634 22.71 0.145 0.0162

FS49 LPT.Fl_O 23.31 3.312 886.36 -105.33 0.0081 135.21 3.139 873.29 860.2 0.2800 1.38118 0.0063634 22.98 0.146 0.0161

FS5 TEGV.Fl_O 23.31 3.312 886.43 -105.33 0.0081 135.22 3.139 873.36 860.2 0.2800 1.38117 0.0063634 22.98 0.146 0.0161

FS8 Core_Nozz.Fl_O 23.31 3.312 886.50 -105.33 0.0081 135.22 2.947 858.32 613.4 0.4145 1.38117 0.0063634 22.98 0.146 0.0161

FS17 FanDuctLkg.Fl_O 225.02 4.717 468.44 -18.39 0.0000 666.28 3.980 446.21 2606.7 0.4985 1.40077 0.0000285 225.02 0.006 0.0000

FS171 Bleed15.Fl_O 227.59 4.717 469.14 -18.63 0.0000 674.39 3.855 442.81 2481.9 0.5446 1.40075 0.0000996 227.57 0.023 0.0001

FS172 FanDuct.Fl_O 227.59 4.717 469.14 -18.63 0.0000 674.39 3.855 442.81 2481.9 0.5446 1.40075 0.0000996 227.57 0.023 0.0001

FS173 Byp_Nozz.Fl_O 227.59 4.717 469.14 -18.63 0.0000 674.39 2.947 410.05 2006.9 0.8478 1.40075 0.0000996 227.57 0.023 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 734.79 1.123 0.9050 2511.599 1.0374 0.9066 -1287.0 2101.01 54.60

LPC 83.38 1.532 0.8342 2511.599 1.1556 0.8439 -608.3 6.80 3.37

HPC 53.42 6.023 0.8175 8939.174 1.8073 0.8562 -3339.8 61.38 57.98

HPT 12.08 4.117 0.8739 219.913 1.3616 0.8516 3339.8 

LPT 54.05 2.777 0.8476 70.099 1.2590 0.8280 1895.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 853.75 1.120 0.9069 2487.652 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 71.46 1.497 0.7772 0.663 0.0000 1.1669 1.0712 1.0733 0.0003

HPC 48.59 5.786 0.8259 8700.862 10.9822 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.030 0.8739 1.322 4.0304 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.336 0.8539 0.789 2.3362 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–19
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2559.33 5631.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8510 746.36 12.48 9.196

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2706 746.36 12.48 3.312

TEGV 0.0000 0.2800 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 724.90 7.25 13.543

FanDuct 0.0000 0.5446 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 857.39 39.68 26.470

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 724.90 7.25 13.543

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 958.82 64.78 38.751

Splitter 8.8127 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 724.90 7.25 13.543

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9040.7 1940.3 3339.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5695 530.51 -39.83 6.434

LP_Shaft 2343.5 4247.6 1895.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6405 958.82 64.78 37.858

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3105 958.82 64.78 21.463

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 958.82 64.78 38.751

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 958.82 64.78 38.751

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 958.82 64.78 38.751

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 468.44 -18.39 4.717

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 468.44 -18.39 4.717

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 468.44 -18.39 4.717

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 468.44 -18.39 4.717

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1689.98 0.9995 0.0230 0.18517 0.01093 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.415 580.9 420.9

Byp_Nozz 1.601 0.9800 1.0000 0.9800 2006.86 0.848 825.1 5836.7

NASA/TM—2013-218094 K–20
************************************************************************************************************************************ 

Date:07/05/13 Time:11:14:03 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 454.98 Stator 1 exit: 461.84 Stator 2 inlet: 470.44 Stator 2 exit: 474.87 

 Stator 3 inlet: 483.70 Stator 3 exit: 487.70 Stator 4 inlet: 495.92 Stator 4 exit: 499.31 

 Stator 5 inlet: 506.04 Stator 5 exit: 508.97 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.40 

Fan Bypass Relative Humidity 1.73 

LPC Inlet Relative Humidity 1.56 

LPC Exit Relative Humidity 0.14 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 707.26 Fan/LPC Inlet Flow Velocity 176.74 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 447.07 

Additional Water at LPC Exit 0.0056534 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 18.00 257.30 639.1 1.0605 677.76 8.8384 707.26 9.105 0.772 10.000 1677.8 1586.0 1105.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.30 4.339 449.68 -22.87 0.0000 811.37 3.088 407.97 2563.9 0.7140 1.40090 0.0000272 257.29 0.007 0.0000

FS1 Inlet.Fl_O 257.30 4.339 449.68 -22.87 0.0000 811.37 3.980 438.69 4168.2 0.3534 1.40090 0.0000272 257.29 0.007 0.0000

FS12 Splitter.Fl_02 231.15 4.337 449.68 -22.87 0.0000 729.27 3.928 437.09 3531.8 0.3790 1.40090 0.0000272 231.14 0.006 0.0000

FS2 Splitter.Fl_01 26.15 4.337 449.68 -22.87 0.0000 82.51 4.250 447.07 830.5 0.1705 1.40090 0.0000272 26.15 0.001 0.0000

FS14 Fan.Fl_O 231.15 4.858 466.07 -18.95 0.0000 662.85 4.109 444.26 2606.7 0.4949 1.40079 0.0000272 231.14 0.006 0.0000

FS23 LPC.Fl_O 26.15 6.587 518.04 -6.49 0.0000 58.32 6.312 511.78 412.6 0.2472 1.40024 0.0000272 26.15 0.001 0.0000

FS24 VaporIN.Fl_O 26.30 6.587 525.86 -37.06 0.0000 59.09 6.304 519.31 412.6 0.2512 1.39936 0.0056806 26.15 0.149 0.0056

FS25 Bleed2.Fl_O 23.67 6.587 525.86 -37.06 0.0000 53.18 6.360 520.62 412.6 0.2244 1.39936 0.0056806 23.54 0.134 0.0056

FS3 HPC.Fl_O 22.52 39.511 949.74 66.36 0.0000 11.34 34.790 916.80 49.7 0.4325 1.38287 0.0056806 22.40 0.127 0.0056

FS36 Bleed3.Fl_O 17.45 39.511 949.74 66.36 0.0000 8.79 36.800 931.21 49.3 0.3221 1.38287 0.0056806 17.36 0.099 0.0056

FS4 Burner.Fl_O 17.64 38.601 1677.81 54.42 0.0108 12.08 36.444 1653.86 74.6 0.2947 1.33269 0.0056806 17.36 0.099 0.0187

FS45 HPT.Fl_O 23.58 9.416 1109.91 -45.77 0.0081 53.84 8.556 1081.67 265.4 0.3764 1.36735 0.0056806 23.26 0.132 0.0155

FS49 LPT.Fl_O 23.86 3.452 884.08 -101.08 0.0080 132.60 3.279 871.58 860.2 0.2740 1.38144 0.0056806 23.54 0.134 0.0153

FS5 TEGV.Fl_O 23.86 3.452 884.15 -101.08 0.0080 132.60 3.279 871.65 860.2 0.2740 1.38144 0.0056806 23.54 0.134 0.0154

FS8 Core_Nozz.Fl_O 23.86 3.452 884.22 -101.08 0.0080 132.61 3.088 857.40 613.4 0.4045 1.38143 0.0056806 23.54 0.134 0.0154

FS17 FanDuctLkg.Fl_O 231.15 4.858 466.07 -18.95 0.0000 662.85 4.109 444.26 2606.7 0.4949 1.40079 0.0000272 231.14 0.006 0.0000

FS171 Bleed15.Fl_O 233.78 4.858 466.75 -19.15 0.0000 670.88 3.982 440.94 2481.9 0.5404 1.40077 0.0000905 233.76 0.021 0.0001

FS172 FanDuct.Fl_O 233.78 4.858 466.75 -19.15 0.0000 670.88 3.982 440.94 2481.9 0.5404 1.40077 0.0000905 233.76 0.021 0.0001

FS173 Byp_Nozz.Fl_O 233.78 4.858 466.75 -19.15 0.0000 670.88 3.088 410.00 2006.9 0.8309 1.40077 0.0000905 233.76 0.021 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 729.27 1.120 0.9046 2484.788 1.0365 0.9062 -1284.6 2460.98 54.53

LPC 82.51 1.519 0.8349 2484.788 1.1520 0.8444 -606.4 6.71 3.29

HPC 53.18 5.999 0.8171 8931.188 1.8061 0.8558 -3379.4 61.40 57.97

HPT 12.08 4.100 0.8733 219.546 1.3607 0.8508 3379.4 

LPT 53.84 2.727 0.8453 69.446 1.2534 0.8258 1891.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 847.34 1.117 0.9065 2461.096 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.29 1.485 0.7760 0.656 0.0000 1.1738 1.0700 1.0760 0.0003

HPC 48.36 5.763 0.8255 8693.089 10.9845 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.014 0.8732 1.319 4.0136 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.299 0.8515 0.781 2.2992 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–21
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2563.86 5656.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8711 739.43 14.65 9.416

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2769 739.43 14.65 3.452

TEGV 0.0000 0.2740 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 718.18 9.48 13.830

FanDuct 0.0000 0.5404 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 849.31 41.54 27.000

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 718.18 9.48 13.830

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 949.74 66.36 39.511

Splitter 8.8384 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 718.18 9.48 13.830

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8992.9 1973.7 3379.4 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6301 525.86 -37.06 6.587

LP_Shaft 2313.6 4292.6 1891.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7027 949.74 66.36 38.601

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3649 949.74 66.36 21.907

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.74 66.36 39.511

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.74 66.36 39.511

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.74 66.36 39.511

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 466.07 -18.95 4.858

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 466.07 -18.95 4.858

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 466.07 -18.95 4.858

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 466.07 -18.95 4.858

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1677.75 0.9995 0.0230 0.18827 0.01085 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.404 566.4 420.0

Byp_Nozz 1.573 0.9800 1.0000 0.9800 2006.86 0.831 808.6 5875.1

NASA/TM—2013-218094 K–22
************************************************************************************************************************************ 

Date:07/05/13 Time:11:14:19 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.59 Stator 1 exit: 463.04 Stator 2 inlet: 471.10 Stator 2 exit: 475.24 

 Stator 3 inlet: 483.51 Stator 3 exit: 487.22 Stator 4 inlet: 494.93 Stator 4 exit: 498.06 

 Stator 5 inlet: 504.37 Stator 5 exit: 507.07 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.01 

Fan Bypass Relative Humidity 2.24 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.21 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 667.90 Fan/LPC Inlet Flow Velocity 171.39 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 414.42 Fan/LPC Inlet Static Temperature 449.16 

Additional Water at LPC Exit 0.0050695 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 18.00 278.85 693.3 1.0485 726.93 8.9096 667.90 8.771 0.795 10.000 1669.0 1577.3 1101.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 278.85 4.831 451.61 -22.45 0.0000 791.52 3.578 414.42 2579.9 0.6690 1.40088 0.0000348 278.84 0.010 0.0000

FS1 Inlet.Fl_O 278.85 4.831 451.61 -22.45 0.0000 791.52 4.452 441.18 4168.2 0.3434 1.40088 0.0000348 278.84 0.010 0.0000

FS12 Splitter.Fl_02 250.71 4.829 451.61 -22.45 0.0000 712.00 4.396 439.65 3531.8 0.3683 1.40088 0.0000348 250.70 0.009 0.0000

FS2 Splitter.Fl_01 28.14 4.829 451.61 -22.45 0.0000 79.91 4.738 449.16 830.5 0.1649 1.40088 0.0000348 28.14 0.001 0.0000

FS14 Fan.Fl_O 250.71 5.369 467.01 -18.76 0.0000 651.15 4.577 446.16 2606.7 0.4829 1.40078 0.0000348 250.70 0.009 0.0000

FS23 LPC.Fl_O 28.14 7.150 515.75 -7.08 0.0000 57.68 6.859 509.66 412.6 0.2442 1.40027 0.0000348 28.14 0.001 0.0000

FS24 VaporIN.Fl_O 28.28 7.150 522.79 -34.51 0.0000 58.36 6.851 516.45 412.6 0.2479 1.39948 0.0051043 28.14 0.144 0.0051

FS25 Bleed2.Fl_O 25.45 7.150 522.79 -34.51 0.0000 52.53 6.910 517.71 412.6 0.2214 1.39948 0.0051043 25.32 0.129 0.0051

FS3 HPC.Fl_O 24.22 42.371 941.47 67.54 0.0000 11.32 37.330 908.93 49.7 0.4314 1.38344 0.0051043 24.10 0.123 0.0051

FS36 Bleed3.Fl_O 18.77 42.371 941.47 67.54 0.0000 8.77 39.475 923.16 49.3 0.3214 1.38344 0.0051043 18.67 0.095 0.0051

FS4 Burner.Fl_O 18.97 41.395 1669.03 55.63 0.0108 12.08 39.082 1645.17 74.6 0.2947 1.33322 0.0051043 18.67 0.095 0.0181

FS45 HPT.Fl_O 25.36 10.206 1105.90 -43.21 0.0081 53.32 9.295 1078.39 265.4 0.3719 1.36771 0.0051043 25.03 0.128 0.0149

FS49 LPT.Fl_O 25.66 3.944 892.20 -95.45 0.0080 125.38 3.768 881.04 860.2 0.2578 1.38107 0.0051043 25.32 0.129 0.0148

FS5 TEGV.Fl_O 25.66 3.944 892.27 -95.45 0.0080 125.39 3.768 881.11 860.2 0.2578 1.38107 0.0051043 25.32 0.129 0.0148

FS8 Core_Nozz.Fl_O 25.66 3.944 892.34 -95.45 0.0080 125.39 3.578 868.66 613.4 0.3779 1.38106 0.0051043 25.32 0.129 0.0148

FS17 FanDuctLkg.Fl_O 250.71 5.369 467.01 -18.76 0.0000 651.15 4.577 446.16 2606.7 0.4829 1.40078 0.0000348 250.70 0.009 0.0000

FS171 Bleed15.Fl_O 253.54 5.369 467.64 -18.94 0.0000 658.93 4.446 443.05 2481.9 0.5262 1.40077 0.0000911 253.52 0.023 0.0001

FS172 FanDuct.Fl_O 253.54 5.369 467.64 -18.94 0.0000 658.93 4.446 443.05 2481.9 0.5262 1.40077 0.0000911 253.52 0.023 0.0001

FS173 Byp_Nozz.Fl_O 253.54 5.369 467.64 -18.94 0.0000 658.93 3.578 416.36 2006.9 0.7838 1.40077 0.0000911 253.52 0.023 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 712.00 1.112 0.9038 2406.933 1.0341 0.9052 -1309.4 4933.57 54.09

LPC 79.91 1.481 0.8366 2406.933 1.1420 0.8454 -612.1 6.45 3.08

HPC 52.53 5.926 0.8159 8909.850 1.8009 0.8546 -3586.1 61.64 58.15

HPT 12.08 4.056 0.8727 218.955 1.3577 0.8503 3586.1 

LPT 53.32 2.588 0.8405 67.537 1.2373 0.8217 1921.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 827.28 1.109 0.9056 2383.983 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.92 1.450 0.7723 0.636 0.0000 1.1940 1.0684 1.0832 0.0003

HPC 47.77 5.694 0.8243 8672.320 10.9775 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.971 0.8727 1.316 3.9712 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.194 0.8467 0.760 2.1942 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–23
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2579.94 5788.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9367 733.69 16.52 10.206

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2978 733.69 16.52 3.944

TEGV 0.0000 0.2578 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.71 11.42 14.899

FanDuct 0.0000 0.5262 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 842.24 43.05 28.987

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.71 11.42 14.899

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 941.47 67.54 42.371

Splitter 8.9096 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.71 11.42 14.899

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8945.1 2105.6 3586.1 WB17Y Bleed> 0.1000 1.0000 1.0000 2.8282 522.79 -34.51 7.150

LP_Shaft 2245.9 4493.3 1921.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.9063 941.47 67.54 41.395

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5431 941.47 67.54 23.555

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.47 67.54 42.371

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.47 67.54 42.371

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.47 67.54 42.371

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 467.01 -18.76 5.369

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 467.01 -18.76 5.369

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 467.01 -18.76 5.369

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 467.01 -18.76 5.369

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1668.97 0.9995 0.0230 0.20192 0.01081 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.378 532.5 424.6

Byp_Nozz 1.501 0.9800 1.0000 0.9800 2006.86 0.784 768.7 6057.4

NASA/TM—2013-218094 K–24
************************************************************************************************************************************ 

Date:07/05/13 Time:11:14:46 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 17/ 45/ 2/14 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.23 Stator 1 exit: 470.82 Stator 2 inlet: 477.74 Stator 2 exit: 481.11 

 Stator 3 inlet: 488.30 Stator 3 exit: 491.27 Stator 4 inlet: 498.01 Stator 4 exit: 500.46 

 Stator 5 inlet: 505.89 Stator 5 exit: 507.95 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.97 

Fan Bypass Relative Humidity 3.10 

LPC Inlet Relative Humidity 2.83 

LPC Exit Relative Humidity 0.45 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 617.99 Fan/LPC Inlet Flow Velocity 173.41 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 429.58 Fan/LPC Inlet Static Temperature 458.91 

Additional Water at LPC Exit 0.0051374 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 18.00 305.45 755.2 1.0510 793.73 8.4645 617.99 8.214 0.828 10.000 1673.3 1580.9 1107.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 305.45 5.595 461.42 -20.30 0.0000 756.70 4.358 429.58 2599.2 0.6080 1.40081 0.0000681 305.43 0.021 0.0001

FS1 Inlet.Fl_O 305.45 5.595 461.42 -20.30 0.0000 756.70 5.198 451.79 4168.2 0.3260 1.40081 0.0000681 305.43 0.021 0.0001

FS12 Splitter.Fl_02 273.17 5.592 461.42 -20.30 0.0000 677.08 5.145 450.53 3531.8 0.3472 1.40081 0.0000681 273.16 0.019 0.0001

FS2 Splitter.Fl_01 32.27 5.592 461.42 -20.30 0.0000 79.99 5.487 458.91 830.5 0.1651 1.40081 0.0000681 32.27 0.002 0.0001

FS14 Fan.Fl_O 273.17 6.149 475.48 -16.93 0.0000 625.13 5.327 456.36 2606.7 0.4572 1.40070 0.0000681 273.16 0.019 0.0001

FS23 LPC.Fl_O 32.27 7.863 516.86 -7.01 0.0000 60.21 7.513 510.18 412.6 0.2559 1.40025 0.0000681 32.27 0.002 0.0001

FS24 VaporIN.Fl_O 32.44 7.863 523.98 -34.80 0.0000 60.94 7.503 517.01 412.6 0.2597 1.39945 0.0052055 32.27 0.168 0.0052

FS25 Bleed2.Fl_O 27.57 7.863 523.98 -34.80 0.0000 51.80 7.607 519.05 412.6 0.2182 1.39945 0.0052055 27.43 0.143 0.0052

FS3 HPC.Fl_O 26.24 45.960 940.22 66.66 0.0000 11.29 40.516 907.88 49.7 0.4304 1.38350 0.0052055 26.10 0.136 0.0052

FS36 Bleed3.Fl_O 20.33 45.960 940.22 66.66 0.0000 8.75 42.832 922.01 49.3 0.3206 1.38350 0.0052055 20.23 0.105 0.0052

FS4 Burner.Fl_O 20.55 44.901 1673.26 54.66 0.0109 12.08 42.392 1649.36 74.6 0.2947 1.33294 0.0052055 20.23 0.105 0.0183

FS45 HPT.Fl_O 27.47 11.224 1111.42 -43.56 0.0081 52.65 10.249 1084.58 265.4 0.3666 1.36729 0.0052055 27.11 0.141 0.0150

FS49 LPT.Fl_O 27.79 4.720 915.41 -91.41 0.0080 114.97 4.544 905.91 860.2 0.2349 1.37966 0.0052055 27.43 0.143 0.0149

FS5 TEGV.Fl_O 27.79 4.720 915.48 -91.41 0.0080 114.98 4.544 905.98 860.2 0.2349 1.37966 0.0052055 27.43 0.143 0.0149

FS8 Core_Nozz.Fl_O 27.79 4.720 915.55 -91.41 0.0080 114.98 4.358 895.69 613.4 0.3415 1.37965 0.0052055 27.43 0.143 0.0149

FS17 FanDuctLkg.Fl_O 273.17 6.149 475.48 -16.93 0.0000 625.13 5.327 456.36 2606.7 0.4572 1.40070 0.0000681 273.16 0.019 0.0001

FS171 Bleed15.Fl_O 278.04 6.149 476.33 -17.24 0.0000 636.83 5.179 453.50 2481.9 0.5012 1.40068 0.0001576 278.00 0.044 0.0002

FS172 FanDuct.Fl_O 278.04 6.149 476.33 -17.24 0.0000 636.83 5.179 453.50 2481.9 0.5012 1.40068 0.0001576 278.00 0.044 0.0002

FS173 Byp_Nozz.Fl_O 278.04 6.149 476.33 -17.24 0.0000 636.83 4.358 431.66 2006.9 0.7185 1.40068 0.0001576 278.00 0.044 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 677.08 1.099 0.9028 2261.160 1.0305 0.9041 -1302.1 -----.-- 52.63

LPC 79.99 1.406 0.8519 2261.160 1.1202 0.8589 -606.9 5.94 2.66

HPC 51.80 5.845 0.8144 8885.964 1.7944 0.8532 -3862.2 61.93 58.35

HPT 12.08 4.001 0.8728 218.341 1.3535 0.8508 3862.2 

LPT 52.65 2.378 0.8324 63.972 1.2116 0.8147 1909.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 786.70 1.097 0.9046 2239.600 0.0417 0.8607 1.0235 0.9980 0.9905

LPC 60.72 1.386 0.7658 0.597 0.0000 1.3175 1.0522 1.1125 0.0003

HPC 47.11 5.617 0.8228 8649.070 10.9695 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.917 0.8728 1.312 3.9175 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.037 0.8386 0.720 2.0365 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–25
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2599.17 5867.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0147 733.64 15.93 11.224

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3226 733.64 15.93 4.720

TEGV 0.0000 0.2349 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.78 10.86 16.244

FanDuct 0.0000 0.5012 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 841.56 42.31 31.483

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.78 10.86 16.244

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 940.22 66.66 45.960

Splitter 8.4645 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.78 10.86 16.244

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8931.3 2271.2 3862.2 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8658 523.98 -34.80 7.863

LP_Shaft 2132.7 4701.4 1909.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1483 940.22 66.66 44.901

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7548 940.22 66.66 25.638

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 940.22 66.66 45.960

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 940.22 66.66 45.960

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 940.22 66.66 45.960

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.48 -16.93 6.149

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.48 -16.93 6.149

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.48 -16.93 6.149

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.48 -16.93 6.149

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1673.20 0.9995 0.0230 0.22048 0.01090 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.083 0.9801 1.0000 0.9800 613.40 0.341 488.3 421.8

Byp_Nozz 1.411 0.9800 1.0000 0.9800 2006.86 0.719 717.5 6200.4

NASA/TM—2013-218094 K–26
************************************************************************************************************************************ 

Date:07/05/13 Time:11:15:17 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 50/ 2/19 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.27 Stator 1 exit: 477.40 Stator 2 inlet: 482.10 Stator 2 exit: 483.97 

 Stator 3 inlet: 489.18 Stator 3 exit: 490.64 Stator 4 inlet: 495.62 Stator 4 exit: 496.68 

 Stator 5 inlet: 500.34 Stator 5 exit: 501.11 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.83 

Fan Bypass Relative Humidity 3.92 

LPC Inlet Relative Humidity 3.81 

LPC Exit Relative Humidity 1.16 

HPC Relative Humidity 0.08 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 571.13 Fan/LPC Inlet Flow Velocity 193.27 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.36 

Ambient Static Temperature 445.14 Fan/LPC Inlet Static Temperature 469.21 

Additional Water at LPC Exit 0.0046325 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 18.00 330.91 775.1 1.0929 847.06 7.1100 571.13 7.359 0.859 10.000 1681.9 1587.3 1116.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 330.91 6.516 472.33 -18.03 0.0000 712.17 5.297 445.14 2597.9 0.5520 1.40072 0.0001274 330.87 0.042 0.0001

FS1 Inlet.Fl_O 330.91 6.516 472.33 -18.03 0.0000 712.17 6.110 463.71 4168.2 0.3044 1.40072 0.0001274 330.87 0.042 0.0001

FS12 Splitter.Fl_02 290.11 6.513 472.33 -18.03 0.0000 624.67 6.076 463.03 3531.8 0.3165 1.40072 0.0001274 290.07 0.037 0.0001

FS2 Splitter.Fl_01 40.80 6.513 472.33 -18.03 0.0000 87.86 6.364 469.21 830.5 0.1820 1.40072 0.0001274 40.80 0.005 0.0001

FS14 Fan.Fl_O 290.11 7.066 484.65 -15.07 0.0000 583.25 6.264 468.24 2606.7 0.4183 1.40061 0.0001274 290.07 0.037 0.0001

FS23 LPC.Fl_O 40.80 8.252 512.38 -8.42 0.0000 72.22 7.710 502.53 412.6 0.3128 1.40030 0.0001274 40.80 0.005 0.0001

FS24 VaporIN.Fl_O 40.99 8.252 518.87 -33.48 0.0000 73.02 7.696 508.64 412.6 0.3173 1.39958 0.0047599 40.80 0.194 0.0047

FS25 Bleed2.Fl_O 28.69 8.252 518.87 -33.48 0.0000 51.11 7.990 514.12 412.6 0.2151 1.39958 0.0047599 28.56 0.136 0.0047

FS3 HPC.Fl_O 27.30 47.950 930.01 66.64 0.0000 11.20 42.378 898.61 49.7 0.4258 1.38416 0.0047599 27.17 0.129 0.0047

FS36 Bleed3.Fl_O 21.16 47.950 930.01 66.64 0.0000 8.68 44.745 912.30 49.3 0.3176 1.38416 0.0047599 21.06 0.100 0.0047

FS4 Burner.Fl_O 21.39 46.846 1681.87 54.34 0.0112 12.09 44.227 1657.86 74.6 0.2948 1.33241 0.0047599 21.06 0.100 0.0182

FS45 HPT.Fl_O 28.59 12.061 1121.21 -42.45 0.0083 51.23 11.075 1095.83 265.4 0.3549 1.36658 0.0047599 28.22 0.134 0.0149

FS49 LPT.Fl_O 28.93 5.629 946.68 -84.93 0.0082 102.03 5.466 939.07 860.2 0.2071 1.37772 0.0047599 28.56 0.136 0.0147

FS5 TEGV.Fl_O 28.93 5.629 946.75 -84.93 0.0082 102.04 5.466 939.14 860.2 0.2071 1.37772 0.0047599 28.56 0.136 0.0147

FS8 Core_Nozz.Fl_O 28.93 5.629 946.82 -84.93 0.0082 102.04 5.297 931.14 613.4 0.2984 1.37771 0.0047599 28.56 0.136 0.0147

FS17 FanDuctLkg.Fl_O 290.11 7.066 484.65 -15.07 0.0000 583.25 6.264 468.24 2606.7 0.4183 1.40061 0.0001274 290.07 0.037 0.0001

FS171 Bleed15.Fl_O 302.40 7.066 486.05 -15.82 0.0000 608.85 6.068 465.34 2481.9 0.4713 1.40057 0.0003149 302.31 0.095 0.0003

FS172 FanDuct.Fl_O 302.40 7.066 486.05 -15.82 0.0000 608.85 6.068 465.34 2481.9 0.4713 1.40057 0.0003149 302.31 0.095 0.0003

FS173 Byp_Nozz.Fl_O 302.40 7.066 486.05 -15.82 0.0000 608.85 5.297 447.59 2006.9 0.6549 1.40057 0.0003149 302.31 0.095 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 624.67 1.085 0.9039 2054.570 1.0261 0.9050 -1212.6 -2862.02 49.81

LPC 87.86 1.267 0.8256 2054.570 1.0848 0.8314 -554.4 6.36 2.41

HPC 51.11 5.811 0.8137 8864.644 1.7924 0.8526 -3966.1 61.03 57.40

HPT 12.09 3.884 0.8741 216.197 1.3450 0.8528 3966.2 

LPT 51.23 2.142 0.8229 58.554 1.1815 0.8067 1766.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 725.81 1.083 0.9057 2034.980 0.0426 0.8607 1.0235 0.9980 0.9905

LPC 53.80 1.315 0.7610 0.543 0.0000 1.6329 0.8487 1.0850 0.0003

HPC 46.49 5.584 0.8221 8628.318 11.0332 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.804 0.8741 1.299 3.8043 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.859 0.8290 0.659 1.8593 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–27
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2597.91 5874.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0559 725.91 16.58 12.061

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3357 725.91 16.58 5.629

TEGV 0.0000 0.2071 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 705.31 11.57 16.985

FanDuct 0.0000 0.4713 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 832.52 42.61 32.865

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 705.31 11.57 16.985

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 930.01 66.64 47.950

Splitter 7.1100 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 705.31 11.57 16.985

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8866.4 2349.4 3966.2 WB17Y Bleed> 0.3000 1.0000 1.0000 12.2974 518.87 -33.48 8.252

LP_Shaft 1960.6 4733.2 1766.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2763 930.01 66.64 46.846

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8668 930.01 66.64 26.949

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 930.01 66.64 47.950

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 930.01 66.64 47.950

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 930.01 66.64 47.950

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 484.65 -15.07 7.066

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 484.65 -15.07 7.066

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 484.65 -15.07 7.066

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 484.65 -15.07 7.066

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1681.80 0.9995 0.0230 0.23529 0.01117 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.063 0.9801 1.0000 0.9800 613.40 0.298 434.7 390.8

Byp_Nozz 1.334 0.9800 1.0000 0.9800 2006.86 0.655 665.8 6258.3

NASA/TM—2013-218094 K–28
************************************************************************************************************************************ 

Date:07/05/13 Time:11:15:53 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 33/ 61/ 2/30 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 486.43 Stator 1 exit: 489.44 Stator 2 inlet: 492.29 Stator 2 exit: 493.11 

 Stator 3 inlet: 496.53 Stator 3 exit: 496.92 Stator 4 inlet: 500.25 Stator 4 exit: 500.33 

 Stator 5 inlet: 502.26 Stator 5 exit: 502.15 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.86 

Fan Bypass Relative Humidity 4.89 

LPC Inlet Relative Humidity 5.02 

LPC Exit Relative Humidity 2.54 

HPC Relative Humidity 0.09 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 518.26 Fan/LPC Inlet Flow Velocity 203.16 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 465.18 Fan/LPC Inlet Static Temperature 484.12 

Additional Water at LPC Exit 0.0050450 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 18.00 368.61 863.8 1.0938 944.87 6.2869 518.26 6.484 0.890 10.000 1716.0 1617.4 1148.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 368.61 7.943 487.56 -15.16 0.0000 661.20 6.740 465.18 2619.3 0.4900 1.40057 0.0002627 368.52 0.097 0.0003

FS1 Inlet.Fl_O 368.61 7.943 487.56 -15.16 0.0000 661.20 7.521 480.00 4168.2 0.2803 1.40057 0.0002627 368.52 0.097 0.0003

FS12 Splitter.Fl_02 318.03 7.939 487.56 -15.16 0.0000 570.75 7.500 479.69 3531.8 0.2861 1.40057 0.0002627 317.94 0.084 0.0003

FS2 Splitter.Fl_01 50.59 7.939 487.56 -15.16 0.0000 90.78 7.745 484.12 830.5 0.1883 1.40057 0.0002627 50.57 0.013 0.0003

FS14 Fan.Fl_O 318.03 8.522 498.58 -12.52 0.0000 537.67 7.719 484.66 2606.7 0.3786 1.40045 0.0002627 317.94 0.084 0.0003

FS23 LPC.Fl_O 50.59 9.130 515.91 -8.36 0.0000 81.21 8.356 503.00 412.6 0.3581 1.40023 0.0002627 50.57 0.013 0.0003

FS24 VaporIN.Fl_O 50.84 9.130 522.91 -35.64 0.0000 82.17 8.332 509.44 412.6 0.3638 1.39945 0.0053078 50.57 0.268 0.0053

FS25 Bleed2.Fl_O 30.50 9.130 522.91 -35.64 0.0000 49.30 8.861 518.47 412.6 0.2071 1.39945 0.0053078 30.34 0.161 0.0053

FS3 HPC.Fl_O 29.02 51.507 930.22 63.61 0.0000 11.09 45.661 899.59 49.7 0.4205 1.38407 0.0053078 28.87 0.153 0.0053

FS36 Bleed3.Fl_O 22.49 51.507 930.22 63.61 0.0000 8.59 48.139 912.91 49.3 0.3140 1.38407 0.0053078 22.38 0.119 0.0053

FS4 Burner.Fl_O 22.76 50.321 1716.02 50.74 0.0117 12.09 47.505 1691.63 74.6 0.2952 1.33033 0.0053078 22.38 0.119 0.0194

FS45 HPT.Fl_O 30.41 13.596 1152.90 -44.99 0.0088 49.01 12.589 1129.41 265.4 0.3375 1.36417 0.0053078 29.99 0.159 0.0159

FS49 LPT.Fl_O 30.77 7.051 997.43 -82.80 0.0086 88.92 6.897 991.44 860.2 0.1796 1.37425 0.0053078 30.34 0.161 0.0158

FS5 TEGV.Fl_O 30.77 7.051 997.50 -82.80 0.0086 88.93 6.897 991.51 860.2 0.1796 1.37425 0.0053078 30.34 0.161 0.0158

FS8 Core_Nozz.Fl_O 30.77 7.051 997.57 -82.80 0.0086 88.93 6.740 985.38 613.4 0.2569 1.37424 0.0053078 30.34 0.161 0.0158

FS17 FanDuctLkg.Fl_O 318.03 8.522 498.58 -12.52 0.0000 537.67 7.719 484.66 2606.7 0.3786 1.40045 0.0002627 317.94 0.084 0.0003

FS171 Bleed15.Fl_O 338.36 8.522 500.04 -13.91 0.0000 572.90 7.482 481.77 2481.9 0.4352 1.40039 0.0005645 338.17 0.191 0.0006

FS172 FanDuct.Fl_O 338.36 8.522 500.04 -13.91 0.0000 572.90 7.482 481.77 2481.9 0.4352 1.40039 0.0005645 338.17 0.191 0.0006

FS173 Byp_Nozz.Fl_O 338.36 8.522 500.04 -13.91 0.0000 572.90 6.740 467.59 2006.9 0.5886 1.40039 0.0005645 338.17 0.191 0.0006

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 570.75 1.073 0.9059 1859.517 1.0226 0.9069 -1189.0 -1898.08 46.37

LPC 90.78 1.150 0.7009 1859.517 1.0582 0.7067 -486.8 6.92 2.24

HPC 49.30 5.641 0.8098 8806.179 1.7789 0.8490 -4179.6 60.83 57.00

HPT 12.09 3.701 0.8764 213.449 1.3304 0.8563 4179.6 

LPT 49.01 1.928 0.8161 53.097 1.1526 0.8019 1675.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 663.16 1.072 0.9077 1841.787 0.0439 0.8607 1.0235 0.9980 0.9905

LPC 47.37 1.250 0.7561 0.491 0.0000 1.9165 0.6000 0.9269 0.0003

HPC 44.84 5.423 0.8182 8571.412 11.0706 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.626 0.8764 1.283 3.6262 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.698 0.8222 0.597 1.6982 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–29
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2619.30 5937.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.1226 728.02 13.99 13.596

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3569 728.02 13.99 7.051

TEGV 0.0000 0.1796 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 707.61 9.02 18.453

FanDuct 0.0000 0.4352 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 833.64 39.79 35.404

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 707.61 9.02 18.453

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 930.22 63.61 51.507

Splitter 6.2869 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 707.61 9.02 18.453

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8842.1 2482.6 4179.6 WB17Y Bleed> 0.4000 1.0000 1.0000 20.3362 522.91 -35.64 9.130

LP_Shaft 1802.9 4881.7 1675.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4830 930.22 63.61 50.321

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 3.0477 930.22 63.61 29.314

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 930.22 63.61 51.507

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 930.22 63.61 51.507

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 930.22 63.61 51.507

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 498.58 -12.52 8.522

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 498.58 -12.52 8.522

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 498.58 -12.52 8.522

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 498.58 -12.52 8.522

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1715.97 0.9995 0.0230 0.26246 0.01173 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.046 0.9801 1.0000 0.9800 613.40 0.257 384.6 367.8

Byp_Nozz 1.264 0.9800 1.0000 0.9800 2006.86 0.589 611.8 6433.7

NASA/TM—2013-218094 K–30
************************************************************************************************************************************ 

Date:07/05/13 Time:11:16:32 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 45/ 73/ 2/42 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 500.42 Stator 1 exit: 502.83 Stator 2 inlet: 505.20 Stator 2 exit: 505.94 

 Stator 3 inlet: 508.67 Stator 3 exit: 509.07 Stator 4 inlet: 511.74 Stator 4 exit: 511.95 

 Stator 5 inlet: 513.62 Stator 5 exit: 513.67 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.54 

Fan Bypass Relative Humidity 5.94 

LPC Inlet Relative Humidity 5.70 

LPC Exit Relative Humidity 3.33 

HPC Relative Humidity 0.15 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 479.99 Fan/LPC Inlet Flow Velocity 172.31 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.18 

Ambient Static Temperature 481.63 Fan/LPC Inlet Static Temperature 498.34 

Additional Water at LPC Exit 0.0062740 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 18.00 387.48 679.7 1.3219 898.46 6.8471 479.99 5.320 0.902 10.000 1670.4 1573.8 1140.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 387.48 9.342 500.81 -13.05 0.0000 598.97 8.149 481.63 2546.1 0.4460 1.40040 0.0004484 387.31 0.174 0.0004

FS1 Inlet.Fl_O 387.48 9.342 500.81 -13.05 0.0000 598.97 8.939 494.54 4168.2 0.2517 1.40040 0.0004484 387.31 0.174 0.0004

FS12 Splitter.Fl_02 338.10 9.337 500.81 -13.05 0.0000 522.90 8.909 494.13 3531.8 0.2600 1.40040 0.0004484 337.95 0.152 0.0004

FS2 Splitter.Fl_01 49.38 9.337 500.81 -13.05 0.0000 76.37 9.177 498.34 830.5 0.1574 1.40040 0.0004484 49.36 0.022 0.0004

FS14 Fan.Fl_O 338.10 9.826 508.99 -11.09 0.0000 500.92 9.036 496.93 2606.7 0.3483 1.40030 0.0004484 337.95 0.152 0.0004

FS23 LPC.Fl_O 49.38 10.483 523.69 -7.56 0.0000 69.56 9.848 514.42 412.6 0.2999 1.40010 0.0004484 49.36 0.022 0.0004

FS24 VaporIN.Fl_O 49.69 10.483 532.27 -41.45 0.0000 70.57 9.826 522.53 412.6 0.3056 1.39912 0.0067224 49.36 0.332 0.0067

FS25 Bleed2.Fl_O 29.81 10.483 532.27 -41.45 0.0000 42.34 10.257 528.97 412.6 0.1767 1.39912 0.0067224 29.61 0.199 0.0067

FS3 HPC.Fl_O 28.37 49.699 902.08 48.69 0.0000 11.06 44.087 872.46 49.7 0.4191 1.38547 0.0067224 28.18 0.189 0.0067

FS36 Bleed3.Fl_O 21.98 49.699 902.08 48.69 0.0000 8.57 46.463 885.33 49.3 0.3131 1.38547 0.0067224 21.84 0.147 0.0067

FS4 Burner.Fl_O 22.23 48.554 1670.35 36.33 0.0114 12.08 45.841 1646.52 74.6 0.2948 1.33250 0.0067224 21.84 0.147 0.0204

FS45 HPT.Fl_O 29.71 14.322 1144.85 -50.47 0.0085 45.30 13.427 1125.25 265.4 0.3088 1.36464 0.0067224 29.27 0.197 0.0170

FS49 LPT.Fl_O 30.06 8.400 1018.64 -80.92 0.0084 73.71 8.275 1014.49 860.2 0.1481 1.37285 0.0067224 29.61 0.199 0.0169

FS5 TEGV.Fl_O 30.06 8.400 1018.71 -80.92 0.0084 73.71 8.275 1014.56 860.2 0.1481 1.37284 0.0067224 29.61 0.199 0.0169

FS8 Core_Nozz.Fl_O 30.06 8.400 1018.78 -80.92 0.0084 73.71 8.149 1010.43 613.3 0.2105 1.37284 0.0067224 29.61 0.199 0.0169

FS17 FanDuctLkg.Fl_O 338.10 9.826 508.99 -11.09 0.0000 500.92 9.036 496.93 2606.7 0.3483 1.40030 0.0004484 337.95 0.152 0.0004

FS171 Bleed15.Fl_O 357.98 9.826 510.29 -12.77 0.0000 531.04 8.820 494.77 2481.9 0.3959 1.40023 0.0007946 357.70 0.284 0.0008

FS172 FanDuct.Fl_O 357.98 9.826 510.29 -12.77 0.0000 531.04 8.820 494.77 2481.9 0.3959 1.40023 0.0007946 357.70 0.284 0.0008

FS173 Byp_Nozz.Fl_O 357.98 9.826 510.29 -12.77 0.0000 531.04 8.149 483.71 2006.9 0.5240 1.40023 0.0007946 357.70 0.284 0.0008

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 522.90 1.052 0.9000 1622.380 1.0163 0.9007 -938.7 -1530.50 44.70

LPC 76.37 1.123 0.7362 1622.380 1.0457 0.7405 -383.4 8.18 1.95

HPC 42.34 4.741 0.7956 8545.229 1.6948 0.8340 -3709.9 68.50 63.29 

HPT 12.08 3.390 0.8682 211.807 1.3030 0.8485 3709.9 

LPT 45.30 1.705 0.8029 47.116 1.1204 0.7907 1322.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 607.56 1.051 0.9018 1606.910 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 40.07 1.188 0.7484 0.429 0.0000 1.9057 0.6541 0.9837 0.0003

HPC 38.51 4.565 0.8038 8317.419 10.7439 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.324 0.8682 1.273 3.3240 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.530 0.8089 0.530 1.5303 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–31
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2546.12 5780.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0971 718.34 3.62 14.322

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3488 718.34 3.62 8.400

TEGV 0.0000 0.1481 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 699.82 -0.89 19.110

FanDuct 0.0000 0.3959 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 814.26 27.06 34.797

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 699.82 -0.89 19.110

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 902.08 48.69 49.699

Splitter 6.8471 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 699.82 -0.89 19.110

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8656.5 2250.9 3709.9 WB17Y Bleed> 0.4000 1.0000 1.0000 19.8754 532.27 -41.45 10.483

LP_Shaft 1594.2 4355.9 1322.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4041 902.08 48.69 48.554

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9786 902.08 48.69 28.973

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 902.08 48.69 49.699

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 902.08 48.69 49.699

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 902.08 48.69 49.699

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 508.99 -11.09 9.826

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 508.99 -11.09 9.826

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 508.99 -11.09 9.826

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 508.99 -11.09 9.826

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1670.29 0.9995 0.0230 0.24957 0.01143 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.031 0.9801 1.0000 0.9800 613.40 0.210 319.0 298.1

Byp_Nozz 1.206 0.9800 1.0000 0.9800 2006.86 0.524 553.8 6162.3

NASA/TM—2013-218094 K–32
5μm, 2g/m3

, ISA +27R

************************************************************************************************************************************ 

Date:04/04/13 Time:08:33:20 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.74 Stator 1 exit: 481.44 Stator 2 inlet: 491.10 Stator 2 exit: 496.08 

 Stator 3 inlet: 506.00 Stator 3 exit: 510.52 Stator 4 inlet: 519.75 Stator 4 exit: 523.58 

 Stator 5 inlet: 531.12 Stator 5 exit: 534.43 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.87 

Fan Bypass Relative Humidity 1.31 

LPC Inlet Relative Humidity 1.21 

LPC Exit Relative Humidity 0.11 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 781.11 Fan/LPC Inlet Flow Velocity 188.09 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 464.88 

Additional Water at LPC Exit 0.0065190 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 27.00 254.88 641.4 1.1030 707.49 8.7021 781.11 9.514 0.736 10.000 1748.7 1654.5 1151.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 254.88 4.267 467.83 -18.66 0.0000 833.73 2.854 416.97 2543.5 0.7800 1.40077 0.0000507 254.86 0.013 0.0001

FS1 Inlet.Fl_O 254.88 4.267 467.83 -18.66 0.0000 833.73 3.892 455.67 4168.2 0.3649 1.40077 0.0000507 254.86 0.013 0.0001

FS12 Splitter.Fl_02 228.61 4.265 467.83 -18.66 0.0000 748.17 3.838 453.93 3531.8 0.3910 1.40077 0.0000507 228.59 0.012 0.0001

FS2 Splitter.Fl_01 26.27 4.265 467.83 -18.66 0.0000 85.98 4.171 464.88 830.5 0.1779 1.40077 0.0000507 26.27 0.001 0.0001

FS14 Fan.Fl_O 228.61 4.825 486.40 -14.21 0.0000 674.27 4.048 462.58 2606.7 0.5069 1.40061 0.0000507 228.59 0.012 0.0001

FS23 LPC.Fl_O 26.27 6.679 544.53 -0.27 0.0000 59.23 6.392 537.74 412.6 0.2514 1.39985 0.0000507 26.27 0.001 0.0001

FS24 VaporIN.Fl_O 26.44 6.679 553.21 -35.52 0.0000 60.09 6.382 546.08 412.6 0.2560 1.39881 0.0065697 26.27 0.173 0.0065

FS25 Bleed2.Fl_O 23.80 6.679 553.21 -35.52 0.0000 54.08 6.440 547.51 412.6 0.2286 1.39881 0.0065697 23.64 0.155 0.0065

FS3 HPC.Fl_O 22.64 40.595 1000.91 74.13 0.0000 11.39 35.687 965.97 49.7 0.4357 1.37964 0.0065697 22.50 0.148 0.0065

FS36 Bleed3.Fl_O 17.55 40.595 1000.91 74.13 0.0000 8.82 37.780 981.29 49.3 0.3242 1.37964 0.0065697 17.43 0.115 0.0065

FS4 Burner.Fl_O 17.74 39.660 1748.67 61.66 0.0113 12.07 37.445 1723.93 74.6 0.2951 1.32894 0.0065697 17.43 0.115 0.0201

FS45 HPT.Fl_O 23.72 9.517 1156.08 -44.59 0.0084 54.67 8.617 1125.76 265.4 0.3841 1.36401 0.0065697 23.37 0.154 0.0167

FS49 LPT.Fl_O 23.99 3.263 905.69 -106.38 0.0083 142.79 3.071 890.69 860.2 0.2976 1.37987 0.0065697 23.64 0.155 0.0166

FS5 TEGV.Fl_O 23.99 3.263 905.76 -106.38 0.0083 142.80 3.071 890.76 860.2 0.2976 1.37987 0.0065697 23.64 0.155 0.0166

FS8 Core_Nozz.Fl_O 23.99 3.263 905.84 -106.38 0.0083 142.80 2.854 872.97 613.4 0.4445 1.37986 0.0065697 23.64 0.155 0.0166

FS17 FanDuctLkg.Fl_O 228.61 4.825 486.40 -14.21 0.0000 674.27 4.048 462.58 2606.7 0.5069 1.40061 0.0000507 228.59 0.012 0.0001

FS171 Bleed15.Fl_O 231.25 4.825 487.16 -14.45 0.0000 682.61 3.914 458.86 2481.9 0.5548 1.40059 0.0001248 231.22 0.029 0.0001

FS172 FanDuct.Fl_O 231.25 4.825 487.16 -14.45 0.0000 682.61 3.914 458.86 2481.9 0.5548 1.40059 0.0001248 231.22 0.029 0.0001 

FS173 Byp_Nozz.Fl_O 231.25 4.825 487.16 -14.45 0.0000 682.61 2.854 419.20 2006.9 0.8994 1.40059 0.0001248 231.22 0.029 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 748.17 1.131 0.9059 2578.090 1.0397 0.9075 -1439.1 1544.31 54.69

LPC 85.98 1.566 0.8346 2578.090 1.1639 0.8448 -683.7 7.00 3.80

HPC 54.08 6.078 0.8182 8960.188 1.8093 0.8569 -3602.5 61.62 58.27

HPT 12.07 4.167 0.8768 221.291 1.3641 0.8547 3602.5 

LPT 54.67 2.917 0.8555 72.012 1.2747 0.8359 2122.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 869.30 1.128 0.9078 2553.508 0.0415 0.8607 1.0235 0.9980 0.9905

LPC 74.33 1.526 0.7804 0.681 0.0000 1.1567 1.0754 1.0696 0.0003

HPC 49.18 5.839 0.8267 8721.315 10.9601 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.079 0.8767 1.330 4.0795 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.441 0.8618 0.810 2.4415 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–33
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2543.49 6187.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8757 779.09 19.30 9.517

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2784 779.09 19.30 3.263 

TEGV 0.0000 0.2976 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 756.65 13.82 14.140

FanDuct 0.0000 0.5548 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 895.07 47.81 27.707

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 756.65 13.82 14.140

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1000.91 74.13 40.595

Splitter 8.7021 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 756.65 13.82 14.140

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9253.8 2044.7 3602.5 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6442 553.21 -35.52 6.679

LP_Shaft 2448.5 4553.5 2122.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7172 1000.91 74.13 39.660

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3776 1000.91 74.13 22.418

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1000.91 74.13 40.595

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1000.91 74.13 40.595

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1000.91 74.13 40.595

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.40 -14.21 4.825

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.40 -14.21 4.825

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.40 -14.21 4.825

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.40 -14.21 4.825

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1748.62 0.9995 0.0230 0.19653 0.01127 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.445 628.0 468.4

Byp_Nozz 1.691 0.9800 1.0000 0.9800 2006.86 0.899 885.0 6360.8

NASA/TM—2013-218094 K–34
************************************************************************************************************************************ 

Date:04/04/13 Time:08:33:45 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 467.07 Stator 1 exit: 474.28 Stator 2 inlet: 483.32 Stator 2 exit: 487.97 

 Stator 3 inlet: 497.25 Stator 3 exit: 501.46 Stator 4 inlet: 510.10 Stator 4 exit: 513.67 

 Stator 5 inlet: 520.74 Stator 5 exit: 523.81 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.35 

Fan Bypass Relative Humidity 1.69 

LPC Inlet Relative Humidity 1.54 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 731.04 Fan/LPC Inlet Flow Velocity 181.64 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 458.77 

Additional Water at LPC Exit 0.0058255 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 27.00 248.00 627.9 1.0732 673.92 8.7855 731.04 9.234 0.763 10.000 1720.2 1626.7 1134.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 248.00 4.201 461.52 -20.16 0.0000 818.30 2.947 416.97 2561.1 0.7300 1.40081 0.0000491 247.99 0.012 0.0000

FS1 Inlet.Fl_O 248.00 4.201 461.52 -20.16 0.0000 818.30 3.847 450.03 4168.2 0.3570 1.40081 0.0000491 247.99 0.012 0.0000

FS12 Splitter.Fl_02 222.66 4.199 461.52 -20.16 0.0000 735.05 3.795 448.36 3531.8 0.3827 1.40081 0.0000491 222.65 0.011 0.0000

FS2 Splitter.Fl_01 25.34 4.199 461.52 -20.16 0.0000 83.67 4.112 458.77 830.5 0.1729 1.40081 0.0000491 25.34 0.001 0.0000

FS14 Fan.Fl_O 222.66 4.718 478.81 -16.02 0.0000 666.32 3.981 456.10 2606.7 0.4985 1.40067 0.0000491 222.65 0.011 0.0000

FS23 LPC.Fl_O 25.34 6.437 533.31 -2.95 0.0000 58.67 6.166 526.78 412.6 0.2488 1.40002 0.0000491 25.34 0.001 0.0000

FS24 VaporIN.Fl_O 25.49 6.437 541.20 -34.47 0.0000 59.45 6.157 534.37 412.6 0.2529 1.39910 0.0058747 25.34 0.149 0.0058

FS25 Bleed2.Fl_O 22.94 6.437 541.20 -34.47 0.0000 53.50 6.212 535.74 412.6 0.2259 1.39910 0.0058747 22.81 0.134 0.0058

FS3 HPC.Fl_O 21.83 38.796 977.79 72.25 0.0000 11.35 34.142 943.84 49.7 0.4337 1.38116 0.0058747 21.70 0.127 0.0058

FS36 Bleed3.Fl_O 16.92 38.796 977.79 72.25 0.0000 8.80 36.125 958.70 49.3 0.3229 1.38116 0.0058747 16.82 0.099 0.0058

FS4 Burner.Fl_O 17.11 37.903 1720.20 59.95 0.0111 12.08 35.785 1695.76 74.6 0.2949 1.33045 0.0058747 16.82 0.099 0.0193

FS45 HPT.Fl_O 22.86 9.210 1138.44 -43.42 0.0083 54.05 8.361 1109.32 265.4 0.3785 1.36532 0.0058747 22.54 0.132 0.0159

FS49 LPT.Fl_O 23.13 3.313 902.50 -101.44 0.0082 135.34 3.139 889.19 860.2 0.2804 1.38022 0.0058747 22.81 0.134 0.0158

FS5 TEGV.Fl_O 23.13 3.313 902.57 -101.44 0.0082 135.35 3.139 889.26 860.2 0.2804 1.38022 0.0058747 22.81 0.134 0.0158

FS8 Core_Nozz.Fl_O 23.13 3.313 902.64 -101.44 0.0082 135.35 2.947 873.93 613.4 0.4151 1.38021 0.0058747 22.81 0.134 0.0158

FS17 FanDuctLkg.Fl_O 222.66 4.718 478.81 -16.02 0.0000 666.32 3.981 456.10 2606.7 0.4985 1.40067 0.0000491 222.65 0.011 0.0000

FS171 Bleed15.Fl_O 225.21 4.718 479.52 -16.23 0.0000 674.45 3.856 452.61 2481.9 0.5447 1.40066 0.0001147 225.18 0.026 0.0001

FS172 FanDuct.Fl_O 225.21 4.718 479.52 -16.23 0.0000 674.45 3.856 452.61 2481.9 0.5447 1.40066 0.0001147 225.18 0.026 0.0001

FS173 Byp_Nozz.Fl_O 225.21 4.718 479.52 -16.23 0.0000 674.45 2.947 419.09 2006.9 0.8481 1.40066 0.0001147 225.18 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 735.05 1.124 0.9051 2513.662 1.0375 0.9067 -1305.3 2076.94 54.57

LPC 83.67 1.533 0.8353 2513.662 1.1555 0.8449 -617.2 6.81 3.37

HPC 53.50 6.027 0.8175 8941.663 1.8067 0.8562 -3380.0 61.49 58.09

HPT 12.08 4.116 0.8754 220.223 1.3611 0.8534 3380.0 

LPT 54.05 2.780 0.8497 70.275 1.2595 0.8304 1922.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 854.05 1.121 0.9070 2489.695 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 71.54 1.498 0.7773 0.664 0.0000 1.1694 1.0709 1.0745 0.0003

HPC 48.66 5.790 0.8260 8703.284 10.9750 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.029 0.8754 1.324 4.0293 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.339 0.8561 0.791 2.3387 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–35
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.10 5634.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8443 761.33 18.89 9.210

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2684 761.33 18.89 3.313

TEGV 0.0000 0.2804 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 739.45 13.56 13.556

FanDuct 0.0000 0.5447 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 874.47 46.64 26.500

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 739.45 13.56 13.556

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 977.79 72.25 38.796

Splitter 8.7855 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 739.45 13.56 13.556 

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9133.8 1943.5 3380.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5492 541.20 -34.47 6.437

LP_Shaft 2371.1 4258.3 1922.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6196 977.79 72.25 37.903

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2922 977.79 72.25 21.490

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 977.79 72.25 38.796

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 977.79 72.25 38.796

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 977.79 72.25 38.796

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 478.81 -16.02 4.718

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 478.81 -16.02 4.718

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 478.81 -16.02 4.718

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 478.81 -16.02 4.718

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1720.14 0.9995 0.0230 0.18720 0.01113 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.415 586.7 421.8

Byp_Nozz 1.601 0.9800 1.0000 0.9800 2006.86 0.848 834.5 5841.1

NASA/TM—2013-218094 K–36
************************************************************************************************************************************ 

Date:04/04/13 Time:08:34:09 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.00 Stator 1 exit: 472.02 Stator 2 inlet: 480.81 Stator 2 exit: 485.33 

 Stator 3 inlet: 494.36 Stator 3 exit: 498.45 Stator 4 inlet: 506.86 Stator 4 exit: 510.32 

 Stator 5 inlet: 517.21 Stator 5 exit: 520.19 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.52 

Fan Bypass Relative Humidity 1.84 

LPC Inlet Relative Humidity 1.66 

LPC Exit Relative Humidity 0.16 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 715.01 Fan/LPC Inlet Flow Velocity 179.15 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 456.92 

Additional Water at LPC Exit 0.0052577 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 27.00 254.64 640.0 1.0699 684.75 8.8179 715.01 9.110 0.772 10.000 1707.9 1614.8 1126.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 254.64 4.339 459.59 -20.61 0.0000 811.78 3.088 416.97 2565.2 0.7140 1.40083 0.0000469 254.62 0.012 0.0000

FS1 Inlet.Fl_O 254.64 4.339 459.59 -20.61 0.0000 811.78 3.980 448.35 4168.2 0.3536 1.40083 0.0000469 254.62 0.012 0.0000

FS12 Splitter.Fl_02 228.70 4.337 459.59 -20.61 0.0000 729.46 3.927 446.72 3531.8 0.3792 1.40083 0.0000469 228.69 0.011 0.0000

FS2 Splitter.Fl_01 25.94 4.337 459.59 -20.61 0.0000 82.72 4.250 456.92 830.5 0.1709 1.40083 0.0000469 25.93 0.001 0.0000

FS14 Fan.Fl_O 228.70 4.859 476.38 -16.59 0.0000 662.88 4.110 454.09 2606.7 0.4949 1.40070 0.0000469 228.69 0.011 0.0000

FS23 LPC.Fl_O 25.94 6.590 529.47 -3.86 0.0000 58.44 6.314 523.05 412.6 0.2478 1.40008 0.0000469 25.93 0.001 0.0000

FS24 VaporIN.Fl_O 26.07 6.590 536.64 -32.31 0.0000 59.14 6.306 529.94 412.6 0.2515 1.39925 0.0053046 25.93 0.138 0.0053

FS25 Bleed2.Fl_O 23.46 6.590 536.64 -32.31 0.0000 53.23 6.362 531.28 412.6 0.2246 1.39925 0.0053046 23.34 0.124 0.0053

FS3 HPC.Fl_O 22.33 39.530 968.70 73.19 0.0000 11.34 34.800 935.12 49.7 0.4330 1.38180 0.0053046 22.21 0.118 0.0053

FS36 Bleed3.Fl_O 17.30 39.530 968.70 73.19 0.0000 8.79 36.815 949.82 49.3 0.3224 1.38180 0.0053046 17.21 0.091 0.0053

FS4 Burner.Fl_O 17.49 38.620 1707.93 60.95 0.0111 12.08 36.462 1683.63 74.6 0.2948 1.33117 0.0053046 17.21 0.091 0.0186

FS45 HPT.Fl_O 23.38 9.425 1130.77 -41.23 0.0082 53.83 8.565 1102.10 265.4 0.3765 1.36594 0.0053046 23.07 0.122 0.0153

FS49 LPT.Fl_O 23.66 3.453 900.41 -97.78 0.0081 132.66 3.279 887.70 860.2 0.2742 1.38046 0.0053046 23.34 0.124 0.0152

FS5 TEGV.Fl_O 23.66 3.453 900.48 -97.78 0.0081 132.66 3.279 887.77 860.2 0.2742 1.38046 0.0053046 23.34 0.124 0.0152

FS8 Core_Nozz.Fl_O 23.66 3.453 900.55 -97.78 0.0081 132.67 3.088 873.26 613.4 0.4048 1.38045 0.0053046 23.34 0.124 0.0152

FS17 FanDuctLkg.Fl_O 228.70 4.859 476.38 -16.59 0.0000 662.88 4.110 454.09 2606.7 0.4949 1.40070 0.0000469 228.69 0.011 0.0000

FS171 Bleed15.Fl_O 231.31 4.859 477.06 -16.77 0.0000 670.92 3.983 450.68 2481.9 0.5405 1.40068 0.0001058 231.28 0.024 0.0001

FS172 FanDuct.Fl_O 231.31 4.859 477.06 -16.77 0.0000 670.92 3.983 450.68 2481.9 0.5405 1.40068 0.0001058 231.28 0.024 0.0001

FS173 Byp_Nozz.Fl_O 231.31 4.859 477.06 -16.77 0.0000 670.92 3.088 419.04 2006.9 0.8311 1.40068 0.0001058 231.28 0.024 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 729.46 1.120 0.9047 2486.297 1.0365 0.9062 -1301.8 2436.79 54.51

LPC 82.72 1.519 0.8357 2486.297 1.1520 0.8451 -614.8 6.72 3.30

HPC 53.23 5.999 0.8171 8932.753 1.8051 0.8558 -3417.6 61.53 58.10

HPT 12.08 4.097 0.8748 219.859 1.3600 0.8526 3417.6 

LPT 53.83 2.730 0.8474 69.599 1.2538 0.8282 1916.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 847.56 1.118 0.9066 2462.591 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.36 1.485 0.7761 0.657 0.0000 1.1758 1.0699 1.0768 0.0003

HPC 48.41 5.763 0.8255 8694.612 10.9759 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.012 0.8748 1.321 4.0116 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.301 0.8537 0.783 2.3010 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–37
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2565.19 5658.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8635 754.44 20.44 9.425

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2745 754.44 20.44 3.453

TEGV 0.0000 0.2742 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.78 15.16 13.837

FanDuct 0.0000 0.5405 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 866.42 47.87 27.013

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.78 15.16 13.837

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 968.70 73.19 39.530

Splitter 8.8179 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.78 15.16 13.837

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9086.2 1975.5 3417.6 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6072 536.64 -32.31 6.590

LP_Shaft 2340.4 4301.1 1916.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6792 968.70 73.19 38.620

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3444 968.70 73.19 21.921

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 968.70 73.19 39.530

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 968.70 73.19 39.530

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 968.70 73.19 39.530

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 476.38 -16.59 4.859

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 476.38 -16.59 4.859

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 476.38 -16.59 4.859

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 476.38 -16.59 4.859

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1707.87 0.9995 0.0230 0.19021 0.01105 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.405 571.9 420.5

Byp_Nozz 1.573 0.9800 1.0000 0.9800 2006.86 0.831 817.7 5878.4

NASA/TM—2013-218094 K–38
************************************************************************************************************************************ 

Date:04/04/13 Time:08:34:25 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 466.50 Stator 1 exit: 473.07 Stator 2 inlet: 481.29 Stator 2 exit: 485.51 

 Stator 3 inlet: 493.94 Stator 3 exit: 497.73 Stator 4 inlet: 505.60 Stator 4 exit: 508.79 

 Stator 5 inlet: 515.22 Stator 5 exit: 517.96 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.13 

Fan Bypass Relative Humidity 2.36 

LPC Inlet Relative Humidity 2.11 

LPC Exit Relative Humidity 0.24 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 675.10 Fan/LPC Inlet Flow Velocity 173.29 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 423.42 Fan/LPC Inlet Static Temperature 458.91 

Additional Water at LPC Exit 0.0047504 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 27.00 275.81 689.8 1.0611 731.95 8.9045 675.10 8.753 0.795 10.000 1697.4 1604.5 1121.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 275.81 4.831 461.41 -20.25 0.0000 791.34 3.578 423.42 2579.4 0.6690 1.40081 0.0000588 275.79 0.016 0.0001

FS1 Inlet.Fl_O 275.81 4.831 461.41 -20.25 0.0000 791.34 4.453 450.77 4168.2 0.3433 1.40081 0.0000588 275.79 0.016 0.0001

FS12 Splitter.Fl_02 247.96 4.829 461.41 -20.25 0.0000 711.80 4.397 449.20 3531.8 0.3682 1.40081 0.0000588 247.95 0.015 0.0001

FS2 Splitter.Fl_01 27.85 4.829 461.41 -20.25 0.0000 79.94 4.738 458.91 830.5 0.1650 1.40081 0.0000588 27.84 0.002 0.0001

FS14 Fan.Fl_O 247.96 5.368 477.12 -16.48 0.0000 651.08 4.576 455.82 2606.7 0.4828 1.40069 0.0000588 247.95 0.015 0.0001

FS23 LPC.Fl_O 27.85 7.146 526.80 -4.57 0.0000 57.71 6.855 520.58 412.6 0.2444 1.40011 0.0000588 27.84 0.002 0.0001

FS24 VaporIN.Fl_O 27.98 7.146 533.31 -30.28 0.0000 58.34 6.848 526.85 412.6 0.2478 1.39937 0.0048092 27.84 0.134 0.0048

FS25 Bleed2.Fl_O 25.18 7.146 533.31 -30.28 0.0000 52.51 6.907 528.14 412.6 0.2213 1.39937 0.0048092 25.06 0.121 0.0048

FS3 HPC.Fl_O 23.96 42.285 959.54 73.69 0.0000 11.33 37.245 926.38 49.7 0.4320 1.38242 0.0048092 23.85 0.115 0.0048

FS36 Bleed3.Fl_O 18.57 42.285 959.54 73.69 0.0000 8.78 39.391 940.89 49.3 0.3217 1.38242 0.0048092 18.48 0.089 0.0048

FS4 Burner.Fl_O 18.77 41.311 1697.41 61.50 0.0110 12.08 39.004 1673.22 74.6 0.2948 1.33177 0.0048092 18.48 0.089 0.0181

FS45 HPT.Fl_O 25.09 10.194 1125.74 -39.17 0.0082 53.29 9.285 1097.85 265.4 0.3719 1.36636 0.0048092 24.77 0.119 0.0147

FS49 LPT.Fl_O 25.38 3.943 908.34 -92.43 0.0081 125.21 3.768 897.04 860.2 0.2574 1.38009 0.0048092 25.06 0.121 0.0146

FS5 TEGV.Fl_O 25.38 3.943 908.42 -92.43 0.0081 125.21 3.768 897.11 860.2 0.2574 1.38008 0.0048092 25.06 0.121 0.0146

FS8 Core_Nozz.Fl_O 25.38 3.943 908.49 -92.43 0.0081 125.22 3.578 884.49 613.3 0.3774 1.38008 0.0048092 25.06 0.121 0.0146

FS17 FanDuctLkg.Fl_O 247.96 5.368 477.12 -16.48 0.0000 651.08 4.576 455.82 2606.7 0.4828 1.40069 0.0000588 247.95 0.015 0.0001

FS171 Bleed15.Fl_O 250.76 5.368 477.75 -16.64 0.0000 658.86 4.445 452.64 2481.9 0.5262 1.40068 0.0001115 250.73 0.028 0.0001

FS172 FanDuct.Fl_O 250.76 5.368 477.75 -16.64 0.0000 658.86 4.445 452.64 2481.9 0.5262 1.40068 0.0001115 250.73 0.028 0.0001

FS173 Byp_Nozz.Fl_O 250.76 5.368 477.75 -16.64 0.0000 658.86 3.578 425.39 2006.9 0.7836 1.40068 0.0001115 250.73 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 711.80 1.112 0.9037 2405.476 1.0340 0.9052 -1320.5 5030.32 54.10

LPC 79.94 1.480 0.8371 2405.476 1.1417 0.8459 -617.7 6.44 3.08

HPC 52.51 5.917 0.8157 8909.132 1.7992 0.8544 -3614.6 61.85 58.34

HPT 12.08 4.052 0.8741 219.273 1.3569 0.8520 3614.6 

LPT 53.29 2.586 0.8423 67.621 1.2371 0.8238 1938.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 827.04 1.109 0.9056 2382.540 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.86 1.449 0.7723 0.635 0.0000 1.1957 1.0683 1.0840 0.0003

HPC 47.76 5.685 0.8241 8671.620 10.9653 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.968 0.8741 1.318 3.9678 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.193 0.8486 0.761 2.1925 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–39
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2579.39 5787.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9267 748.11 21.70 10.194

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2946 748.11 21.70 3.943

TEGV 0.0000 0.2574 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 726.75 16.50 14.877

FanDuct 0.0000 0.5262 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 858.60 48.74 28.932

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 726.75 16.50 14.877

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 959.54 73.69 42.285

Splitter 8.9045 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 726.75 16.50 14.877

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9034.0 2101.4 3614.6 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7979 533.31 -30.28 7.146

LP_Shaft 2268.8 4486.7 1938.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8752 959.54 73.69 41.311

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5158 959.54 73.69 23.512

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 959.54 73.69 42.285

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 959.54 73.69 42.285

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 959.54 73.69 42.285

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 477.12 -16.48 5.368

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 477.12 -16.48 5.368

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 477.12 -16.48 5.368

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 477.12 -16.48 5.368

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1697.35 0.9995 0.0230 0.20332 0.01100 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.377 536.4 423.2

Byp_Nozz 1.500 0.9800 1.0000 0.9800 2006.86 0.784 776.7 6053.8

NASA/TM—2013-218094 K–40
************************************************************************************************************************************ 

Date:04/04/13 Time:08:34:42 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 15/ 29/ 1/13 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 474.95 Stator 1 exit: 480.63 Stator 2 inlet: 487.65 Stator 2 exit: 491.07 

 Stator 3 inlet: 498.37 Stator 3 exit: 501.38 Stator 4 inlet: 508.23 Stator 4 exit: 510.71 

 Stator 5 inlet: 516.21 Stator 5 exit: 518.29 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.08 

Fan Bypass Relative Humidity 3.22 

LPC Inlet Relative Humidity 2.94 

LPC Exit Relative Humidity 0.50 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 624.43 Fan/LPC Inlet Flow Velocity 174.75 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 438.58 Fan/LPC Inlet Static Temperature 468.53 

Additional Water at LPC Exit 0.0047726 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 27.00 301.88 743.4 1.0696 795.15 8.4760 624.43 8.168 0.828 10.000 1698.4 1605.0 1125.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 301.88 5.595 471.08 -18.23 0.0000 755.65 4.358 438.58 2595.7 0.6080 1.40073 0.0001104 301.84 0.033 0.0001

FS1 Inlet.Fl_O 301.88 5.595 471.08 -18.23 0.0000 755.65 5.199 461.28 4168.2 0.3255 1.40073 0.0001104 301.84 0.033 0.0001

FS12 Splitter.Fl_02 270.02 5.592 471.08 -18.23 0.0000 676.24 5.146 460.00 3531.8 0.3467 1.40073 0.0001104 269.99 0.030 0.0001

FS2 Splitter.Fl_01 31.86 5.592 471.08 -18.23 0.0000 79.78 5.487 468.53 830.5 0.1646 1.40073 0.0001104 31.85 0.004 0.0001

FS14 Fan.Fl_O 270.02 6.144 485.31 -14.82 0.0000 624.79 5.324 465.82 2606.7 0.4569 1.40061 0.0001104 269.99 0.030 0.0001

FS23 LPC.Fl_O 31.86 7.848 527.32 -4.74 0.0000 60.15 7.499 520.51 412.6 0.2556 1.40010 0.0001104 31.85 0.004 0.0001

FS24 VaporIN.Fl_O 32.01 7.848 533.85 -30.58 0.0000 60.81 7.490 526.79 412.6 0.2591 1.39935 0.0048829 31.85 0.156 0.0049

FS25 Bleed2.Fl_O 27.21 7.848 533.85 -30.58 0.0000 51.69 7.593 528.84 412.6 0.2177 1.39935 0.0048829 27.08 0.132 0.0049

FS3 HPC.Fl_O 25.89 45.703 956.58 72.54 0.0000 11.30 40.280 923.66 49.7 0.4309 1.38259 0.0048829 25.76 0.126 0.0049

FS36 Bleed3.Fl_O 20.06 45.703 956.58 72.54 0.0000 8.76 42.588 938.05 49.3 0.3210 1.38259 0.0048829 19.97 0.097 0.0049

FS4 Burner.Fl_O 20.28 44.651 1698.45 60.30 0.0111 12.08 42.156 1674.25 74.6 0.2948 1.33167 0.0048829 19.97 0.097 0.0182

FS45 HPT.Fl_O 27.11 11.175 1129.30 -39.50 0.0083 52.61 10.207 1102.15 265.4 0.3663 1.36609 0.0048829 26.76 0.131 0.0149

FS49 LPT.Fl_O 27.43 4.716 930.87 -88.04 0.0082 114.51 4.542 921.32 860.2 0.2340 1.37871 0.0048829 27.08 0.132 0.0148

FS5 TEGV.Fl_O 27.43 4.716 930.94 -88.04 0.0082 114.51 4.542 921.39 860.2 0.2340 1.37870 0.0048829 27.08 0.132 0.0148

FS8 Core_Nozz.Fl_O 27.43 4.716 931.01 -88.04 0.0082 114.52 4.358 911.04 613.5 0.3399 1.37870 0.0048829 27.08 0.132 0.0148

FS17 FanDuctLkg.Fl_O 270.02 6.144 485.31 -14.82 0.0000 624.79 5.324 465.82 2606.7 0.4569 1.40061 0.0001104 269.99 0.030 0.0001

FS171 Bleed15.Fl_O 274.82 6.144 486.16 -15.09 0.0000 636.46 5.176 462.90 2481.9 0.5008 1.40059 0.0001934 274.77 0.053 0.0002

FS172 FanDuct.Fl_O 274.82 6.144 486.16 -15.09 0.0000 636.46 5.176 462.90 2481.9 0.5008 1.40059 0.0001934 274.77 0.053 0.0002

FS173 Byp_Nozz.Fl_O 274.82 6.144 486.16 -15.09 0.0000 636.46 4.358 440.68 2006.9 0.7176 1.40059 0.0001934 274.77 0.053 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 676.24 1.099 0.9025 2255.002 1.0302 0.9038 -1303.0 -9896.42 52.67

LPC 79.78 1.403 0.8521 2255.002 1.1194 0.8591 -607.8 5.95 2.64

HPC 51.69 5.824 0.8140 8882.190 1.7918 0.8528 -3873.2 62.24 58.63

HPT 12.08 3.996 0.8740 218.654 1.3526 0.8522 3873.2 

LPT 52.61 2.370 0.8339 63.950 1.2107 0.8164 1910.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 785.73 1.096 0.9043 2233.501 0.0417 0.8607 1.0235 0.9980 0.9905

LPC 60.51 1.384 0.7656 0.596 0.0000 1.3184 1.0509 1.1130 0.0003

HPC 47.01 5.596 0.8224 8645.397 10.9526 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.913 0.8740 1.314 3.9125 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.030 0.8401 0.719 2.0302 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–41
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2595.66 5858.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0012 746.86 20.98 11.175

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3183 746.86 20.98 4.716

TEGV 0.0000 0.2340 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 725.68 15.83 16.176

FanDuct 0.0000 0.5008 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 856.44 47.79 31.318

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 725.68 15.83 16.176

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 956.58 72.54 45.703

Splitter 8.4760 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 725.68 15.83 16.176

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9011.2 2257.4 3873.2 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8014 533.85 -30.58 7.848

LP_Shaft 2149.1 4670.0 1910.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1066 956.58 72.54 44.651

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7183 956.58 72.54 25.503

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 956.58 72.54 45.703

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 956.58 72.54 45.703

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 956.58 72.54 45.703

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 485.31 -14.82 6.144

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 485.31 -14.82 6.144

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 485.31 -14.82 6.144

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 485.31 -14.82 6.144

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1698.39 0.9995 0.0230 0.22088 0.01106 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 490.0 417.8

Byp_Nozz 1.410 0.9800 1.0000 0.9800 2006.86 0.718 724.0 6184.4

NASA/TM—2013-218094 K–42
************************************************************************************************************************************ 

Date:04/04/13 Time:08:35:12 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 21/ 49/ 2/18 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 482.85 Stator 1 exit: 487.03 Stator 2 inlet: 491.79 Stator 2 exit: 493.68 

 Stator 3 inlet: 498.94 Stator 3 exit: 500.42 Stator 4 inlet: 505.46 Stator 4 exit: 506.53 

 Stator 5 inlet: 510.22 Stator 5 exit: 511.00 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.93 

Fan Bypass Relative Humidity 4.06 

LPC Inlet Relative Humidity 3.92 

LPC Exit Relative Humidity 1.25 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 576.87 Fan/LPC Inlet Flow Velocity 193.91 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 454.14 Fan/LPC Inlet Static Temperature 478.74 

Additional Water at LPC Exit 0.0044016 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 27.00 326.71 754.1 1.1196 844.26 7.1404 576.87 7.287 0.858 10.000 1704.6 1609.0 1133.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 326.71 6.516 481.87 -16.15 0.0000 710.20 5.297 454.14 2590.8 0.5520 1.40063 0.0001988 326.64 0.065 0.0002

FS1 Inlet.Fl_O 326.71 6.516 481.87 -16.15 0.0000 710.20 6.113 473.14 4168.2 0.3035 1.40063 0.0001988 326.64 0.065 0.0002

FS12 Splitter.Fl_02 286.57 6.513 481.87 -16.15 0.0000 623.27 6.078 472.43 3531.8 0.3157 1.40063 0.0001988 286.51 0.057 0.0002

FS2 Splitter.Fl_01 40.13 6.513 481.87 -16.15 0.0000 87.29 6.366 478.74 830.5 0.1807 1.40063 0.0001988 40.13 0.008 0.0002

FS14 Fan.Fl_O 286.57 7.056 494.24 -13.19 0.0000 582.60 6.258 477.55 2606.7 0.4177 1.40050 0.0001988 286.51 0.057 0.0002

FS23 LPC.Fl_O 40.13 8.235 522.34 -6.45 0.0000 71.87 7.701 512.41 412.6 0.3111 1.40016 0.0001988 40.13 0.008 0.0002

FS24 VaporIN.Fl_O 40.31 8.235 528.40 -30.27 0.0000 72.61 7.687 518.12 412.6 0.3153 1.39947 0.0046004 40.13 0.185 0.0046

FS25 Bleed2.Fl_O 28.22 8.235 528.40 -30.27 0.0000 50.82 7.977 523.62 412.6 0.2138 1.39947 0.0046004 28.09 0.129 0.0046

FS3 HPC.Fl_O 26.85 47.484 944.78 71.20 0.0000 11.21 41.955 912.87 49.7 0.4264 1.38333 0.0046004 26.73 0.123 0.0046

FS36 Bleed3.Fl_O 20.81 47.484 944.78 71.20 0.0000 8.69 44.303 926.79 49.3 0.3180 1.38333 0.0046004 20.71 0.095 0.0046

FS4 Burner.Fl_O 21.04 46.390 1704.55 58.69 0.0113 12.08 43.797 1680.29 74.6 0.2949 1.33125 0.0046004 20.71 0.095 0.0183

FS45 HPT.Fl_O 28.12 11.977 1137.91 -39.39 0.0084 51.11 11.004 1112.35 265.4 0.3541 1.36544 0.0046004 27.76 0.128 0.0148

FS49 LPT.Fl_O 28.45 5.624 962.12 -82.25 0.0083 101.27 5.463 954.52 860.2 0.2055 1.37673 0.0046004 28.09 0.129 0.0147

FS5 TEGV.Fl_O 28.45 5.624 962.19 -82.25 0.0083 101.27 5.463 954.59 860.2 0.2055 1.37673 0.0046004 28.09 0.129 0.0147

FS8 Core_Nozz.Fl_O 28.45 5.624 962.26 -82.25 0.0083 101.27 5.297 946.62 613.4 0.2960 1.37672 0.0046004 28.09 0.129 0.0147

FS17 FanDuctLkg.Fl_O 286.57 7.056 494.24 -13.19 0.0000 582.60 6.258 477.55 2606.7 0.4177 1.40050 0.0001988 286.51 0.057 0.0002

FS171 Bleed15.Fl_O 298.66 7.056 495.63 -13.88 0.0000 608.04 6.063 474.59 2481.9 0.4705 1.40046 0.0003763 298.55 0.112 0.0004

FS172 FanDuct.Fl_O 298.66 7.056 495.63 -13.88 0.0000 608.04 6.063 474.59 2481.9 0.4705 1.40046 0.0003763 298.55 0.112 0.0004

FS173 Byp_Nozz.Fl_O 298.66 7.056 495.63 -13.88 0.0000 608.04 5.297 456.59 2006.9 0.6533 1.40046 0.0003763 298.55 0.112 0.0004

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.27 1.083 0.9031 2044.393 1.0257 0.9043 -1202.5 -2763.57 49.88

LPC 87.29 1.264 0.8262 2044.393 1.0840 0.8319 -551.1 6.38 2.41

HPC 50.82 5.766 0.8128 8854.850 1.7880 0.8517 -3953.0 61.50 57.83

HPT 12.08 3.873 0.8751 216.478 1.3437 0.8539 3952.9 

LPT 51.11 2.130 0.8239 58.416 1.1798 0.8080 1753.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.18 1.082 0.9050 2024.900 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.46 1.311 0.7607 0.540 0.0000 1.6327 0.8502 1.0861 0.0003

HPC 46.22 5.541 0.8212 8618.786 11.0083 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.794 0.8750 1.301 3.7936 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.850 0.8300 0.657 1.8498 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–43
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2590.82 5857.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0384 738.16 20.46 11.977

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3301 738.16 20.46 5.624

TEGV 0.0000 0.2055 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.29 15.39 16.870

FanDuct 0.0000 0.4705 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 846.11 46.85 32.569

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.29 15.39 16.870

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 944.78 71.20 47.484

Splitter 7.1404 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.29 15.39 16.870

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8937.6 2322.9 3952.9 WB17Y Bleed> 0.3000 1.0000 1.0000 12.0932 528.40 -30.27 8.235

LP_Shaft 1970.5 4674.1 1753.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2219 944.78 71.20 46.390

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8192 944.78 71.20 26.706

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.78 71.20 47.484

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.78 71.20 47.484

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.78 71.20 47.484

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 494.24 -13.19 7.056

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 494.24 -13.19 7.056

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 494.24 -13.19 7.056

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 494.24 -13.19 7.056

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1704.49 0.9995 0.0230 0.23452 0.01132 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.296 434.5 384.3

Byp_Nozz 1.332 0.9800 1.0000 0.9800 2006.86 0.653 670.9 6227.5

NASA/TM—2013-218094 K–44
************************************************************************************************************************************ 

Date:04/04/13 Time:08:35:59 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 50/ 78/ 2/47 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 495.90 Stator 1 exit: 498.91 Stator 2 inlet: 501.78 Stator 2 exit: 502.62 

 Stator 3 inlet: 506.05 Stator 3 exit: 506.45 Stator 4 inlet: 509.77 Stator 4 exit: 509.86 

 Stator 5 inlet: 511.80 Stator 5 exit: 511.68 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.94 

Fan Bypass Relative Humidity 5.03 

LPC Inlet Relative Humidity 5.11 

LPC Exit Relative Humidity 2.66 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 523.25 Fan/LPC Inlet Flow Velocity 202.76 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 474.18 Fan/LPC Inlet Static Temperature 493.56 

Additional Water at LPC Exit 0.0045473 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 27.00 363.33 826.2 1.1307 934.23 6.3335 523.25 6.383 0.889 10.000 1733.9 1634.6 1162.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.33 7.943 496.98 -13.65 0.0000 658.00 6.740 474.18 2606.8 0.4900 1.40045 0.0003932 363.18 0.143 0.0004

FS1 Inlet.Fl_O 363.33 7.943 496.98 -13.65 0.0000 658.00 7.525 489.36 4168.2 0.2788 1.40045 0.0003932 363.18 0.143 0.0004

FS12 Splitter.Fl_02 313.78 7.939 496.98 -13.65 0.0000 568.56 7.504 489.03 3531.8 0.2849 1.40045 0.0003932 313.66 0.123 0.0004

FS2 Splitter.Fl_01 49.54 7.939 496.98 -13.65 0.0000 89.77 7.750 493.56 830.5 0.1861 1.40045 0.0003932 49.52 0.019 0.0004

FS14 Fan.Fl_O 313.78 8.506 507.91 -11.03 0.0000 536.50 7.708 493.81 2606.7 0.3777 1.40032 0.0003932 313.66 0.123 0.0004

FS23 LPC.Fl_O 49.54 9.112 525.37 -6.84 0.0000 80.42 8.356 512.52 412.6 0.3540 1.40009 0.0003932 49.52 0.019 0.0004

FS24 VaporIN.Fl_O 49.77 9.112 531.61 -31.45 0.0000 81.26 8.336 518.26 412.6 0.3591 1.39937 0.0049405 49.52 0.245 0.0049

FS25 Bleed2.Fl_O 29.86 9.112 531.61 -31.45 0.0000 48.76 8.850 527.20 412.6 0.2047 1.39937 0.0049405 29.71 0.147 0.0049

FS3 HPC.Fl_O 28.41 50.698 941.92 68.58 0.0000 11.10 44.934 910.89 49.7 0.4209 1.38344 0.0049405 28.27 0.140 0.0049

FS36 Bleed3.Fl_O 22.02 50.698 941.92 68.58 0.0000 8.60 47.376 924.38 49.3 0.3143 1.38344 0.0049405 21.91 0.108 0.0049

FS4 Burner.Fl_O 22.28 49.530 1733.93 55.53 0.0118 12.09 46.760 1709.31 74.6 0.2952 1.32947 0.0049405 21.91 0.108 0.0192

FS45 HPT.Fl_O 29.77 13.458 1167.13 -40.93 0.0088 48.77 12.472 1143.66 265.4 0.3357 1.36325 0.0049405 29.37 0.145 0.0156

FS49 LPT.Fl_O 30.12 7.042 1011.85 -78.73 0.0087 87.79 6.892 1005.95 860.2 0.1773 1.37333 0.0049405 29.71 0.147 0.0155

FS5 TEGV.Fl_O 30.12 7.042 1011.92 -78.73 0.0087 87.80 6.892 1006.02 860.2 0.1773 1.37333 0.0049405 29.71 0.147 0.0155

FS8 Core_Nozz.Fl_O 30.12 7.042 1011.99 -78.73 0.0087 87.80 6.740 999.99 613.5 0.2534 1.37332 0.0049405 29.71 0.147 0.0155

FS17 FanDuctLkg.Fl_O 313.78 8.506 507.91 -11.03 0.0000 536.50 7.708 493.81 2606.7 0.3777 1.40032 0.0003932 313.66 0.123 0.0004

FS171 Bleed15.Fl_O 333.69 8.506 509.33 -12.25 0.0000 571.33 7.474 490.84 2481.9 0.4338 1.40026 0.0006634 333.47 0.221 0.0007

FS172 FanDuct.Fl_O 333.69 8.506 509.33 -12.25 0.0000 571.33 7.474 490.84 2481.9 0.4338 1.40026 0.0006634 333.47 0.221 0.0007

FS173 Byp_Nozz.Fl_O 333.69 8.506 509.33 -12.25 0.0000 571.33 6.740 476.55 2006.9 0.5861 1.40026 0.0006634 333.47 0.221 0.0007

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 568.56 1.071 0.9051 1842.251 1.0220 0.9060 -1163.4 -1872.26 46.44

LPC 89.77 1.148 0.7035 1842.251 1.0571 0.7092 -477.4 7.00 2.16

HPC 48.76 5.564 0.8084 8787.280 1.7718 0.8475 -4123.4 61.55 57.62

HPT 12.09 3.680 0.8770 213.643 1.3284 0.8571 4123.4 

LPT 48.77 1.911 0.8165 52.785 1.1502 0.8025 1640.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 660.61 1.070 0.9069 1824.685 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 46.84 1.245 0.7556 0.487 0.0000 1.9166 0.6021 0.9310 0.0003

HPC 44.34 5.349 0.8167 8553.017 11.0349 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.606 0.8770 1.284 3.6060 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.685 0.8226 0.594 1.6852 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–45
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2606.80 5908.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0989 738.29 18.57 13.458

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3494 738.29 18.57 7.042

TEGV 0.0000 0.1773 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.72 13.56 18.261

FanDuct 0.0000 0.4338 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 844.67 44.57 34.895

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.72 13.56 18.261

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 941.92 68.58 50.698

Splitter 6.3335 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.72 13.56 18.261

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8896.2 2434.4 4123.4 WB17Y Bleed> 0.4000 1.0000 1.0000 19.9076 531.61 -31.45 9.112

LP_Shaft 1803.3 4778.5 1640.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4096 941.92 68.58 49.530

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9835 941.92 68.58 28.897

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.92 68.58 50.698

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.92 68.58 50.698

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.92 68.58 50.698

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 507.91 -11.03 8.506

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 507.91 -11.03 8.506

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 507.91 -11.03 8.506

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 507.91 -11.03 8.506

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1733.87 0.9995 0.0230 0.25951 0.01184 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.045 0.9801 1.0000 0.9800 613.40 0.253 382.0 357.6

Byp_Nozz 1.262 0.9800 1.0000 0.9800 2006.86 0.586 614.9 6377.5

NASA/TM—2013-218094 K–46
************************************************************************************************************************************ 

Date:04/04/13 Time:08:36:38 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 43/ 71/ 2/40 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 509.88 Stator 1 exit: 512.25 Stator 2 inlet: 514.65 Stator 2 exit: 515.45 

 Stator 3 inlet: 518.24 Stator 3 exit: 518.72 Stator 4 inlet: 521.40 Stator 4 exit: 521.64 

 Stator 5 inlet: 523.34 Stator 5 exit: 523.42 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.60 

Fan Bypass Relative Humidity 6.07 

LPC Inlet Relative Humidity 5.78 

LPC Exit Relative Humidity 3.42 

HPC Relative Humidity 0.14 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 484.46 Fan/LPC Inlet Flow Velocity 170.01 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.18 

Ambient Static Temperature 490.63 Fan/LPC Inlet Static Temperature 507.76 

Additional Water at LPC Exit 0.0069693 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 27.00 380.80 629.6 1.3999 881.42 6.9588 484.46 5.188 0.900 10.000 1688.0 1590.7 1156.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 380.80 9.342 510.16 -11.98 0.0000 594.11 8.149 490.63 2525.7 0.4460 1.40025 0.0006510 380.55 0.248 0.0007

FS1 Inlet.Fl_O 380.80 9.342 510.16 -11.98 0.0000 594.11 8.946 503.89 4168.2 0.2495 1.40025 0.0006510 380.55 0.248 0.0007

FS12 Splitter.Fl_02 332.95 9.337 510.16 -11.98 0.0000 519.72 8.914 503.44 3531.8 0.2583 1.40025 0.0006510 332.74 0.217 0.0007

FS2 Splitter.Fl_01 47.85 9.337 510.16 -11.98 0.0000 74.69 9.184 507.76 830.5 0.1539 1.40025 0.0006510 47.82 0.031 0.0007

FS14 Fan.Fl_O 332.95 9.802 518.13 -10.07 0.0000 498.93 9.020 505.96 2606.7 0.3467 1.40015 0.0006510 332.74 0.217 0.0007

FS23 LPC.Fl_O 47.85 10.476 533.17 -6.45 0.0000 68.05 9.871 524.19 412.6 0.2927 1.39994 0.0006510 47.82 0.031 0.0007

FS24 VaporIN.Fl_O 48.18 10.476 542.57 -44.07 0.0000 69.13 9.847 533.09 412.6 0.2987 1.39884 0.0076203 47.82 0.364 0.0076

FS25 Bleed2.Fl_O 28.91 10.476 542.57 -44.07 0.0000 41.48 10.259 539.35 412.6 0.1730 1.39884 0.0076203 28.69 0.219 0.0076

FS3 HPC.Fl_O 27.51 48.463 913.20 46.40 0.0000 11.07 42.980 883.20 49.7 0.4197 1.38470 0.0076203 27.30 0.208 0.0076

FS36 Bleed3.Fl_O 21.32 48.463 913.20 46.40 0.0000 8.58 45.302 896.23 49.3 0.3135 1.38470 0.0076203 21.16 0.161 0.0076

FS4 Burner.Fl_O 21.56 47.347 1688.00 33.93 0.0116 12.07 44.700 1663.96 74.6 0.2949 1.33142 0.0076203 21.16 0.161 0.0215

FS45 HPT.Fl_O 28.81 14.130 1160.80 -53.16 0.0086 44.83 13.266 1141.41 265.4 0.3054 1.36341 0.0076203 28.35 0.216 0.0180

FS49 LPT.Fl_O 29.15 8.389 1035.70 -83.41 0.0085 72.17 8.269 1031.67 860.2 0.1451 1.37157 0.0076203 28.69 0.219 0.0179

FS5 TEGV.Fl_O 29.15 8.389 1035.77 -83.41 0.0085 72.17 8.269 1031.74 860.2 0.1451 1.37156 0.0076203 28.69 0.219 0.0179

FS8 Core_Nozz.Fl_O 29.15 8.389 1035.85 -83.41 0.0085 72.17 8.149 1027.74 613.4 0.2060 1.37156 0.0076203 28.69 0.219 0.0179

FS17 FanDuctLkg.Fl_O 332.95 9.802 518.13 -10.07 0.0000 498.93 9.020 505.96 2606.7 0.3467 1.40015 0.0006510 332.74 0.217 0.0007

FS171 Bleed15.Fl_O 352.23 9.802 519.47 -11.93 0.0000 528.49 8.809 503.85 2481.9 0.3937 1.40008 0.0010299 351.86 0.362 0.0010

FS172 FanDuct.Fl_O 352.23 9.802 519.47 -11.93 0.0000 528.49 8.809 503.85 2481.9 0.3937 1.40008 0.0010299 351.86 0.362 0.0010

FS173 Byp_Nozz.Fl_O 352.23 9.802 519.47 -11.93 0.0000 528.49 8.149 492.76 2006.9 0.5204 1.40008 0.0010299 351.86 0.362 0.0010

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 519.72 1.050 0.8960 1600.228 1.0156 0.8967 -899.9 -1532.72 44.75

LPC 74.69 1.122 0.7411 1600.228 1.0451 0.7453 -373.9 8.33 1.96

HPC 41.48 4.626 0.7926 8512.931 1.6831 0.8310 -3610.6 69.77 64.34

HPT 12.07 3.351 0.8685 211.922 1.2991 0.8491 3610.6 

LPT 44.83 1.684 0.8032 46.582 1.1172 0.7913 1273.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 603.87 1.049 0.8978 1584.970 0.0441 0.8607 1.0235 0.9980 0.9905

LPC 39.39 1.182 0.7477 0.423 0.0000 1.8959 0.6712 0.9912 0.0003

HPC 37.72 4.455 0.8008 8285.982 10.6913 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.286 0.8685 1.274 3.2856 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.515 0.8091 0.524 1.5147 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–47
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2525.74 5733.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0638 729.10 1.17 14.130

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3382 729.10 1.17 8.389

TEGV 0.0000 0.1451 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 710.53 -3.36 18.833

FanDuct 0.0000 0.3937 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 825.22 24.69 34.028

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 710.53 -3.36 18.833

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 913.20 46.40 48.463

Splitter 6.9588 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 710.53 -3.36 18.833

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8706.9 2177.9 3610.6 WB17Y Bleed> 0.4000 1.0000 1.0000 19.2718 542.57 -44.07 10.476

LP_Shaft 1587.1 4214.9 1273.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3007 913.20 46.40 47.347

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8882 913.20 46.40 28.347

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 913.20 46.40 48.463

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 913.20 46.40 48.463

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 913.20 46.40 48.463

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 518.13 -10.07 9.802

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 518.13 -10.07 9.802

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 518.13 -10.07 9.802

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 518.13 -10.07 9.802

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1687.94 0.9995 0.0230 0.24484 0.01157 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.029 0.9801 1.0000 0.9800 613.40 0.206 314.8 285.2

Byp_Nozz 1.203 0.9800 1.0000 0.9800 2006.86 0.520 555.2 6078.3

NASA/TM—2013-218094 K–48
 5μm, 4g/m3

, ISA +27R

************************************************************************************************************************************ 

Date:04/04/13 Time:08:19:37 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.84 Stator 1 exit: 481.57 Stator 2 inlet: 491.27 Stator 2 exit: 496.29 

 Stator 3 inlet: 506.22 Stator 3 exit: 510.77 Stator 4 inlet: 519.97 Stator 4 exit: 523.76 

 Stator 5 inlet: 531.28 Stator 5 exit: 534.66 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.87 

Fan Bypass Relative Humidity 1.30 

LPC Inlet Relative Humidity 1.21 

LPC Exit Relative Humidity 0.11 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 781.11 Fan/LPC Inlet Flow Velocity 187.19 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 464.91 

Additional Water at LPC Exit 0.0091071 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 27.00 254.97 652.9 1.0891 711.14 8.7511 781.11 9.520 0.736 10.000 1757.5 1663.0 1158.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 254.97 4.267 467.83 -18.66 0.0000 834.05 2.854 416.97 2544.5 0.7800 1.40077 0.0000507 254.96 0.013 0.0001

FS1 Inlet.Fl_O 254.97 4.267 467.83 -18.66 0.0000 834.05 3.891 455.66 4168.2 0.3651 1.40077 0.0000507 254.96 0.013 0.0001

FS12 Splitter.Fl_02 228.82 4.265 467.83 -18.66 0.0000 748.89 3.837 453.89 3531.8 0.3914 1.40077 0.0000507 228.81 0.012 0.0001

FS2 Splitter.Fl_01 26.15 4.265 467.83 -18.66 0.0000 85.58 4.172 464.91 830.5 0.1770 1.40077 0.0000507 26.15 0.001 0.0001

FS14 Fan.Fl_O 228.82 4.830 486.54 -14.18 0.0000 674.37 4.052 462.71 2606.7 0.5070 1.40061 0.0000507 228.81 0.012 0.0001

FS23 LPC.Fl_O 26.15 6.690 545.05 -0.14 0.0000 58.88 6.406 538.33 412.6 0.2498 1.39984 0.0000507 26.15 0.001 0.0001

FS24 VaporIN.Fl_O 26.39 6.690 557.10 -49.28 0.0000 60.07 6.392 549.91 412.6 0.2561 1.39840 0.0091579 26.15 0.239 0.0091

FS25 Bleed2.Fl_O 23.75 6.690 557.10 -49.28 0.0000 54.06 6.451 551.35 412.6 0.2287 1.39840 0.0091579 23.53 0.216 0.0091

FS3 HPC.Fl_O 22.60 40.618 1007.03 61.22 0.0000 11.39 35.694 971.83 49.7 0.4365 1.37886 0.0091579 22.39 0.205 0.0091

FS36 Bleed3.Fl_O 17.51 40.618 1007.03 61.22 0.0000 8.83 37.794 987.27 49.3 0.3248 1.37886 0.0091579 17.35 0.159 0.0091

FS4 Burner.Fl_O 17.71 39.683 1757.48 48.80 0.0114 12.07 37.463 1732.61 74.6 0.2954 1.32807 0.0091579 17.35 0.159 0.0227

FS45 HPT.Fl_O 23.67 9.523 1162.54 -58.29 0.0085 54.68 8.619 1132.03 265.4 0.3846 1.36318 0.0091579 23.26 0.213 0.0193

FS49 LPT.Fl_O 23.95 3.264 910.78 -120.61 0.0084 142.85 3.072 895.67 860.2 0.2981 1.37916 0.0091579 23.53 0.216 0.0192

FS5 TEGV.Fl_O 23.95 3.264 910.85 -120.61 0.0084 142.86 3.072 895.74 860.2 0.2981 1.37916 0.0091579 23.53 0.216 0.0192

FS8 Core_Nozz.Fl_O 23.95 3.264 910.92 -120.61 0.0084 142.86 2.854 877.83 613.5 0.4452 1.37915 0.0091579 23.53 0.216 0.0192

FS17 FanDuctLkg.Fl_O 228.82 4.830 486.54 -14.18 0.0000 674.37 4.052 462.71 2606.7 0.5070 1.40061 0.0000507 228.81 0.012 0.0001

FS171 Bleed15.Fl_O 231.46 4.830 487.35 -14.58 0.0000 682.71 3.918 459.03 2481.9 0.5549 1.40058 0.0001536 231.43 0.036 0.0002

FS172 FanDuct.Fl_O 231.46 4.830 487.35 -14.58 0.0000 682.71 3.918 459.03 2481.9 0.5549 1.40058 0.0001536 231.43 0.036 0.0002

FS173 Byp_Nozz.Fl_O 231.46 4.830 487.35 -14.58 0.0000 682.71 2.854 419.24 2006.8 0.9002 1.40058 0.0001536 231.43 0.036 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 748.89 1.132 0.9062 2583.766 1.0400 0.9078 -1451.6 1508.91 54.61

LPC 85.58 1.569 0.8325 2583.766 1.1650 0.8428 -685.1 7.02 3.84

HPC 54.06 6.071 0.8181 8959.355 1.8076 0.8567 -3622.5 61.75 58.40

HPT 12.07 4.167 0.8772 221.489 1.3636 0.8553 3622.4 

LPT 54.68 2.917 0.8564 71.970 1.2747 0.8369 2136.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 870.14 1.129 0.9080 2559.130 0.0415 0.8607 1.0235 0.9980 0.9905

LPC 74.58 1.529 0.7806 0.682 0.0000 1.1475 1.0754 1.0664 0.0003

HPC 49.16 5.832 0.8266 8720.505 10.9525 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.079 0.8772 1.331 4.0795 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.442 0.8627 0.810 2.4419 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–49
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2544.46 6190.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8739 784.14 5.97 9.523

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2778 784.14 5.97 3.264

TEGV 0.0000 0.2981 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 761.59 0.45 14.155

FanDuct 0.0000 0.5549 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 900.69 34.70 27.726

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 761.59 0.45 14.155

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1007.03 61.22 40.618

Splitter 8.7511 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 761.59 0.45 14.155

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9285.3 2049.0 3622.4 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6386 557.10 -49.28 6.690

LP_Shaft 2453.9 4573.1 2136.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7115 1007.03 61.22 39.683

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3726 1007.03 61.22 22.431

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.03 61.22 40.618

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.03 61.22 40.618

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.03 61.22 40.618

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.54 -14.18 4.830

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.54 -14.18 4.830

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.54 -14.18 4.830

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.54 -14.18 4.830

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1757.42 0.9995 0.0230 0.19754 0.01138 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.144 0.9801 1.0000 0.9800 613.40 0.445 631.1 469.7

Byp_Nozz 1.692 0.9800 1.0000 0.9800 2006.86 0.900 885.9 6373.4

NASA/TM—2013-218094 K–50
************************************************************************************************************************************ 

Date:04/04/13 Time:08:20:03 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 41/ 2/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 467.15 Stator 1 exit: 474.39 Stator 2 inlet: 483.46 Stator 2 exit: 488.14 

 Stator 3 inlet: 497.43 Stator 3 exit: 501.66 Stator 4 inlet: 510.30 Stator 4 exit: 513.86 

 Stator 5 inlet: 520.89 Stator 5 exit: 523.93 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.36 

Fan Bypass Relative Humidity 1.69 

LPC Inlet Relative Humidity 1.54 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 731.04 Fan/LPC Inlet Flow Velocity 180.92 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 458.79 

Additional Water at LPC Exit 0.0079013 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 27.00 248.09 636.9 1.0625 676.68 8.8265 731.04 9.238 0.763 10.000 1727.2 1633.5 1139.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 248.09 4.201 461.52 -20.16 0.0000 818.60 2.947 416.97 2562.0 0.7300 1.40081 0.0000491 248.08 0.012 0.0000

FS1 Inlet.Fl_O 248.09 4.201 461.52 -20.16 0.0000 818.60 3.847 450.02 4168.2 0.3571 1.40081 0.0000491 248.08 0.012 0.0000

FS12 Splitter.Fl_02 222.84 4.199 461.52 -20.16 0.0000 735.66 3.795 448.34 3531.8 0.3830 1.40081 0.0000491 222.83 0.011 0.0000

FS2 Splitter.Fl_01 25.25 4.199 461.52 -20.16 0.0000 83.35 4.113 458.79 830.5 0.1723 1.40081 0.0000491 25.25 0.001 0.0000

FS14 Fan.Fl_O 222.84 4.722 478.92 -15.99 0.0000 666.45 3.984 456.19 2606.7 0.4987 1.40067 0.0000491 222.83 0.011 0.0000

FS23 LPC.Fl_O 25.25 6.446 533.65 -2.87 0.0000 58.38 6.177 527.19 412.6 0.2475 1.40002 0.0000491 25.25 0.001 0.0000

FS24 VaporIN.Fl_O 25.45 6.446 544.30 -45.53 0.0000 59.43 6.166 537.44 412.6 0.2530 1.39877 0.0079504 25.25 0.201 0.0079

FS25 Bleed2.Fl_O 22.90 6.446 544.30 -45.53 0.0000 53.48 6.221 538.81 412.6 0.2260 1.39877 0.0079504 22.72 0.181 0.0079

FS3 HPC.Fl_O 21.79 38.812 982.65 61.85 0.0000 11.36 34.145 948.49 49.7 0.4343 1.38055 0.0079504 21.62 0.172 0.0079

FS36 Bleed3.Fl_O 16.89 38.812 982.65 61.85 0.0000 8.80 36.134 963.45 49.3 0.3233 1.38055 0.0079504 16.76 0.133 0.0079

FS4 Burner.Fl_O 17.08 37.918 1727.24 49.59 0.0112 12.08 35.797 1702.69 74.6 0.2952 1.32976 0.0079504 16.76 0.133 0.0214

FS45 HPT.Fl_O 22.82 9.213 1143.60 -54.44 0.0084 54.05 8.363 1114.34 265.4 0.3789 1.36465 0.0079504 22.46 0.179 0.0180

FS49 LPT.Fl_O 23.09 3.314 906.61 -112.87 0.0083 135.38 3.140 893.24 860.2 0.2807 1.37965 0.0079504 22.72 0.181 0.0179

FS5 TEGV.Fl_O 23.09 3.314 906.68 -112.87 0.0083 135.38 3.140 893.31 860.2 0.2807 1.37965 0.0079504 22.72 0.181 0.0179

FS8 Core_Nozz.Fl_O 23.09 3.314 906.75 -112.87 0.0083 135.39 2.947 877.88 613.4 0.4157 1.37964 0.0079504 22.72 0.181 0.0179

FS17 FanDuctLkg.Fl_O 222.84 4.722 478.92 -15.99 0.0000 666.45 3.984 456.19 2606.7 0.4987 1.40067 0.0000491 222.83 0.011 0.0000

FS171 Bleed15.Fl_O 225.39 4.722 479.66 -16.33 0.0000 674.58 3.858 452.73 2481.9 0.5449 1.40066 0.0001376 225.36 0.031 0.0001

FS172 FanDuct.Fl_O 225.39 4.722 479.66 -16.33 0.0000 674.58 3.858 452.73 2481.9 0.5449 1.40066 0.0001376 225.36 0.031 0.0001

FS173 Byp_Nozz.Fl_O 225.39 4.722 479.66 -16.33 0.0000 674.58 2.947 419.12 2006.9 0.8489 1.40066 0.0001376 225.36 0.031 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 735.66 1.124 0.9053 2518.320 1.0377 0.9069 -1314.7 2024.64 54.51

LPC 83.35 1.535 0.8343 2518.320 1.1563 0.8440 -617.8 6.82 3.38

HPC 53.48 6.021 0.8174 8940.949 1.8054 0.8560 -3394.8 61.61 58.21

HPT 12.08 4.116 0.8758 220.384 1.3607 0.8538 3394.8 

LPT 54.05 2.780 0.8505 70.246 1.2594 0.8312 1932.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 854.77 1.122 0.9072 2494.309 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 71.75 1.500 0.7776 0.665 0.0000 1.1617 1.0709 1.0730 0.0003

HPC 48.64 5.784 0.8259 8702.589 10.9679 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.029 0.8758 1.324 4.0292 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.339 0.8568 0.790 2.3390 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–51
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2562.02 5637.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8428 765.35 8.16 9.213

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2680 765.35 8.16 3.314

TEGV 0.0000 0.2807 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.38 2.79 13.567

FanDuct 0.0000 0.5449 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 878.94 36.08 26.513

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.38 2.79 13.567

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 982.65 61.85 38.812

Splitter 8.8265 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.38 2.79 13.567

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9159.2 1946.7 3394.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5447 544.30 -45.53 6.446

LP_Shaft 2375.5 4272.5 1932.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6150 982.65 61.85 37.918

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2882 982.65 61.85 21.499

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 982.65 61.85 38.812

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 982.65 61.85 38.812

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 982.65 61.85 38.812

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 478.92 -15.99 4.722

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 478.92 -15.99 4.722

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 478.92 -15.99 4.722

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 478.92 -15.99 4.722

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1727.18 0.9995 0.0230 0.18797 0.01122 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.125 0.9801 1.0000 0.9800 613.40 0.416 589.1 422.8

Byp_Nozz 1.602 0.9800 1.0000 0.9800 2006.86 0.849 835.2 5851.1

NASA/TM—2013-218094 K–52
************************************************************************************************************************************ 

Date:04/04/13 Time:08:20:27 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 40/ 2/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.08 Stator 1 exit: 472.13 Stator 2 inlet: 480.96 Stator 2 exit: 485.51 

 Stator 3 inlet: 494.56 Stator 3 exit: 498.67 Stator 4 inlet: 507.09 Stator 4 exit: 510.56 

 Stator 5 inlet: 517.42 Stator 5 exit: 520.37 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.52 

Fan Bypass Relative Humidity 1.83 

LPC Inlet Relative Humidity 1.66 

LPC Exit Relative Humidity 0.16 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 715.01 Fan/LPC Inlet Flow Velocity 178.44 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 456.94 

Additional Water at LPC Exit 0.0073898 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 27.00 254.74 649.5 1.0589 687.73 8.8602 715.01 9.114 0.772 10.000 1715.3 1621.9 1132.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 254.74 4.339 459.59 -20.61 0.0000 812.10 3.088 416.97 2566.2 0.7140 1.40083 0.0000469 254.73 0.012 0.0000

FS1 Inlet.Fl_O 254.74 4.339 459.59 -20.61 0.0000 812.10 3.979 448.34 4168.2 0.3538 1.40083 0.0000469 254.73 0.012 0.0000

FS12 Splitter.Fl_02 228.90 4.337 459.59 -20.61 0.0000 730.10 3.926 446.69 3531.8 0.3796 1.40083 0.0000469 228.89 0.011 0.0000

FS2 Splitter.Fl_01 25.83 4.337 459.59 -20.61 0.0000 82.40 4.250 456.94 830.5 0.1702 1.40083 0.0000469 25.83 0.001 0.0000

FS14 Fan.Fl_O 228.90 4.863 476.49 -16.56 0.0000 663.04 4.112 454.18 2606.7 0.4951 1.40070 0.0000469 228.89 0.011 0.0000

FS23 LPC.Fl_O 25.83 6.599 529.84 -3.77 0.0000 58.15 6.326 523.48 412.6 0.2464 1.40007 0.0000469 25.83 0.001 0.0000

FS24 VaporIN.Fl_O 26.03 6.599 539.86 -43.68 0.0000 59.13 6.315 533.12 412.6 0.2516 1.39891 0.0074367 25.83 0.192 0.0074

FS25 Bleed2.Fl_O 23.42 6.599 539.86 -43.68 0.0000 53.22 6.371 534.47 412.6 0.2247 1.39891 0.0074367 23.25 0.173 0.0074

FS3 HPC.Fl_O 22.29 39.550 973.80 62.51 0.0000 11.35 34.806 939.99 49.7 0.4337 1.38116 0.0074367 22.12 0.165 0.0074

FS36 Bleed3.Fl_O 17.27 39.550 973.80 62.51 0.0000 8.79 36.827 954.80 49.3 0.3229 1.38116 0.0074367 17.15 0.128 0.0074

FS4 Burner.Fl_O 17.46 38.639 1715.31 50.31 0.0111 12.08 36.478 1690.93 74.6 0.2951 1.33044 0.0074367 17.15 0.128 0.0208

FS45 HPT.Fl_O 23.34 9.430 1136.17 -52.56 0.0083 53.84 8.568 1107.34 265.4 0.3769 1.36524 0.0074367 22.98 0.171 0.0174

FS49 LPT.Fl_O 23.61 3.454 904.72 -109.52 0.0082 132.71 3.280 891.94 860.2 0.2745 1.37987 0.0074367 23.25 0.173 0.0173

FS5 TEGV.Fl_O 23.61 3.454 904.79 -109.52 0.0082 132.71 3.280 892.01 860.2 0.2746 1.37987 0.0074367 23.25 0.173 0.0173

FS8 Core_Nozz.Fl_O 23.61 3.454 904.86 -109.52 0.0082 132.72 3.088 877.40 613.4 0.4054 1.37986 0.0074367 23.25 0.173 0.0173

FS17 FanDuctLkg.Fl_O 228.90 4.863 476.49 -16.56 0.0000 663.04 4.112 454.18 2606.7 0.4951 1.40070 0.0000469 228.89 0.011 0.0000

FS171 Bleed15.Fl_O 231.50 4.863 477.21 -16.87 0.0000 671.08 3.986 450.80 2481.9 0.5406 1.40068 0.0001294 231.47 0.030 0.0001

FS172 FanDuct.Fl_O 231.50 4.863 477.21 -16.87 0.0000 671.08 3.986 450.80 2481.9 0.5406 1.40068 0.0001294 231.47 0.030 0.0001

FS173 Byp_Nozz.Fl_O 231.50 4.863 477.21 -16.87 0.0000 671.08 3.088 419.07 2006.9 0.8319 1.40068 0.0001294 231.47 0.030 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 730.10 1.121 0.9050 2491.117 1.0368 0.9065 -1311.6 2362.72 54.45

LPC 82.40 1.522 0.8344 2491.117 1.1528 0.8439 -615.6 6.73 3.31

HPC 53.22 5.993 0.8170 8932.199 1.8038 0.8556 -3433.7 61.65 58.22

HPT 12.08 4.098 0.8752 220.030 1.3596 0.8532 3433.7 

LPT 53.84 2.730 0.8482 69.568 1.2538 0.8291 1927.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 848.31 1.118 0.9068 2467.365 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 70.57 1.488 0.7763 0.658 0.0000 1.1677 1.0698 1.0749 0.0003

HPC 48.40 5.758 0.8254 8694.072 10.9686 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.012 0.8752 1.322 4.0117 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.301 0.8545 0.783 2.3014 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–53
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2566.21 5661.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8620 758.64 9.41 9.430

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2741 758.64 9.41 3.454

TEGV 0.0000 0.2745 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.89 4.10 13.849

FanDuct 0.0000 0.5406 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 871.09 37.02 27.029

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.89 4.10 13.849

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 973.80 62.51 39.550

Splitter 8.8602 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.89 4.10 13.849

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9112.8 1979.0 3433.7 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6026 539.86 -43.68 6.599

LP_Shaft 2345.0 4316.5 1927.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6745 973.80 62.51 38.639

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3402 973.80 62.51 21.932

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 973.80 62.51 39.550

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 973.80 62.51 39.550

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 973.80 62.51 39.550

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 476.49 -16.56 4.863

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 476.49 -16.56 4.863

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 476.49 -16.56 4.863

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 476.49 -16.56 4.863

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1715.26 0.9995 0.0230 0.19104 0.01114 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.405 574.3 421.5

Byp_Nozz 1.575 0.9800 1.0000 0.9800 2006.86 0.832 818.4 5889.0

NASA/TM—2013-218094 K–54
************************************************************************************************************************************ 

Date:04/04/13 Time:08:20:53 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 14/ 42/ 2/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 466.56 Stator 1 exit: 473.17 Stator 2 inlet: 481.42 Stator 2 exit: 485.66 

 Stator 3 inlet: 494.12 Stator 3 exit: 497.93 Stator 4 inlet: 505.80 Stator 4 exit: 509.01 

 Stator 5 inlet: 515.41 Stator 5 exit: 518.13 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.13 

Fan Bypass Relative Humidity 2.35 

LPC Inlet Relative Humidity 2.10 

LPC Exit Relative Humidity 0.24 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 675.10 Fan/LPC Inlet Flow Velocity 172.69 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 423.42 Fan/LPC Inlet Static Temperature 458.93 

Additional Water at LPC Exit 0.0066923 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 27.00 275.93 699.1 1.0513 735.03 8.9426 675.10 8.759 0.795 10.000 1704.2 1611.0 1126.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 275.93 4.831 461.41 -20.25 0.0000 791.69 3.578 423.42 2580.5 0.6690 1.40081 0.0000588 275.91 0.016 0.0001

FS1 Inlet.Fl_O 275.93 4.831 461.41 -20.25 0.0000 791.69 4.452 450.76 4168.2 0.3435 1.40081 0.0000588 275.91 0.016 0.0001

FS12 Splitter.Fl_02 248.18 4.829 461.41 -20.25 0.0000 712.42 4.396 449.18 3531.8 0.3686 1.40081 0.0000588 248.16 0.015 0.0001

FS2 Splitter.Fl_01 27.75 4.829 461.41 -20.25 0.0000 79.67 4.738 458.93 830.5 0.1644 1.40081 0.0000588 27.75 0.002 0.0001

FS14 Fan.Fl_O 248.18 5.372 477.22 -16.46 0.0000 651.27 4.579 455.90 2606.7 0.4830 1.40069 0.0000588 248.16 0.015 0.0001

FS23 LPC.Fl_O 27.75 7.156 527.14 -4.49 0.0000 57.45 6.868 520.97 412.6 0.2432 1.40011 0.0000588 27.75 0.002 0.0001

FS24 VaporIN.Fl_O 27.94 7.156 536.26 -40.65 0.0000 58.34 6.857 529.76 412.6 0.2479 1.39906 0.0067510 27.75 0.187 0.0067

FS25 Bleed2.Fl_O 25.14 7.156 536.26 -40.65 0.0000 52.50 6.916 531.06 412.6 0.2215 1.39906 0.0067510 24.98 0.169 0.0067

FS3 HPC.Fl_O 23.92 42.313 964.23 63.96 0.0000 11.33 37.259 930.86 49.7 0.4326 1.38184 0.0067510 23.76 0.160 0.0067

FS36 Bleed3.Fl_O 18.54 42.313 964.23 63.96 0.0000 8.78 39.411 945.46 49.3 0.3221 1.38184 0.0067510 18.42 0.124 0.0067

FS4 Burner.Fl_O 18.75 41.338 1704.23 51.80 0.0111 12.08 39.026 1679.96 74.6 0.2950 1.33111 0.0067510 18.42 0.124 0.0201

FS45 HPT.Fl_O 25.05 10.200 1130.72 -49.50 0.0083 53.30 9.289 1102.69 265.4 0.3723 1.36572 0.0067510 24.68 0.167 0.0167

FS49 LPT.Fl_O 25.35 3.944 912.34 -103.13 0.0082 125.28 3.768 900.97 860.2 0.2578 1.37954 0.0067510 24.98 0.169 0.0166

FS5 TEGV.Fl_O 25.35 3.944 912.41 -103.13 0.0082 125.28 3.768 901.04 860.2 0.2578 1.37954 0.0067510 24.98 0.169 0.0166

FS8 Core_Nozz.Fl_O 25.35 3.944 912.48 -103.13 0.0082 125.29 3.578 888.34 613.4 0.3780 1.37953 0.0067510 24.98 0.169 0.0166

FS17 FanDuctLkg.Fl_O 248.18 5.372 477.22 -16.46 0.0000 651.27 4.579 455.90 2606.7 0.4830 1.40069 0.0000588 248.16 0.015 0.0001

FS171 Bleed15.Fl_O 250.97 5.372 477.88 -16.73 0.0000 659.06 4.447 452.74 2481.9 0.5264 1.40067 0.0001328 250.94 0.033 0.0001

FS172 FanDuct.Fl_O 250.97 5.372 477.88 -16.73 0.0000 659.06 4.447 452.74 2481.9 0.5264 1.40067 0.0001328 250.94 0.033 0.0001

FS173 Byp_Nozz.Fl_O 250.97 5.372 477.88 -16.73 0.0000 659.06 3.578 425.42 2006.9 0.7843 1.40067 0.0001328 250.94 0.033 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 712.42 1.112 0.9040 2409.995 1.0343 0.9054 -1330.0 4741.63 54.05

LPC 79.67 1.482 0.8361 2409.995 1.1424 0.8449 -618.7 6.46 3.09

HPC 52.50 5.913 0.8156 8908.784 1.7981 0.8543 -3631.2 61.96 58.44

HPT 12.08 4.053 0.8745 219.430 1.3566 0.8525 3631.2 

LPT 53.30 2.586 0.8430 67.599 1.2371 0.8245 1948.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 827.76 1.110 0.9058 2387.016 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 67.06 1.451 0.7725 0.637 0.0000 1.1881 1.0682 1.0823 0.0003

HPC 47.75 5.681 0.8240 8671.282 10.9589 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.968 0.8745 1.319 3.9681 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.193 0.8493 0.760 2.1932 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–55
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2580.55 5789.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9253 751.97 11.65 10.200

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2942 751.97 11.65 3.944

TEGV 0.0000 0.2578 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.52 6.42 14.891

FanDuct 0.0000 0.5264 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 862.89 38.85 28.953

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.52 6.42 14.891

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 964.23 63.96 42.313

Splitter 8.9426 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.52 6.42 14.891

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9058.6 2105.4 3631.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7938 536.26 -40.65 7.156

LP_Shaft 2273.1 4502.7 1948.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8710 964.23 63.96 41.338

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5122 964.23 63.96 23.527

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.23 63.96 42.313

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.23 63.96 42.313

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.23 63.96 42.313

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 477.22 -16.46 5.372

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 477.22 -16.46 5.372

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 477.22 -16.46 5.372

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 477.22 -16.46 5.372

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1704.16 0.9995 0.0230 0.20418 0.01109 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.378 538.6 424.3

Byp_Nozz 1.501 0.9800 1.0000 0.9800 2006.86 0.784 777.5 6064.6

NASA/TM—2013-218094 K–56
************************************************************************************************************************************ 

Date:04/04/13 Time:08:21:22 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 48/ 2/17 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 475.00 Stator 1 exit: 480.71 Stator 2 inlet: 487.75 Stator 2 exit: 491.19 

 Stator 3 inlet: 498.51 Stator 3 exit: 501.53 Stator 4 inlet: 508.37 Stator 4 exit: 510.85 

 Stator 5 inlet: 516.32 Stator 5 exit: 518.38 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.08 

Fan Bypass Relative Humidity 3.22 

LPC Inlet Relative Humidity 2.94 

LPC Exit Relative Humidity 0.50 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 624.43 Fan/LPC Inlet Flow Velocity 174.28 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 438.58 Fan/LPC Inlet Static Temperature 468.55 

Additional Water at LPC Exit 0.0064079 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 27.00 302.02 752.3 1.0607 797.99 8.5056 624.43 8.174 0.828 10.000 1704.0 1610.3 1129.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 302.02 5.595 471.08 -18.23 0.0000 755.99 4.358 438.58 2596.9 0.6080 1.40073 0.0001104 301.98 0.033 0.0001

FS1 Inlet.Fl_O 302.02 5.595 471.08 -18.23 0.0000 755.99 5.199 461.27 4168.2 0.3257 1.40073 0.0001104 301.98 0.033 0.0001

FS12 Splitter.Fl_02 270.24 5.592 471.08 -18.23 0.0000 676.80 5.145 459.98 3531.8 0.3470 1.40073 0.0001104 270.21 0.030 0.0001

FS2 Splitter.Fl_01 31.77 5.592 471.08 -18.23 0.0000 79.57 5.488 468.55 830.5 0.1642 1.40073 0.0001104 31.77 0.004 0.0001

FS14 Fan.Fl_O 270.24 6.147 485.39 -14.80 0.0000 625.01 5.326 465.88 2606.7 0.4571 1.40061 0.0001104 270.21 0.030 0.0001

FS23 LPC.Fl_O 31.77 7.859 527.53 -4.69 0.0000 59.92 7.512 520.78 412.6 0.2545 1.40010 0.0001104 31.77 0.004 0.0001

FS24 VaporIN.Fl_O 31.98 7.859 536.26 -39.32 0.0000 60.80 7.500 529.16 412.6 0.2592 1.39909 0.0065183 31.77 0.207 0.0065

FS25 Bleed2.Fl_O 27.18 7.859 536.26 -39.32 0.0000 51.68 7.603 531.23 412.6 0.2178 1.39909 0.0065183 27.00 0.176 0.0065

FS3 HPC.Fl_O 25.86 45.736 960.38 64.30 0.0000 11.31 40.299 927.30 49.7 0.4314 1.38211 0.0065183 25.69 0.167 0.0065

FS36 Bleed3.Fl_O 20.04 45.736 960.38 64.30 0.0000 8.76 42.613 941.77 49.3 0.3213 1.38211 0.0065183 19.91 0.130 0.0065

FS4 Burner.Fl_O 20.26 44.683 1703.95 52.09 0.0111 12.08 42.184 1679.69 74.6 0.2950 1.33112 0.0065183 19.91 0.130 0.0199

FS45 HPT.Fl_O 27.08 11.182 1133.33 -48.22 0.0083 52.61 10.212 1106.07 265.4 0.3666 1.36556 0.0065183 26.69 0.174 0.0165

FS49 LPT.Fl_O 27.40 4.717 934.15 -97.04 0.0082 114.57 4.543 924.55 860.2 0.2343 1.37825 0.0065183 27.00 0.176 0.0164

FS5 TEGV.Fl_O 27.40 4.717 934.22 -97.04 0.0082 114.57 4.543 924.62 860.2 0.2343 1.37825 0.0065183 27.00 0.176 0.0164

FS8 Core_Nozz.Fl_O 27.40 4.717 934.30 -97.04 0.0082 114.58 4.358 914.21 613.3 0.3405 1.37824 0.0065183 27.00 0.176 0.0164

FS17 FanDuctLkg.Fl_O 270.24 6.147 485.39 -14.80 0.0000 625.01 5.326 465.88 2606.7 0.4571 1.40061 0.0001104 270.21 0.030 0.0001

FS171 Bleed15.Fl_O 275.04 6.147 486.28 -15.22 0.0000 636.69 5.178 462.99 2481.9 0.5011 1.40058 0.0002214 274.98 0.061 0.0002

FS172 FanDuct.Fl_O 275.04 6.147 486.28 -15.22 0.0000 636.69 5.178 462.99 2481.9 0.5011 1.40058 0.0002214 274.98 0.061 0.0002

FS173 Byp_Nozz.Fl_O 275.04 6.147 486.28 -15.22 0.0000 636.69 4.358 440.72 2006.9 0.7182 1.40058 0.0002214 274.98 0.061 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 676.80 1.099 0.9027 2259.122 1.0304 0.9040 -1311.5 -----.-- 52.64

LPC 79.57 1.405 0.8526 2259.122 1.1198 0.8595 -608.5 5.94 2.65

HPC 51.68 5.820 0.8139 8881.892 1.7909 0.8527 -3888.4 62.33 58.71

HPT 12.08 3.996 0.8743 218.786 1.3523 0.8526 3888.3 

LPT 52.61 2.371 0.8345 63.953 1.2107 0.8170 1920.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 786.38 1.097 0.9045 2237.582 0.0417 0.8607 1.0235 0.9980 0.9905

LPC 60.65 1.385 0.7657 0.597 0.0000 1.3120 1.0520 1.1134 0.0003

HPC 47.01 5.593 0.8224 8645.107 10.9472 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.913 0.8743 1.315 3.9128 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.031 0.8407 0.719 2.0309 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–57
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.85 5861.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0002 750.01 12.49 11.182

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3180 750.01 12.49 4.717

TEGV 0.0000 0.2343 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 728.75 7.31 16.192

FanDuct 0.0000 0.5011 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 859.94 39.43 31.343

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 728.75 7.31 16.192

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 960.38 64.30 45.736

Splitter 8.5056 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 728.75 7.31 16.192

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9031.3 2261.3 3888.3 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7964 536.26 -39.32 7.859

LP_Shaft 2153.0 4683.7 1920.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1034 960.38 64.30 44.683

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7155 960.38 64.30 25.520

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 960.38 64.30 45.736

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 960.38 64.30 45.736

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 960.38 64.30 45.736

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 485.39 -14.80 6.147

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 485.39 -14.80 6.147

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 485.39 -14.80 6.147

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 485.39 -14.80 6.147

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1703.89 0.9995 0.0230 0.22166 0.01113 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 491.9 418.9

Byp_Nozz 1.410 0.9800 1.0000 0.9800 2006.86 0.718 724.7 6194.9

NASA/TM—2013-218094 K–58
************************************************************************************************************************************ 

Date:04/04/13 Time:08:21:55 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 27/ 55/ 2/24 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 482.91 Stator 1 exit: 487.10 Stator 2 inlet: 491.89 Stator 2 exit: 493.80 

 Stator 3 inlet: 499.08 Stator 3 exit: 500.58 Stator 4 inlet: 505.62 Stator 4 exit: 506.70 

 Stator 5 inlet: 510.38 Stator 5 exit: 511.15 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.93 

Fan Bypass Relative Humidity 4.05 

LPC Inlet Relative Humidity 3.92 

LPC Exit Relative Humidity 1.24 

HPC Relative Humidity 0.08 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 576.87 Fan/LPC Inlet Flow Velocity 193.48 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 454.14 Fan/LPC Inlet Static Temperature 478.75 

Additional Water at LPC Exit 0.0060058 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 27.00 326.86 763.7 1.1097 847.48 7.1619 576.87 7.295 0.858 10.000 1709.9 1614.2 1137.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 326.86 6.516 481.87 -16.15 0.0000 710.53 5.297 454.14 2592.0 0.5520 1.40063 0.0001988 326.79 0.065 0.0002

FS1 Inlet.Fl_O 326.86 6.516 481.87 -16.15 0.0000 710.53 6.112 473.13 4168.2 0.3036 1.40063 0.0001988 326.79 0.065 0.0002

FS12 Splitter.Fl_02 286.81 6.513 481.87 -16.15 0.0000 623.79 6.077 472.42 3531.8 0.3160 1.40063 0.0001988 286.75 0.057 0.0002

FS2 Splitter.Fl_01 40.05 6.513 481.87 -16.15 0.0000 87.10 6.367 478.75 830.5 0.1803 1.40063 0.0001988 40.04 0.008 0.0002

FS14 Fan.Fl_O 286.81 7.060 494.31 -13.17 0.0000 582.84 6.260 477.60 2606.7 0.4180 1.40050 0.0001988 286.75 0.057 0.0002

FS23 LPC.Fl_O 40.05 8.250 522.54 -6.40 0.0000 71.60 7.719 512.69 412.6 0.3098 1.40016 0.0001988 40.04 0.008 0.0002

FS24 VaporIN.Fl_O 40.29 8.250 530.79 -38.86 0.0000 72.60 7.701 520.45 412.6 0.3154 1.39921 0.0062046 40.04 0.248 0.0062

FS25 Bleed2.Fl_O 28.20 8.250 530.79 -38.86 0.0000 50.82 7.992 525.98 412.6 0.2139 1.39921 0.0062046 28.03 0.174 0.0062

FS3 HPC.Fl_O 26.83 47.534 948.51 63.11 0.0000 11.22 41.989 916.44 49.7 0.4269 1.38286 0.0062046 26.67 0.165 0.0062

FS36 Bleed3.Fl_O 20.80 47.534 948.51 63.11 0.0000 8.69 44.345 930.43 49.3 0.3184 1.38286 0.0062046 20.67 0.128 0.0062

FS4 Burner.Fl_O 21.03 46.440 1709.89 50.63 0.0114 12.08 43.841 1685.56 74.6 0.2951 1.33071 0.0062046 20.67 0.128 0.0199

FS45 HPT.Fl_O 28.11 11.988 1141.82 -47.94 0.0085 51.12 11.012 1116.16 265.4 0.3545 1.36493 0.0062046 27.70 0.172 0.0165

FS49 LPT.Fl_O 28.44 5.625 965.31 -91.07 0.0084 101.36 5.464 957.68 860.2 0.2059 1.37628 0.0062046 28.03 0.174 0.0163

FS5 TEGV.Fl_O 28.44 5.625 965.38 -91.07 0.0084 101.36 5.464 957.75 860.2 0.2059 1.37628 0.0062046 28.03 0.174 0.0163

FS8 Core_Nozz.Fl_O 28.44 5.625 965.46 -91.07 0.0084 101.37 5.297 949.73 613.4 0.2965 1.37627 0.0062046 28.03 0.174 0.0163

FS17 FanDuctLkg.Fl_O 286.81 7.060 494.31 -13.17 0.0000 582.84 6.260 477.60 2606.7 0.4180 1.40050 0.0001988 286.75 0.057 0.0002

FS171 Bleed15.Fl_O 298.90 7.060 495.80 -14.21 0.0000 608.31 6.065 474.72 2481.9 0.4708 1.40045 0.0004403 298.76 0.132 0.0004

FS172 FanDuct.Fl_O 298.90 7.060 495.80 -14.21 0.0000 608.31 6.065 474.72 2481.9 0.4708 1.40045 0.0004403 298.76 0.132 0.0004

FS173 Byp_Nozz.Fl_O 298.90 7.060 495.80 -14.21 0.0000 608.31 5.297 456.68 2006.9 0.6538 1.40045 0.0004403 298.76 0.132 0.0004

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.79 1.084 0.9034 2048.126 1.0258 0.9045 -1210.6 -2798.92 49.86

LPC 87.10 1.267 0.8287 2048.126 1.0844 0.8343 -552.7 6.37 2.41

HPC 50.82 5.762 0.8127 8854.502 1.7870 0.8516 -3969.9 61.61 57.92

HPT 12.08 3.874 0.8754 216.618 1.3435 0.8543 3969.8 

LPT 51.12 2.131 0.8245 58.422 1.1800 0.8086 1763.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.78 1.082 0.9053 2028.597 0.0426 0.8607 1.0235 0.9980 0.9905

LPC 53.59 1.312 0.7608 0.541 0.0000 1.6253 0.8541 1.0892 0.0003

HPC 46.22 5.537 0.8212 8618.447 11.0023 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.794 0.8753 1.302 3.7943 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.851 0.8306 0.657 1.8509 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–59
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2592.02 5860.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0378 741.24 12.13 11.988

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3300 741.24 12.13 5.625

TEGV 0.0000 0.2059 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.31 7.03 16.893

FanDuct 0.0000 0.4708 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 849.54 38.64 32.606

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.31 7.03 16.893

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 948.51 63.11 47.534

Splitter 7.1619 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.31 7.03 16.893

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8957.3 2327.7 3969.8 WB17Y Bleed> 0.3000 1.0000 1.0000 12.0861 530.79 -38.86 8.250

LP_Shaft 1974.1 4691.2 1763.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2200 948.51 63.11 46.440

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8175 948.51 63.11 26.733

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 948.51 63.11 47.534

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 948.51 63.11 47.534

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 948.51 63.11 47.534

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 494.31 -13.17 7.060

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 494.31 -13.17 7.060

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 494.31 -13.17 7.060

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 494.31 -13.17 7.060

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1709.83 0.9995 0.0230 0.23541 0.01139 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.296 436.1 385.5

Byp_Nozz 1.333 0.9800 1.0000 0.9800 2006.86 0.654 671.5 6238.7

NASA/TM—2013-218094 K–60
************************************************************************************************************************************ 

Date:04/04/13 Time:08:22:46 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 56/ 84/ 2/53 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 495.95 Stator 1 exit: 498.98 Stator 2 inlet: 501.87 Stator 2 exit: 502.71 

 Stator 3 inlet: 506.14 Stator 3 exit: 506.54 Stator 4 inlet: 509.85 Stator 4 exit: 509.93 

 Stator 5 inlet: 511.88 Stator 5 exit: 511.80 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.94 

Fan Bypass Relative Humidity 5.02 

LPC Inlet Relative Humidity 5.10 

LPC Exit Relative Humidity 2.65 

HPC Relative Humidity 0.09 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 523.25 Fan/LPC Inlet Flow Velocity 202.42 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 474.18 Fan/LPC Inlet Static Temperature 493.57 

Additional Water at LPC Exit 0.0059479 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 27.00 363.50 836.0 1.1216 937.61 6.3486 523.25 6.390 0.889 10.000 1738.6 1639.1 1165.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.50 7.943 496.98 -13.65 0.0000 658.32 6.740 474.18 2608.1 0.4900 1.40045 0.0003932 363.36 0.143 0.0004

FS1 Inlet.Fl_O 363.50 7.943 496.98 -13.65 0.0000 658.32 7.525 489.36 4168.2 0.2790 1.40045 0.0003932 363.36 0.143 0.0004

FS12 Splitter.Fl_02 314.04 7.939 496.98 -13.65 0.0000 569.02 7.503 489.02 3531.8 0.2852 1.40045 0.0003932 313.92 0.123 0.0004

FS2 Splitter.Fl_01 49.47 7.939 496.98 -13.65 0.0000 89.63 7.750 493.57 830.5 0.1858 1.40045 0.0003932 49.45 0.019 0.0004

FS14 Fan.Fl_O 314.04 8.509 507.97 -11.02 0.0000 536.75 7.710 493.85 2606.7 0.3779 1.40032 0.0003932 313.92 0.123 0.0004

FS23 LPC.Fl_O 49.47 9.126 525.49 -6.81 0.0000 80.18 8.373 512.72 412.6 0.3528 1.40009 0.0003932 49.45 0.019 0.0004

FS24 VaporIN.Fl_O 49.76 9.126 533.61 -38.95 0.0000 81.27 8.347 520.20 412.6 0.3594 1.39915 0.0063412 49.45 0.314 0.0063

FS25 Bleed2.Fl_O 29.86 9.126 533.61 -38.95 0.0000 48.76 8.863 529.18 412.6 0.2048 1.39915 0.0063412 29.67 0.188 0.0063

FS3 HPC.Fl_O 28.41 50.761 945.12 61.50 0.0000 11.10 44.981 913.95 49.7 0.4214 1.38304 0.0063412 28.23 0.179 0.0063

FS36 Bleed3.Fl_O 22.02 50.761 945.12 61.50 0.0000 8.60 47.430 927.51 49.3 0.3146 1.38304 0.0063412 21.88 0.139 0.0063

FS4 Burner.Fl_O 22.28 49.592 1738.58 48.48 0.0119 12.09 46.816 1713.91 74.6 0.2954 1.32901 0.0063412 21.88 0.139 0.0206

FS45 HPT.Fl_O 29.77 13.470 1170.54 -48.41 0.0089 48.79 12.481 1146.97 265.4 0.3361 1.36281 0.0063412 29.32 0.186 0.0170

FS49 LPT.Fl_O 30.12 7.043 1014.66 -86.42 0.0088 87.89 6.893 1008.73 860.2 0.1776 1.37293 0.0063412 29.67 0.188 0.0169

FS5 TEGV.Fl_O 30.12 7.043 1014.73 -86.42 0.0088 87.89 6.893 1008.80 860.2 0.1776 1.37292 0.0063412 29.67 0.188 0.0169

FS8 Core_Nozz.Fl_O 30.12 7.043 1014.80 -86.42 0.0088 87.89 6.740 1002.73 613.4 0.2539 1.37292 0.0063412 29.67 0.188 0.0169

FS17 FanDuctLkg.Fl_O 314.04 8.509 507.97 -11.02 0.0000 536.75 7.710 493.85 2606.7 0.3779 1.40032 0.0003932 313.92 0.123 0.0004

FS171 Bleed15.Fl_O 333.94 8.509 509.51 -12.68 0.0000 571.63 7.475 490.99 2481.9 0.4341 1.40025 0.0007458 333.69 0.249 0.0007

FS172 FanDuct.Fl_O 333.94 8.509 509.51 -12.68 0.0000 571.63 7.475 490.99 2481.9 0.4341 1.40025 0.0007458 333.69 0.249 0.0007

FS173 Byp_Nozz.Fl_O 333.94 8.509 509.51 -12.68 0.0000 571.63 6.740 476.66 2006.9 0.5866 1.40025 0.0007458 333.69 0.249 0.0007

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 569.02 1.072 0.9053 1845.827 1.0221 0.9062 -1171.0 -1877.59 46.43

LPC 89.63 1.149 0.7084 1845.827 1.0574 0.7142 -478.5 6.98 2.18

HPC 48.76 5.562 0.8084 8787.568 1.7712 0.8475 -4140.5 61.62 57.69 

HPT 12.09 3.682 0.8773 213.766 1.3282 0.8574 4140.5 

LPT 48.79 1.912 0.8170 52.811 1.1503 0.8031 1649.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 661.15 1.070 0.9071 1828.227 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 46.95 1.246 0.7557 0.488 0.0000 1.9091 0.6068 0.9375 0.0003

HPC 44.35 5.347 0.8167 8553.298 11.0305 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.607 0.8773 1.285 3.6072 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.686 0.8231 0.594 1.6863 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–61
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2608.07 5911.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0987 740.91 11.27 13.470

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3493 740.91 11.27 7.043

TEGV 0.0000 0.1776 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.29 6.25 18.286

FanDuct 0.0000 0.4341 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 847.60 37.39 34.940

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.29 6.25 18.286

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 945.12 61.50 50.761

Splitter 6.3486 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.29 6.25 18.286

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8913.3 2439.8 4140.5 WB17Y Bleed> 0.4000 1.0000 1.0000 19.9039 533.61 -38.95 9.126

LP_Shaft 1806.8 4794.8 1649.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4089 945.12 61.50 49.592

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9829 945.12 61.50 28.930

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 945.12 61.50 50.761

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 945.12 61.50 50.761

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 945.12 61.50 50.761

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 507.97 -11.02 8.509

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 507.97 -11.02 8.509

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 507.97 -11.02 8.509

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 507.97 -11.02 8.509

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1738.53 0.9995 0.0230 0.26045 0.01190 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.045 0.9801 1.0000 0.9800 613.40 0.254 383.3 358.8

Byp_Nozz 1.262 0.9800 1.0000 0.9800 2006.86 0.587 615.5 6388.9

NASA/TM—2013-218094 K–62
************************************************************************************************************************************ 

Date:04/04/13 Time:08:23:20 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 39/ 67/ 2/36 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 509.87 Stator 1 exit: 512.21 Stator 2 inlet: 514.69 Stator 2 exit: 515.51 

 Stator 3 inlet: 518.33 Stator 3 exit: 518.84 Stator 4 inlet: 521.54 Stator 4 exit: 521.80 

 Stator 5 inlet: 523.52 Stator 5 exit: 523.62 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.61 

Fan Bypass Relative Humidity 6.06 

LPC Inlet Relative Humidity 5.77 

LPC Exit Relative Humidity 3.40 

HPC Relative Humidity 0.18 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 484.46 Fan/LPC Inlet Flow Velocity 169.47 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.19 

Ambient Static Temperature 490.63 Fan/LPC Inlet Static Temperature 507.77 

Additional Water at LPC Exit 0.0097470 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 27.00 381.14 646.0 1.3738 887.55 6.9906 484.46 5.200 0.900 10.000 1696.9 1599.2 1162.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 381.14 9.342 510.16 -11.98 0.0000 594.65 8.149 490.63 2528.0 0.4460 1.40025 0.0006510 380.90 0.248 0.0007

FS1 Inlet.Fl_O 381.14 9.342 510.16 -11.98 0.0000 594.65 8.945 503.87 4168.2 0.2497 1.40025 0.0006510 380.90 0.248 0.0007

FS12 Splitter.Fl_02 333.45 9.337 510.16 -11.98 0.0000 520.49 8.913 503.42 3531.8 0.2587 1.40025 0.0006510 333.23 0.217 0.0007

FS2 Splitter.Fl_01 47.70 9.337 510.16 -11.98 0.0000 74.46 9.185 507.77 830.5 0.1534 1.40025 0.0006510 47.67 0.031 0.0007

FS14 Fan.Fl_O 333.45 9.808 518.21 -10.05 0.0000 499.41 9.023 506.01 2606.7 0.3471 1.40015 0.0006510 333.23 0.217 0.0007

FS23 LPC.Fl_O 47.70 10.496 533.38 -6.40 0.0000 67.73 9.896 524.49 412.6 0.2912 1.39994 0.0006510 47.67 0.031 0.0007

FS24 VaporIN.Fl_O 48.16 10.496 546.45 -58.87 0.0000 69.22 9.863 536.86 412.6 0.2995 1.39841 0.0103980 47.67 0.496 0.0103

FS25 Bleed2.Fl_O 28.90 10.496 546.45 -58.87 0.0000 41.53 10.278 543.19 412.6 0.1735 1.39841 0.0103980 28.60 0.297 0.0103

FS3 HPC.Fl_O 27.50 48.582 919.37 32.42 0.0000 11.07 43.068 889.10 49.7 0.4205 1.38392 0.0103980 27.21 0.283 0.0103

FS36 Bleed3.Fl_O 21.31 48.582 919.37 32.42 0.0000 8.58 45.404 902.26 49.3 0.3140 1.38392 0.0103980 21.09 0.219 0.0103

FS4 Burner.Fl_O 21.56 47.463 1696.85 20.01 0.0117 12.07 44.806 1672.69 74.6 0.2952 1.33051 0.0103980 21.09 0.219 0.0243

FS45 HPT.Fl_O 28.81 14.150 1167.22 -67.91 0.0087 44.88 13.281 1147.67 265.4 0.3062 1.36255 0.0103980 28.27 0.294 0.0208

FS49 LPT.Fl_O 29.14 8.390 1041.21 -98.48 0.0086 72.33 8.270 1037.13 860.2 0.1455 1.37077 0.0103980 28.60 0.297 0.0207

FS5 TEGV.Fl_O 29.14 8.390 1041.28 -98.48 0.0086 72.33 8.270 1037.20 860.2 0.1455 1.37077 0.0103980 28.60 0.297 0.0207

FS8 Core_Nozz.Fl_O 29.14 8.390 1041.35 -98.48 0.0086 72.33 8.149 1033.16 613.4 0.2067 1.37076 0.0103980 28.60 0.297 0.0207

FS17 FanDuctLkg.Fl_O 333.45 9.808 518.21 -10.05 0.0000 499.41 9.023 506.01 2606.7 0.3471 1.40015 0.0006510 333.23 0.217 0.0007

FS171 Bleed15.Fl_O 352.71 9.808 519.77 -12.71 0.0000 529.06 8.811 504.09 2481.9 0.3942 1.40006 0.0011786 352.30 0.415 0.0012

FS172 FanDuct.Fl_O 352.71 9.808 519.77 -12.71 0.0000 529.06 8.811 504.09 2481.9 0.3942 1.40006 0.0011786 352.30 0.415 0.0012

FS173 Byp_Nozz.Fl_O 352.71 9.808 519.77 -12.71 0.0000 529.06 8.149 492.96 2006.9 0.5212 1.40006 0.0011786 352.30 0.415 0.0012

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 520.49 1.050 0.8972 1605.437 1.0158 0.8979 -911.0 -1529.28 44.74

LPC 74.46 1.124 0.7470 1605.437 1.0455 0.7512 -376.0 8.29 1.96

HPC 41.53 4.629 0.7926 8515.007 1.6824 0.8310 -3641.8 69.87 64.45

HPT 12.07 3.354 0.8692 212.174 1.2991 0.8499 3641.8 

LPT 44.88 1.686 0.8042 46.604 1.1175 0.7923 1287.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 604.76 1.049 0.8990 1590.130 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 39.55 1.183 0.7479 0.424 0.0000 1.8825 0.6780 0.9989 0.0003

HPC 37.77 4.458 0.8008 8288.003 10.6846 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.289 0.8692 1.275 3.2891 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.516 0.8102 0.524 1.5163 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–63
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2528.02 5739.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0634 734.17 -13.23 14.150

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3381 734.17 -13.23 8.390

TEGV 0.0000 0.1455 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 715.48 -17.79 18.875

FanDuct 0.0000 0.3942 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 830.87 10.51 34.109

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 715.48 -17.79 18.875

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 919.37 32.42 48.582

Splitter 6.9906 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 715.48 -17.79 18.875

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8740.1 2188.4 3641.8 WB17Y Bleed> 0.4000 1.0000 1.0000 19.2654 546.45 -58.87 10.496

LP_Shaft 1592.2 4245.4 1287.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2996 919.37 32.42 47.463

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8872 919.37 32.42 28.408

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 919.37 32.42 48.582

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 919.37 32.42 48.582

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 919.37 32.42 48.582

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 518.21 -10.05 9.808

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 518.21 -10.05 9.808

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 518.21 -10.05 9.808

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 518.21 -10.05 9.808

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1696.79 0.9995 0.0230 0.24654 0.01169 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.030 0.9801 1.0000 0.9800 613.40 0.207 316.9 287.1

Byp_Nozz 1.204 0.9800 1.0000 0.9800 2006.86 0.521 556.3 6098.1

NASA/TM—2013-218094 K–64
 5μm, 2g/m3

, ISA +36R

************************************************************************************************************************************ 

Date:05/10/13 Time:11:40:17 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 40/ 2/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.08 Stator 1 exit: 492.01 Stator 2 inlet: 501.96 Stator 2 exit: 507.10 

 Stator 3 inlet: 517.28 Stator 3 exit: 521.94 Stator 4 inlet: 531.38 Stator 4 exit: 535.30 

 Stator 5 inlet: 543.07 Stator 5 exit: 546.53 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.98 

Fan Bypass Relative Humidity 1.39 

LPC Inlet Relative Humidity 1.30 

LPC Exit Relative Humidity 0.12 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 189.51 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 474.93 

Additional Water at LPC Exit 0.0095376 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 252.43 657.7 1.0947 719.97 8.7419 789.49 9.531 0.736 10.000 1791.0 1695.1 1181.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.43 4.267 477.92 -16.44 0.0000 834.59 2.854 425.97 2546.2 0.7800 1.40068 0.0000851 252.41 0.021 0.0001

FS1 Inlet.Fl_O 252.43 4.267 477.92 -16.44 0.0000 834.59 3.891 465.47 4168.2 0.3654 1.40068 0.0000851 252.41 0.021 0.0001

FS12 Splitter.Fl_02 226.52 4.265 477.92 -16.44 0.0000 749.30 3.836 463.67 3531.8 0.3917 1.40068 0.0000851 226.50 0.019 0.0001

FS2 Splitter.Fl_01 25.91 4.265 477.92 -16.44 0.0000 85.71 4.172 474.93 830.5 0.1773 1.40068 0.0000851 25.91 0.002 0.0001

FS14 Fan.Fl_O 226.52 4.832 497.11 -11.84 0.0000 674.40 4.054 472.76 2606.7 0.5071 1.40049 0.0000851 226.50 0.019 0.0001

FS23 LPC.Fl_O 25.91 6.699 557.07 2.55 0.0000 58.91 6.415 550.20 412.6 0.2499 1.39964 0.0000851 25.91 0.002 0.0001

FS24 VaporIN.Fl_O 26.16 6.699 569.47 -48.91 0.0000 60.13 6.400 562.11 412.6 0.2565 1.39811 0.0096227 25.91 0.249 0.0095

FS25 Bleed2.Fl_O 23.54 6.699 569.47 -48.91 0.0000 54.11 6.459 563.58 412.6 0.2290 1.39811 0.0096227 23.32 0.224 0.0095

FS3 HPC.Fl_O 22.40 40.666 1028.50 64.03 0.0000 11.40 35.725 992.56 49.7 0.4372 1.37745 0.0096227 22.19 0.214 0.0095

FS36 Bleed3.Fl_O 17.36 40.666 1028.50 64.03 0.0000 8.83 37.833 1008.33 49.3 0.3252 1.37745 0.0096227 17.20 0.165 0.0095

FS4 Burner.Fl_O 17.56 39.729 1791.04 51.33 0.0116 12.07 37.506 1765.80 74.6 0.2956 1.32633 0.0096227 17.20 0.165 0.0235

FS45 HPT.Fl_O 23.47 9.537 1185.91 -58.12 0.0087 54.68 8.632 1154.87 265.4 0.3849 1.36150 0.0096227 23.05 0.222 0.0200

FS49 LPT.Fl_O 23.74 3.266 928.81 -121.97 0.0086 142.98 3.073 913.40 860.2 0.2986 1.37791 0.0096227 23.32 0.224 0.0199

FS5 TEGV.Fl_O 23.74 3.266 928.88 -121.97 0.0086 142.99 3.073 913.47 860.2 0.2986 1.37790 0.0096227 23.32 0.224 0.0199

FS8 Core_Nozz.Fl_O 23.74 3.266 928.95 -121.97 0.0086 142.99 2.854 895.18 613.4 0.4461 1.37790 0.0096227 23.32 0.224 0.0199

FS17 FanDuctLkg.Fl_O 226.52 4.832 497.11 -11.84 0.0000 674.40 4.054 472.76 2606.7 0.5071 1.40049 0.0000851 226.50 0.019 0.0001

FS171 Bleed15.Fl_O 229.13 4.832 497.95 -12.26 0.0000 682.76 3.920 469.01 2481.9 0.5550 1.40046 0.0001929 229.09 0.044 0.0002

FS172 FanDuct.Fl_O 229.13 4.832 497.95 -12.26 0.0000 682.76 3.920 469.01 2481.9 0.5550 1.40046 0.0001929 229.09 0.044 0.0002

FS173 Byp_Nozz.Fl_O 229.13 4.832 497.95 -12.26 0.0000 682.76 2.854 428.30 2006.9 0.9008 1.40046 0.0001929 229.09 0.044 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 749.30 1.133 0.9063 2587.056 1.0402 0.9080 -1474.6 1489.03 54.55

LPC 85.71 1.571 0.8321 2587.056 1.1656 0.8425 -696.0 7.03 3.87

HPC 54.11 6.070 0.8181 8961.021 1.8061 0.8566 -3670.8 61.93 58.58

HPT 12.07 4.166 0.8788 221.867 1.3628 0.8572 3670.8 

LPT 54.68 2.920 0.8588 72.113 1.2751 0.8396 2170.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 870.61 1.130 0.9081 2562.389 0.0415 0.8607 1.0235 0.9980 0.9905

LPC 74.72 1.530 0.7808 0.683 0.0000 1.1471 1.0764 1.0658 0.0003

HPC 49.22 5.831 0.8265 8722.126 10.9409 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.078 0.8788 1.333 4.0783 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.444 0.8652 0.811 2.4443 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–65
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2546.18 6194.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8664 801.23 7.56 9.537

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2755 801.23 7.56 3.266

TEGV 0.0000 0.2986 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 778.22 1.91 14.172

FanDuct 0.0000 0.5550 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 920.10 36.92 27.758

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 778.22 1.91 14.172

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1028.50 64.03 40.666

Splitter 8.7419 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 778.22 1.91 14.172

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9389.6 2053.3 3670.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6159 569.47 -48.91 6.699

LP_Shaft 2483.4 4590.8 2170.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6881 1028.50 64.03 39.729

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3522 1028.50 64.03 22.459

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1028.50 64.03 40.666

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1028.50 64.03 40.666

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1028.50 64.03 40.666

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 497.11 -11.84 4.832

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 497.11 -11.84 4.832

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 497.11 -11.84 4.832

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 497.11 -11.84 4.832

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1790.99 0.9995 0.0230 0.19999 0.01163 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.144 0.9801 1.0000 0.9800 613.40 0.446 638.4 471.1

Byp_Nozz 1.693 0.9800 1.0000 0.9800 2006.86 0.901 896.0 6380.7

NASA/TM—2013-218094 K–66
************************************************************************************************************************************ 

Date:05/10/13 Time:11:40:42 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 477.21 Stator 1 exit: 484.61 Stator 2 inlet: 493.88 Stator 2 exit: 498.66 

 Stator 3 inlet: 508.16 Stator 3 exit: 512.48 Stator 4 inlet: 521.31 Stator 4 exit: 524.94 

 Stator 5 inlet: 532.15 Stator 5 exit: 535.32 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.47 

Fan Bypass Relative Humidity 1.78 

LPC Inlet Relative Humidity 1.63 

LPC Exit Relative Humidity 0.17 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 738.88 Fan/LPC Inlet Flow Velocity 183.43 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 468.67 

Additional Water at LPC Exit 0.0074386 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 36.00 245.58 637.7 1.0723 683.80 8.8021 738.88 9.246 0.764 10.000 1757.5 1662.4 1160.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 245.58 4.201 471.48 -17.97 0.0000 819.02 2.947 425.97 2563.4 0.7300 1.40073 0.0000824 245.56 0.020 0.0001

FS1 Inlet.Fl_O 245.58 4.201 471.48 -17.97 0.0000 819.02 3.846 459.71 4168.2 0.3574 1.40073 0.0000824 245.56 0.020 0.0001

FS12 Splitter.Fl_02 220.53 4.199 471.48 -17.97 0.0000 735.83 3.794 458.00 3531.8 0.3832 1.40073 0.0000824 220.51 0.018 0.0001

FS2 Splitter.Fl_01 25.05 4.199 471.48 -17.97 0.0000 83.60 4.113 468.67 830.5 0.1728 1.40073 0.0000824 25.05 0.002 0.0001

FS14 Fan.Fl_O 220.53 4.723 489.28 -13.70 0.0000 666.47 3.985 466.06 2606.7 0.4987 1.40057 0.0000824 220.51 0.018 0.0001

FS23 LPC.Fl_O 25.05 6.449 545.22 -0.28 0.0000 58.54 6.178 538.59 412.6 0.2482 1.39983 0.0000824 25.05 0.002 0.0001

FS24 VaporIN.Fl_O 25.24 6.449 555.10 -40.48 0.0000 59.50 6.168 548.08 412.6 0.2534 1.39865 0.0075210 25.05 0.188 0.0075

FS25 Bleed2.Fl_O 22.72 6.449 555.10 -40.48 0.0000 53.55 6.223 549.49 412.6 0.2263 1.39865 0.0075210 22.55 0.170 0.0075

FS3 HPC.Fl_O 21.61 38.845 1001.70 69.01 0.0000 11.36 34.168 966.90 49.7 0.4348 1.37944 0.0075210 21.45 0.161 0.0075

FS36 Bleed3.Fl_O 16.75 38.845 1001.70 69.01 0.0000 8.81 36.162 982.15 49.3 0.3236 1.37944 0.0075210 16.63 0.125 0.0075

FS4 Burner.Fl_O 16.94 37.950 1757.46 56.45 0.0114 12.08 35.828 1732.59 74.6 0.2953 1.32829 0.0075210 16.63 0.125 0.0212

FS45 HPT.Fl_O 22.64 9.224 1164.53 -49.60 0.0085 54.05 8.373 1134.82 265.4 0.3790 1.36326 0.0075210 22.28 0.168 0.0178

FS49 LPT.Fl_O 22.91 3.315 922.92 -109.30 0.0084 135.48 3.140 909.31 860.2 0.2810 1.37865 0.0075210 22.55 0.170 0.0176

FS5 TEGV.Fl_O 22.91 3.315 922.99 -109.30 0.0084 135.48 3.140 909.38 860.2 0.2810 1.37864 0.0075210 22.55 0.170 0.0176

FS8 Core_Nozz.Fl_O 22.91 3.315 923.06 -109.30 0.0084 135.49 2.947 893.68 613.4 0.4161 1.37864 0.0075210 22.55 0.170 0.0176

FS17 FanDuctLkg.Fl_O 220.53 4.723 489.28 -13.70 0.0000 666.47 3.985 466.06 2606.7 0.4987 1.40057 0.0000824 220.51 0.018 0.0001

FS171 Bleed15.Fl_O 223.05 4.723 490.03 -14.00 0.0000 674.61 3.859 462.51 2481.9 0.5450 1.40055 0.0001660 223.02 0.037 0.0002

FS172 FanDuct.Fl_O 223.05 4.723 490.03 -14.00 0.0000 674.61 3.859 462.51 2481.9 0.5450 1.40055 0.0001660 223.02 0.037 0.0002

FS173 Byp_Nozz.Fl_O 223.05 4.723 490.03 -14.00 0.0000 674.61 2.947 428.16 2006.9 0.8491 1.40055 0.0001660 223.02 0.037 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 735.83 1.125 0.9054 2519.750 1.0378 0.9070 -1331.8 2009.04 54.49

LPC 83.60 1.536 0.8342 2519.750 1.1564 0.8440 -627.0 6.83 3.39

HPC 53.55 6.023 0.8174 8943.039 1.8045 0.8560 -3433.6 61.71 58.31

HPT 12.08 4.114 0.8773 220.690 1.3601 0.8556 3433.6 

LPT 54.05 2.783 0.8526 70.399 1.2598 0.8336 1958.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 854.97 1.122 0.9073 2495.725 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 71.81 1.500 0.7776 0.666 0.0000 1.1642 1.0708 1.0728 0.0003

HPC 48.71 5.787 0.8259 8704.623 10.9607 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.028 0.8773 1.326 4.0280 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.341 0.8589 0.792 2.3410 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–67
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2563.40 5639.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8360 780.43 14.27 9.224

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2658 780.43 14.27 3.315

TEGV 0.0000 0.2810 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 758.04 8.79 13.576

FanDuct 0.0000 0.5450 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 896.12 42.73 26.535

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 758.04 8.79 13.576

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1001.70 69.01 38.845

Splitter 8.8021 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 758.04 8.79 13.576

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9251.8 1949.2 3433.6 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5240 555.10 -40.48 6.449

LP_Shaft 2402.4 4282.2 1958.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.5938 1001.70 69.01 37.950

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2696 1001.70 69.01 21.519

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1001.70 69.01 38.845

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1001.70 69.01 38.845

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1001.70 69.01 38.845

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 489.28 -13.70 4.723

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 489.28 -13.70 4.723

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 489.28 -13.70 4.723

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 489.28 -13.70 4.723

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1757.40 0.9995 0.0230 0.18994 0.01142 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.125 0.9801 1.0000 0.9800 613.40 0.416 594.7 423.4

Byp_Nozz 1.603 0.9800 1.0000 0.9800 2006.86 0.849 844.4 5854.1

NASA/TM—2013-218094 K–68
************************************************************************************************************************************ 

Date:05/10/13 Time:11:41:06 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 475.09 Stator 1 exit: 482.29 Stator 2 inlet: 491.30 Stator 2 exit: 495.94 

 Stator 3 inlet: 505.19 Stator 3 exit: 509.38 Stator 4 inlet: 517.98 Stator 4 exit: 521.51 

 Stator 5 inlet: 528.52 Stator 5 exit: 531.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.64 

Fan Bypass Relative Humidity 1.93 

LPC Inlet Relative Humidity 1.76 

LPC Exit Relative Humidity 0.19 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 722.68 Fan/LPC Inlet Flow Velocity 180.89 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 466.78 

Additional Water at LPC Exit 0.0066979 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 36.00 252.12 648.4 1.0703 694.02 8.8351 722.68 9.116 0.772 10.000 1744.1 1649.4 1151.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.12 4.339 469.50 -18.42 0.0000 812.38 3.088 425.97 2567.1 0.7140 1.40075 0.0000786 252.10 0.020 0.0001

FS1 Inlet.Fl_O 252.12 4.339 469.50 -18.42 0.0000 812.38 3.979 458.00 4168.2 0.3539 1.40075 0.0000786 252.10 0.020 0.0001

FS12 Splitter.Fl_02 226.48 4.337 469.50 -18.42 0.0000 730.14 3.926 456.33 3531.8 0.3796 1.40075 0.0000786 226.46 0.018 0.0001

FS2 Splitter.Fl_01 25.63 4.337 469.50 -18.42 0.0000 82.64 4.250 466.78 830.5 0.1707 1.40075 0.0000786 25.63 0.002 0.0001

FS14 Fan.Fl_O 226.48 4.863 486.78 -14.28 0.0000 663.03 4.113 463.99 2606.7 0.4951 1.40060 0.0000786 226.46 0.018 0.0001

FS23 LPC.Fl_O 25.63 6.600 541.20 -1.23 0.0000 58.31 6.325 534.67 412.6 0.2471 1.39990 0.0000786 25.63 0.002 0.0001

FS24 VaporIN.Fl_O 25.81 6.600 550.16 -37.44 0.0000 59.18 6.315 543.29 412.6 0.2518 1.39883 0.0067765 25.63 0.174 0.0067

FS25 Bleed2.Fl_O 23.23 6.600 550.16 -37.44 0.0000 53.26 6.372 544.67 412.6 0.2249 1.39883 0.0067765 23.07 0.156 0.0067

FS3 HPC.Fl_O 22.10 39.555 991.90 70.72 0.0000 11.35 34.805 957.49 49.7 0.4341 1.38017 0.0067765 21.95 0.149 0.0067

FS36 Bleed3.Fl_O 17.13 39.555 991.90 70.72 0.0000 8.80 36.829 972.56 49.3 0.3231 1.38017 0.0067765 17.01 0.115 0.0067

FS4 Burner.Fl_O 17.32 38.644 1744.08 58.23 0.0113 12.08 36.484 1719.37 74.6 0.2952 1.32908 0.0067765 17.01 0.115 0.0204

FS45 HPT.Fl_O 23.15 9.436 1156.11 -46.52 0.0085 53.82 8.574 1126.88 265.4 0.3769 1.36395 0.0067765 22.80 0.154 0.0170

FS49 LPT.Fl_O 23.42 3.454 920.40 -104.64 0.0084 132.74 3.280 907.41 860.2 0.2746 1.37894 0.0067765 23.07 0.156 0.0168

FS5 TEGV.Fl_O 23.42 3.454 920.47 -104.64 0.0084 132.74 3.280 907.48 860.2 0.2746 1.37894 0.0067765 23.07 0.156 0.0168

FS8 Core_Nozz.Fl_O 23.42 3.454 920.54 -104.64 0.0084 132.75 3.088 892.64 613.4 0.4056 1.37893 0.0067765 23.07 0.156 0.0168

FS17 FanDuctLkg.Fl_O 226.48 4.863 486.78 -14.28 0.0000 663.03 4.113 463.99 2606.7 0.4951 1.40060 0.0000786 226.46 0.018 0.0001

FS171 Bleed15.Fl_O 229.06 4.863 487.49 -14.54 0.0000 671.08 3.986 460.52 2481.9 0.5407 1.40058 0.0001536 229.03 0.035 0.0002

FS172 FanDuct.Fl_O 229.06 4.863 487.49 -14.54 0.0000 671.08 3.986 460.52 2481.9 0.5407 1.40058 0.0001536 229.03 0.035 0.0002

FS173 Byp_Nozz.Fl_O 229.06 4.863 487.49 -14.54 0.0000 671.08 3.088 428.11 2006.9 0.8319 1.40058 0.0001536 229.03 0.035 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 730.14 1.121 0.9050 2491.498 1.0368 0.9065 -1326.5 2356.98 54.45

LPC 82.64 1.522 0.8352 2491.498 1.1527 0.8447 -623.6 6.73 3.31

HPC 53.26 5.993 0.8169 8933.540 1.8029 0.8556 -3467.9 61.76 58.33

HPT 12.08 4.095 0.8766 220.312 1.3590 0.8548 3467.9 

LPT 53.82 2.732 0.8501 69.716 1.2541 0.8313 1950.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 848.35 1.119 0.9068 2467.742 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 70.59 1.488 0.7763 0.658 0.0000 1.1708 1.0698 1.0758 0.0003

HPC 48.44 5.758 0.8254 8695.377 10.9612 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.010 0.8766 1.324 4.0097 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.303 0.8565 0.784 2.3027 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–69
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2567.14 5662.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8547 772.97 16.64 9.436

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2717 772.97 16.64 3.454

TEGV 0.0000 0.2746 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 750.83 11.23 13.850

FanDuct 0.0000 0.5407 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 887.42 44.76 27.032

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 750.83 11.23 13.850

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 991.90 70.72 39.555

Splitter 8.8351 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 750.83 11.23 13.850

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9200.7 1979.6 3467.9 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5806 550.16 -37.44 6.600

LP_Shaft 2370.5 4320.8 1950.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6519 991.90 70.72 38.644

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3204 991.90 70.72 21.937

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 991.90 70.72 39.555

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 991.90 70.72 39.555

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 991.90 70.72 39.555

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.78 -14.28 4.863

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.78 -14.28 4.863

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.78 -14.28 4.863

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.78 -14.28 4.863

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1744.03 0.9995 0.0230 0.19278 0.01133 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.406 579.2 421.6

Byp_Nozz 1.575 0.9800 1.0000 0.9800 2006.86 0.832 827.3 5889.8

NASA/TM—2013-218094 K–70
************************************************************************************************************************************ 

Date:05/10/13 Time:11:41:22 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.45 Stator 1 exit: 483.18 Stator 2 inlet: 491.59 Stator 2 exit: 495.91 

 Stator 3 inlet: 504.53 Stator 3 exit: 508.41 Stator 4 inlet: 516.43 Stator 4 exit: 519.68 

 Stator 5 inlet: 526.21 Stator 5 exit: 528.99 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.25 

Fan Bypass Relative Humidity 2.46 

LPC Inlet Relative Humidity 2.21 

LPC Exit Relative Humidity 0.27 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 682.24 Fan/LPC Inlet Flow Velocity 174.69 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 432.42 Fan/LPC Inlet Static Temperature 468.67 

Additional Water at LPC Exit 0.0060647 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 36.00 272.97 694.5 1.0652 739.78 8.9302 682.24 8.742 0.795 10.000 1731.5 1637.1 1145.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 272.97 4.831 471.21 -18.12 0.0000 791.49 3.578 432.42 2580.0 0.6690 1.40074 0.0000968 272.95 0.026 0.0001

FS1 Inlet.Fl_O 272.97 4.831 471.21 -18.12 0.0000 791.49 4.452 460.34 4168.2 0.3434 1.40074 0.0000968 272.95 0.026 0.0001

FS12 Splitter.Fl_02 245.48 4.829 471.21 -18.12 0.0000 712.14 4.396 458.73 3531.8 0.3684 1.40074 0.0000968 245.46 0.024 0.0001

FS2 Splitter.Fl_01 27.49 4.829 471.21 -18.12 0.0000 79.75 4.738 468.67 830.5 0.1646 1.40074 0.0000968 27.49 0.003 0.0001

FS14 Fan.Fl_O 245.48 5.370 487.31 -14.26 0.0000 651.17 4.578 465.55 2606.7 0.4830 1.40059 0.0000968 245.46 0.024 0.0001

FS23 LPC.Fl_O 27.49 7.151 538.14 -2.07 0.0000 57.54 6.862 531.82 412.6 0.2437 1.39994 0.0000968 27.49 0.003 0.0001

FS24 VaporIN.Fl_O 27.66 7.151 546.29 -34.87 0.0000 58.33 6.852 539.68 412.6 0.2478 1.39898 0.0061615 27.49 0.169 0.0061

FS25 Bleed2.Fl_O 24.89 7.151 546.29 -34.87 0.0000 52.49 6.911 541.00 412.6 0.2214 1.39898 0.0061615 24.74 0.152 0.0061

FS3 HPC.Fl_O 23.68 42.231 981.50 71.57 0.0000 11.34 37.181 947.55 49.7 0.4330 1.38090 0.0061615 23.54 0.145 0.0061

FS36 Bleed3.Fl_O 18.35 42.231 981.50 71.57 0.0000 8.79 39.332 962.41 49.3 0.3224 1.38090 0.0061615 18.24 0.112 0.0061

FS4 Burner.Fl_O 18.56 41.259 1731.49 59.13 0.0113 12.08 38.953 1706.91 74.6 0.2951 1.32979 0.0061615 18.24 0.112 0.0197

FS45 HPT.Fl_O 24.80 10.189 1149.77 -43.92 0.0084 53.27 9.280 1121.38 265.4 0.3721 1.36448 0.0061615 24.45 0.151 0.0163

FS49 LPT.Fl_O 25.10 3.942 927.84 -98.52 0.0083 125.12 3.767 916.33 860.2 0.2575 1.37862 0.0061615 24.74 0.152 0.0162

FS5 TEGV.Fl_O 25.10 3.942 927.91 -98.52 0.0083 125.12 3.767 916.40 860.2 0.2575 1.37861 0.0061615 24.74 0.152 0.0162

FS8 Core_Nozz.Fl_O 25.10 3.942 927.98 -98.52 0.0083 125.13 3.578 903.56 613.4 0.3774 1.37861 0.0061615 24.74 0.152 0.0162

FS17 FanDuctLkg.Fl_O 245.48 5.370 487.31 -14.26 0.0000 651.17 4.578 465.55 2606.7 0.4830 1.40059 0.0000968 245.46 0.024 0.0001

FS171 Bleed15.Fl_O 248.25 5.370 487.97 -14.49 0.0000 658.95 4.446 462.31 2481.9 0.5263 1.40057 0.0001640 248.21 0.041 0.0002

FS172 FanDuct.Fl_O 248.25 5.370 487.97 -14.49 0.0000 658.95 4.446 462.31 2481.9 0.5263 1.40057 0.0001640 248.21 0.041 0.0002

FS173 Byp_Nozz.Fl_O 248.25 5.370 487.97 -14.49 0.0000 658.95 3.578 434.45 2006.9 0.7840 1.40057 0.0001640 248.21 0.041 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 712.14 1.112 0.9039 2408.079 1.0342 0.9053 -1340.1 4859.75 54.07

LPC 79.75 1.481 0.8367 2408.079 1.1420 0.8455 -624.2 6.45 3.08

HPC 52.49 5.905 0.8155 8908.345 1.7967 0.8542 -3657.4 62.13 58.61

HPT 12.08 4.049 0.8758 219.712 1.3559 0.8540 3657.4 

LPT 53.27 2.584 0.8447 67.690 1.2370 0.8264 1964.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 827.44 1.110 0.9057 2385.118 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 66.97 1.450 0.7724 0.636 0.0000 1.1907 1.0679 1.0833 0.0003

HPC 47.74 5.674 0.8239 8670.855 10.9485 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.965 0.8758 1.320 3.9648 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.192 0.8510 0.761 2.1917 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–71
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2579.98 5788.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9160 765.75 18.35 10.189

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2912 765.75 18.35 3.942

TEGV 0.0000 0.2575 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.93 13.03 14.869

FanDuct 0.0000 0.5263 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 878.52 46.02 28.901

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.93 13.03 14.869

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 981.50 71.57 42.231

Splitter 8.9302 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.93 13.03 14.869

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9142.5 2101.1 3657.4 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7656 546.29 -34.87 7.151

LP_Shaft 2295.3 4494.7 1964.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8420 981.50 71.57 41.259

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4868 981.50 71.57 23.487

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 981.50 71.57 42.231

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 981.50 71.57 42.231

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 981.50 71.57 42.231

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 487.31 -14.26 5.370

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 487.31 -14.26 5.370

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 487.31 -14.26 5.370

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 487.31 -14.26 5.370

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1731.44 0.9995 0.0230 0.20549 0.01126 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.377 542.1 422.9

Byp_Nozz 1.501 0.9800 1.0000 0.9800 2006.86 0.784 785.4 6059.9

NASA/TM—2013-218094 K–72
************************************************************************************************************************************ 

Date:05/10/13 Time:11:41:38 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.73 Stator 1 exit: 490.51 Stator 2 inlet: 497.66 Stator 2 exit: 501.14 

 Stator 3 inlet: 508.56 Stator 3 exit: 511.63 Stator 4 inlet: 518.56 Stator 4 exit: 521.05 

 Stator 5 inlet: 526.62 Stator 5 exit: 528.77 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.19 

Fan Bypass Relative Humidity 3.34 

LPC Inlet Relative Humidity 3.05 

LPC Exit Relative Humidity 0.55 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 630.80 Fan/LPC Inlet Flow Velocity 175.45 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 447.58 Fan/LPC Inlet Static Temperature 478.17 

Additional Water at LPC Exit 0.0061227 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 36.00 298.46 738.9 1.0811 798.85 8.5220 630.80 8.123 0.827 10.000 1729.0 1634.3 1146.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 298.46 5.595 480.74 -16.28 0.0000 754.73 4.358 447.58 2592.6 0.6080 1.40064 0.0001750 298.41 0.052 0.0002

FS1 Inlet.Fl_O 298.46 5.595 480.74 -16.28 0.0000 754.73 5.200 470.77 4168.2 0.3251 1.40064 0.0001750 298.41 0.052 0.0002

FS12 Splitter.Fl_02 267.12 5.592 480.74 -16.28 0.0000 675.80 5.146 469.45 3531.8 0.3465 1.40064 0.0001750 267.07 0.047 0.0002

FS2 Splitter.Fl_01 31.34 5.592 480.74 -16.28 0.0000 79.30 5.489 478.17 830.5 0.1636 1.40064 0.0001750 31.34 0.005 0.0002

FS14 Fan.Fl_O 267.12 6.141 495.19 -12.82 0.0000 624.61 5.322 475.33 2606.7 0.4568 1.40049 0.0001750 267.07 0.047 0.0002

FS23 LPC.Fl_O 31.34 7.841 538.01 -2.55 0.0000 59.83 7.497 531.15 412.6 0.2542 1.39993 0.0001750 31.34 0.005 0.0002

FS24 VaporIN.Fl_O 31.54 7.841 546.24 -35.66 0.0000 60.66 7.485 539.05 412.6 0.2586 1.39896 0.0062976 31.34 0.197 0.0063

FS25 Bleed2.Fl_O 26.81 7.841 546.24 -35.66 0.0000 51.56 7.588 541.15 412.6 0.2172 1.39896 0.0062976 26.64 0.168 0.0063

FS3 HPC.Fl_O 25.51 45.449 976.73 69.61 0.0000 11.32 40.035 943.07 49.7 0.4320 1.38116 0.0062976 25.35 0.160 0.0063

FS36 Bleed3.Fl_O 19.77 45.449 976.73 69.61 0.0000 8.77 42.340 957.80 49.3 0.3218 1.38116 0.0062976 19.64 0.124 0.0063

FS4 Burner.Fl_O 19.99 44.402 1729.03 57.17 0.0113 12.08 41.920 1704.47 74.6 0.2951 1.32986 0.0062976 19.64 0.124 0.0199

FS45 HPT.Fl_O 26.71 11.128 1151.23 -44.72 0.0084 52.56 10.164 1123.67 265.4 0.3664 1.36435 0.0062976 26.33 0.166 0.0165

FS49 LPT.Fl_O 27.03 4.713 949.82 -94.18 0.0083 114.04 4.541 940.17 860.2 0.2332 1.37726 0.0062976 26.64 0.168 0.0163

FS5 TEGV.Fl_O 27.03 4.713 949.89 -94.18 0.0083 114.05 4.541 940.24 860.2 0.2332 1.37725 0.0062976 26.64 0.168 0.0163

FS8 Core_Nozz.Fl_O 27.03 4.713 949.96 -94.18 0.0083 114.05 4.358 929.79 613.3 0.3388 1.37725 0.0062976 26.64 0.168 0.0163

FS17 FanDuctLkg.Fl_O 267.12 6.141 495.19 -12.82 0.0000 624.61 5.322 475.33 2606.7 0.4568 1.40049 0.0001750 267.07 0.047 0.0002

FS171 Bleed15.Fl_O 271.85 6.141 496.09 -13.22 0.0000 636.24 5.174 472.37 2481.9 0.5006 1.40047 0.0002809 271.77 0.076 0.0003

FS172 FanDuct.Fl_O 271.85 6.141 496.09 -13.22 0.0000 636.24 5.174 472.37 2481.9 0.5006 1.40047 0.0002809 271.77 0.076 0.0003

FS173 Byp_Nozz.Fl_O 271.85 6.141 496.09 -13.22 0.0000 636.24 4.358 449.74 2006.9 0.7172 1.40047 0.0002809 271.77 0.076 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 675.80 1.098 0.9023 2251.777 1.0301 0.9036 -1309.6 -9547.00 52.70

LPC 79.30 1.402 0.8515 2251.777 1.1191 0.8584 -609.2 5.95 2.63

HPC 51.56 5.796 0.8135 8877.522 1.7881 0.8523 -3895.8 62.65 59.01

HPT 12.08 3.990 0.8755 219.098 1.3514 0.8539 3895.7 

LPT 52.56 2.361 0.8358 63.893 1.2096 0.8186 1918.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 785.22 1.096 0.9041 2230.307 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 60.40 1.383 0.7655 0.595 0.0000 1.3129 1.0509 1.1123 0.0003

HPC 46.89 5.570 0.8219 8640.853 10.9296 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.907 0.8754 1.317 3.9074 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.024 0.8420 0.719 2.0237 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–73
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2592.60 5851.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9865 763.28 16.98 11.128

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3136 763.28 16.98 4.713

TEGV 0.0000 0.2332 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 741.71 11.71 16.115

FanDuct 0.0000 0.5006 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 874.84 44.35 31.158

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 741.71 11.71 16.115

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 976.73 69.61 45.449

Splitter 8.5220 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 741.71 11.71 16.115

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9110.4 2245.9 3895.7 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7304 546.24 -35.66 7.841

LP_Shaft 2167.9 4648.8 1918.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.0607 976.73 69.61 44.402

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.6782 976.73 69.61 25.369

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.73 69.61 45.449

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.73 69.61 45.449

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.73 69.61 45.449

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 495.19 -12.82 6.141

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 495.19 -12.82 6.141

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 495.19 -12.82 6.141

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 495.19 -12.82 6.141

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1728.98 0.9995 0.0230 0.22190 0.01130 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.081 0.9801 1.0000 0.9800 613.40 0.339 493.4 414.4

Byp_Nozz 1.409 0.9800 1.0000 0.9800 2006.86 0.717 731.0 6176.0

NASA/TM—2013-218094 K–74
************************************************************************************************************************************ 

Date:05/10/13 Time:11:42:12 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 27/ 55/ 2/24 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 492.48 Stator 1 exit: 496.71 Stator 2 inlet: 501.55 Stator 2 exit: 503.48 

 Stator 3 inlet: 508.81 Stator 3 exit: 510.32 Stator 4 inlet: 515.40 Stator 4 exit: 516.48 

 Stator 5 inlet: 520.20 Stator 5 exit: 521.01 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.02 

Fan Bypass Relative Humidity 4.18 

LPC Inlet Relative Humidity 4.02 

LPC Exit Relative Humidity 1.33 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 582.56 Fan/LPC Inlet Flow Velocity 194.07 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 463.14 Fan/LPC Inlet Static Temperature 488.28 

Additional Water at LPC Exit 0.0055547 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 36.00 322.69 740.5 1.1395 843.77 7.1911 582.56 7.220 0.857 10.000 1731.5 1634.9 1153.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 322.69 6.516 491.41 -14.47 0.0000 708.40 5.297 463.14 2584.4 0.5520 1.40052 0.0003043 322.59 0.098 0.0003

FS1 Inlet.Fl_O 322.69 6.516 491.41 -14.47 0.0000 708.40 6.115 482.56 4168.2 0.3026 1.40052 0.0003043 322.59 0.098 0.0003

FS12 Splitter.Fl_02 283.30 6.513 491.41 -14.47 0.0000 622.22 6.079 481.83 3531.8 0.3152 1.40052 0.0003043 283.21 0.086 0.0003

FS2 Splitter.Fl_01 39.40 6.513 491.41 -14.47 0.0000 86.53 6.369 488.28 830.5 0.1791 1.40052 0.0003043 39.38 0.012 0.0003

FS14 Fan.Fl_O 283.30 7.049 503.88 -11.48 0.0000 582.12 6.253 486.89 2606.7 0.4173 1.40038 0.0003043 283.21 0.086 0.0003

FS23 LPC.Fl_O 39.40 8.231 532.47 -4.63 0.0000 71.27 7.706 522.54 412.6 0.3082 1.40000 0.0003043 39.38 0.012 0.0003

FS24 VaporIN.Fl_O 39.61 8.231 540.00 -34.67 0.0000 72.17 7.690 529.62 412.6 0.3133 1.39912 0.0058591 39.38 0.231 0.0058

FS25 Bleed2.Fl_O 27.73 8.231 540.00 -34.67 0.0000 50.52 7.976 535.17 412.6 0.2126 1.39912 0.0058591 27.57 0.162 0.0058

FS3 HPC.Fl_O 26.38 47.048 962.60 68.55 0.0000 11.23 41.550 930.03 49.7 0.4275 1.38208 0.0058591 26.23 0.154 0.0058

FS36 Bleed3.Fl_O 20.45 47.048 962.60 68.55 0.0000 8.70 43.886 944.24 49.3 0.3187 1.38208 0.0058591 20.33 0.119 0.0058

FS4 Burner.Fl_O 20.68 45.964 1731.49 55.86 0.0115 12.08 43.394 1706.91 74.6 0.2951 1.32966 0.0058591 20.33 0.119 0.0197

FS45 HPT.Fl_O 27.64 11.900 1157.81 -43.90 0.0086 51.00 10.937 1131.99 265.4 0.3536 1.36388 0.0058591 27.25 0.160 0.0162

FS49 LPT.Fl_O 27.96 5.619 980.30 -87.34 0.0085 100.55 5.460 972.68 860.2 0.2042 1.37534 0.0058591 27.57 0.162 0.0161

FS5 TEGV.Fl_O 27.96 5.619 980.37 -87.34 0.0085 100.56 5.460 972.75 860.2 0.2042 1.37534 0.0058591 27.57 0.162 0.0161

FS8 Core_Nozz.Fl_O 27.96 5.619 980.44 -87.34 0.0085 100.56 5.297 964.77 613.4 0.2939 1.37533 0.0058591 27.57 0.162 0.0161

FS17 FanDuctLkg.Fl_O 283.30 7.049 503.88 -11.48 0.0000 582.12 6.253 486.89 2606.7 0.4173 1.40038 0.0003043 283.21 0.086 0.0003

FS171 Bleed15.Fl_O 295.18 7.049 505.34 -12.42 0.0000 607.42 6.059 483.94 2481.9 0.4699 1.40033 0.0005268 295.03 0.155 0.0005

FS172 FanDuct.Fl_O 295.18 7.049 505.34 -12.42 0.0000 607.42 6.059 483.94 2481.9 0.4699 1.40033 0.0005268 295.03 0.155 0.0005

FS173 Byp_Nozz.Fl_O 295.18 7.049 505.34 -12.42 0.0000 607.42 5.297 465.68 2006.9 0.6521 1.40033 0.0005268 295.03 0.155 0.0005

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 622.22 1.082 0.9026 2036.846 1.0254 0.9037 -1197.9 -2694.73 49.93

LPC 86.53 1.264 0.8285 2036.846 1.0835 0.8341 -548.9 6.40 2.41

HPC 50.52 5.716 0.8119 8844.399 1.7826 0.8508 -3951.4 62.08 58.34

HPT 12.08 3.863 0.8762 216.874 1.3421 0.8553 3951.4 

LPT 51.00 2.118 0.8253 58.266 1.1782 0.8097 1746.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 722.96 1.080 0.9044 2017.425 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.21 1.308 0.7606 0.538 0.0000 1.6261 0.8553 1.0894 0.0003

HPC 45.95 5.494 0.8203 8608.613 10.9778 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.783 0.8762 1.303 3.7833 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.841 0.8315 0.655 1.8408 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–75
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2584.38 5842.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0205 752.98 16.94 11.900

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3244 752.98 16.94 5.619

TEGV 0.0000 0.2042 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 731.80 11.78 16.771

FanDuct 0.0000 0.4699 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 862.52 43.78 32.297

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 731.80 11.78 16.771

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 962.60 68.55 47.048

Splitter 7.1911 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 731.80 11.78 16.771

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9024.4 2299.7 3951.4 WB17Y Bleed> 0.3000 1.0000 1.0000 11.8842 540.00 -34.67 8.231

LP_Shaft 1982.6 4627.6 1746.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1662 962.60 68.55 45.964

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7705 962.60 68.55 26.479

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.60 68.55 47.048

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.60 68.55 47.048

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.60 68.55 47.048

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 503.88 -11.48 7.049

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 503.88 -11.48 7.049

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 503.88 -11.48 7.049

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 503.88 -11.48 7.049

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1731.44 0.9995 0.0230 0.23438 0.01153 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.061 0.9801 1.0000 0.9800 613.40 0.294 435.6 378.6 

Byp_Nozz 1.331 0.9800 1.0000 0.9800 2006.86 0.652 676.3 6204.7

NASA/TM—2013-218094 K–76
************************************************************************************************************************************ 

Date:05/10/13 Time:11:42:56 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 43/ 71/ 2/40 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 505.44 Stator 1 exit: 508.48 Stator 2 inlet: 511.40 Stator 2 exit: 512.25 

 Stator 3 inlet: 515.70 Stator 3 exit: 516.12 Stator 4 inlet: 519.49 Stator 4 exit: 519.63 

 Stator 5 inlet: 521.64 Stator 5 exit: 521.58 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.02 

Fan Bypass Relative Humidity 5.16 

LPC Inlet Relative Humidity 5.19 

LPC Exit Relative Humidity 2.75 

HPC Relative Humidity 0.09 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 528.20 Fan/LPC Inlet Flow Velocity 201.72 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 483.18 Fan/LPC Inlet Static Temperature 503.02 

Additional Water at LPC Exit 0.0064451 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 36.00 358.30 801.9 1.1573 928.02 6.4043 528.20 6.292 0.888 10.000 1758.3 1658.1 1181.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 358.30 7.943 506.41 -12.46 0.0000 655.03 6.740 483.18 2595.3 0.4900 1.40031 0.0005787 358.09 0.207 0.0006

FS1 Inlet.Fl_O 358.30 7.943 506.41 -12.46 0.0000 655.03 7.529 498.72 4168.2 0.2775 1.40031 0.0005787 358.09 0.207 0.0006

FS12 Splitter.Fl_02 309.91 7.939 506.41 -12.46 0.0000 566.84 7.507 498.36 3531.8 0.2840 1.40031 0.0005787 309.73 0.179 0.0006

FS2 Splitter.Fl_01 48.39 7.939 506.41 -12.46 0.0000 88.51 7.755 503.02 830.5 0.1834 1.40031 0.0005787 48.36 0.028 0.0006

FS14 Fan.Fl_O 309.91 8.493 517.30 -9.85 0.0000 535.56 7.699 503.00 2606.7 0.3769 1.40017 0.0005787 309.73 0.179 0.0006

FS23 LPC.Fl_O 48.39 9.116 535.13 -5.57 0.0000 79.24 8.384 522.47 412.6 0.3480 1.39992 0.0005787 48.36 0.028 0.0006

FS24 VaporIN.Fl_O 48.70 9.116 543.81 -40.38 0.0000 80.39 8.357 530.48 412.6 0.3549 1.39890 0.0070238 48.36 0.340 0.0070

FS25 Bleed2.Fl_O 29.22 9.116 543.81 -40.38 0.0000 48.23 8.860 539.40 412.6 0.2025 1.39890 0.0070238 29.02 0.204 0.0070

FS3 HPC.Fl_O 27.80 49.978 958.61 61.03 0.0000 11.11 44.269 926.94 49.7 0.4222 1.38214 0.0070238 27.61 0.194 0.0070

FS36 Bleed3.Fl_O 21.55 49.978 958.61 61.03 0.0000 8.61 46.690 940.72 49.3 0.3152 1.38214 0.0070238 21.40 0.150 0.0070

FS4 Burner.Fl_O 21.81 48.827 1758.30 47.88 0.0120 12.08 46.093 1733.41 74.6 0.2955 1.32791 0.0070238 21.40 0.150 0.0215

FS45 HPT.Fl_O 29.14 13.336 1186.38 -49.92 0.0090 48.56 12.366 1162.79 265.4 0.3345 1.36163 0.0070238 28.68 0.201 0.0178

FS49 LPT.Fl_O 29.48 7.035 1030.55 -88.02 0.0089 86.80 6.889 1024.69 860.2 0.1754 1.37175 0.0070238 29.02 0.204 0.0177

FS5 TEGV.Fl_O 29.48 7.035 1030.62 -88.02 0.0089 86.80 6.889 1024.76 860.2 0.1754 1.37175 0.0070238 29.02 0.204 0.0177

FS8 Core_Nozz.Fl_O 29.48 7.035 1030.69 -88.02 0.0089 86.81 6.740 1018.78 613.5 0.2506 1.37174 0.0070238 29.02 0.204 0.0177

FS17 FanDuctLkg.Fl_O 309.91 8.493 517.30 -9.85 0.0000 535.56 7.699 503.00 2606.7 0.3769 1.40017 0.0005787 309.73 0.179 0.0006

FS171 Bleed15.Fl_O 329.39 8.493 518.88 -11.65 0.0000 570.09 7.467 500.14 2481.9 0.4326 1.40010 0.0009575 329.07 0.315 0.0010

FS172 FanDuct.Fl_O 329.39 8.493 518.88 -11.65 0.0000 570.09 7.467 500.14 2481.9 0.4326 1.40010 0.0009575 329.07 0.315 0.0010

FS173 Byp_Nozz.Fl_O 329.39 8.493 518.88 -11.65 0.0000 570.09 6.740 485.70 2006.8 0.5841 1.40010 0.0009575 329.07 0.315 0.0010

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 566.84 1.070 0.9044 1828.989 1.0215 0.9053 -1146.2 -1852.73 46.50

LPC 88.51 1.148 0.7107 1828.989 1.0567 0.7163 -471.9 7.06 2.10

HPC 48.23 5.482 0.8076 8767.052 1.7628 0.8465 -4091.0 62.46 58.43

HPT 12.08 3.661 0.8778 214.084 1.3260 0.8581 4090.9 

LPT 48.56 1.896 0.8176 52.469 1.1479 0.8039 1618.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 658.62 1.068 0.9062 1811.550 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 46.43 1.242 0.7552 0.483 0.0000 1.9063 0.6129 0.9411 0.0003

HPC 43.87 5.271 0.8159 8533.328 10.9880 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.587 0.8778 1.287 3.5875 12.6299 0.9723 1.0000 0.0003

LPT 0.74 1.674 0.8237 0.590 1.6736 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–77
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2595.25 5882.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0753 752.84 10.33 13.336

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3419 752.84 10.33 7.035

TEGV 0.0000 0.1754 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.05 5.26 18.106

FanDuct 0.0000 0.4326 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 860.35 36.69 34.450

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.05 5.26 18.106

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 958.61 61.03 49.978

Splitter 6.4043 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.05 5.26 18.106

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8977.0 2393.4 4090.9 WB17Y Bleed> 0.4000 1.0000 1.0000 19.4809 543.81 -40.38 9.116

LP_Shaft 1807.2 4702.7 1618.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3365 958.61 61.03 48.827

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9195 958.61 61.03 28.526

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 958.61 61.03 49.978

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 958.61 61.03 49.978

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 958.61 61.03 49.978

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 517.30 -9.85 8.493

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 517.30 -9.85 8.493

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 517.30 -9.85 8.493

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 517.30 -9.85 8.493

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1758.25 0.9995 0.0230 0.25778 0.01205 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.044 0.9801 1.0000 0.9800 613.40 0.251 381.3 349.4

Byp_Nozz 1.260 0.9800 1.0000 0.9800 2006.86 0.584 618.8 6334.7

NASA/TM—2013-218094 K–78
 5μm, 4g/m3

, ISA +36R

************************************************************************************************************************************ 

Date:07/05/13 Time:11:40:21 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.24 Stator 1 exit: 492.23 Stator 2 inlet: 502.23 Stator 2 exit: 507.43 

 Stator 3 inlet: 517.61 Stator 3 exit: 522.26 Stator 4 inlet: 531.67 Stator 4 exit: 535.70 

 Stator 5 inlet: 543.48 Stator 5 exit: 546.96 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.98 

Fan Bypass Relative Humidity 1.38 

LPC Inlet Relative Humidity 1.30 

LPC Exit Relative Humidity 0.12 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 188.03 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 474.97 

Additional Water at LPC Exit 0.0136991 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 252.55 675.0 1.0748 725.47 8.8208 789.49 9.536 0.736 10.000 1804.6 1708.2 1191.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.55 4.267 477.92 -16.44 0.0000 834.98 2.854 425.97 2547.4 0.7800 1.40068 0.0000851 252.52 0.021 0.0001

FS1 Inlet.Fl_O 252.55 4.267 477.92 -16.44 0.0000 834.98 3.890 465.46 4168.2 0.3656 1.40068 0.0000851 252.52 0.021 0.0001

FS12 Splitter.Fl_02 226.83 4.265 477.92 -16.44 0.0000 750.33 3.835 463.62 3531.8 0.3923 1.40068 0.0000851 226.81 0.019 0.0001

FS2 Splitter.Fl_01 25.72 4.265 477.92 -16.44 0.0000 85.06 4.173 474.97 830.5 0.1759 1.40068 0.0000851 25.71 0.002 0.0001

FS14 Fan.Fl_O 226.83 4.839 497.33 -11.79 0.0000 674.54 4.059 472.95 2606.7 0.5072 1.40048 0.0000851 226.81 0.019 0.0001

FS23 LPC.Fl_O 25.72 6.717 557.91 2.75 0.0000 58.35 6.437 551.16 412.6 0.2474 1.39963 0.0000851 25.71 0.002 0.0001

FS24 VaporIN.Fl_O 26.07 6.717 575.55 -70.86 0.0000 60.08 6.417 568.11 412.6 0.2567 1.39743 0.0137842 25.71 0.354 0.0136

FS25 Bleed2.Fl_O 23.46 6.717 575.55 -70.86 0.0000 54.07 6.476 569.61 412.6 0.2292 1.39743 0.0137842 23.14 0.319 0.0136

FS3 HPC.Fl_O 22.32 40.686 1037.91 43.38 0.0000 11.41 35.721 1001.55 49.7 0.4384 1.37623 0.0137842 22.02 0.304 0.0136

FS36 Bleed3.Fl_O 17.30 40.686 1037.91 43.38 0.0000 8.84 37.841 1017.51 49.3 0.3261 1.37623 0.0137842 17.07 0.235 0.0136

FS4 Burner.Fl_O 17.50 39.749 1804.55 30.77 0.0118 12.07 37.519 1779.12 74.6 0.2961 1.32499 0.0137842 17.07 0.235 0.0276

FS45 HPT.Fl_O 23.39 9.542 1195.90 -79.98 0.0088 54.69 8.634 1164.58 265.4 0.3858 1.36020 0.0137842 22.87 0.315 0.0241

FS49 LPT.Fl_O 23.66 3.268 936.79 -144.66 0.0087 143.03 3.074 921.23 860.2 0.2992 1.37678 0.0137842 23.14 0.319 0.0240

FS5 TEGV.Fl_O 23.66 3.268 936.86 -144.66 0.0087 143.03 3.074 921.30 860.2 0.2992 1.37677 0.0137842 23.14 0.319 0.0240

FS8 Core_Nozz.Fl_O 23.66 3.268 936.93 -144.66 0.0087 143.04 2.854 902.80 613.4 0.4472 1.37677 0.0137842 23.14 0.319 0.0240

FS17 FanDuctLkg.Fl_O 226.83 4.839 497.33 -11.79 0.0000 674.54 4.059 472.95 2606.7 0.5072 1.40048 0.0000851 226.81 0.019 0.0001

FS171 Bleed15.Fl_O 229.44 4.839 498.23 -12.46 0.0000 682.90 3.925 469.25 2481.9 0.5552 1.40045 0.0002386 229.38 0.055 0.0002

FS172 FanDuct.Fl_O 229.44 4.839 498.23 -12.46 0.0000 682.90 3.925 469.25 2481.9 0.5552 1.40045 0.0002386 229.38 0.055 0.0002

FS173 Byp_Nozz.Fl_O 229.44 4.839 498.23 -12.46 0.0000 682.90 2.854 428.37 2006.9 0.9021 1.40045 0.0002386 229.38 0.055 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 750.33 1.135 0.9066 2595.218 1.0406 0.9083 -1492.9 1442.03 54.43

LPC 85.06 1.575 0.8285 2595.218 1.1674 0.8391 -698.1 7.05 3.93

HPC 54.07 6.057 0.8178 8959.420 1.8033 0.8563 -3700.2 62.16 58.80

HPT 12.07 4.166 0.8795 222.173 1.3620 0.8580 3700.2 

LPT 54.69 2.920 0.8601 72.037 1.2749 0.8411 2191.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 871.82 1.132 0.9085 2570.473 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 75.08 1.534 0.7812 0.685 0.0000 1.1330 1.0768 1.0606 0.0003

HPC 49.18 5.819 0.8263 8720.568 10.9274 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.078 0.8795 1.335 4.0779 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.444 0.8665 0.810 2.4443 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–79
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2547.36 6197.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8634 809.07 -13.74 9.542

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2745 809.07 -13.74 3.268

TEGV 0.0000 0.2992 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 785.89 -19.46 14.190

FanDuct 0.0000 0.5552 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 928.77 15.96 27.778

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 785.89 -19.46 14.190

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1037.91 43.38 40.686

Splitter 8.8208 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 785.89 -19.46 14.190

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9437.9 2059.1 3700.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6068 575.55 -70.86 6.717

LP_Shaft 2491.2 4619.2 2191.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6788 1037.91 43.38 39.749

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3440 1037.91 43.38 22.471

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1037.91 43.38 40.686

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1037.91 43.38 40.686

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1037.91 43.38 40.686

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 497.33 -11.79 4.839

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 497.33 -11.79 4.839

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 497.33 -11.79 4.839

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 497.33 -11.79 4.839

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1804.50 0.9995 0.0230 0.20152 0.01181 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.145 0.9801 1.0000 0.9800 613.40 0.447 643.2 473.1

Byp_Nozz 1.696 0.9800 1.0000 0.9800 2006.86 0.902 897.3 6398.9

NASA/TM—2013-218094 K–80
************************************************************************************************************************************ 

Date:07/05/13 Time:11:40:38 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 477.31 Stator 1 exit: 484.74 Stator 2 inlet: 494.04 Stator 2 exit: 498.85 

 Stator 3 inlet: 508.36 Stator 3 exit: 512.69 Stator 4 inlet: 521.47 Stator 4 exit: 525.07 

 Stator 5 inlet: 532.29 Stator 5 exit: 535.49 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.47 

Fan Bypass Relative Humidity 1.77 

LPC Inlet Relative Humidity 1.63 

LPC Exit Relative Humidity 0.16 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 738.88 Fan/LPC Inlet Flow Velocity 182.53 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 468.70 

Additional Water at LPC Exit 0.0100863 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 36.00 245.68 648.7 1.0595 687.25 8.8534 738.88 9.250 0.764 10.000 1766.2 1670.8 1166.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 245.68 4.201 471.48 -17.97 0.0000 819.36 2.947 425.97 2564.5 0.7300 1.40073 0.0000824 245.66 0.020 0.0001

FS1 Inlet.Fl_O 245.68 4.201 471.48 -17.97 0.0000 819.36 3.846 459.70 4168.2 0.3575 1.40073 0.0000824 245.66 0.020 0.0001

FS12 Splitter.Fl_02 220.75 4.199 471.48 -17.97 0.0000 736.57 3.794 457.97 3531.8 0.3836 1.40073 0.0000824 220.73 0.018 0.0001

FS2 Splitter.Fl_01 24.93 4.199 471.48 -17.97 0.0000 83.20 4.113 468.70 830.5 0.1719 1.40073 0.0000824 24.93 0.002 0.0001

FS14 Fan.Fl_O 220.75 4.727 489.42 -13.67 0.0000 666.62 3.988 466.17 2606.7 0.4989 1.40057 0.0000824 220.73 0.018 0.0001

FS23 LPC.Fl_O 24.93 6.461 545.68 -0.17 0.0000 58.17 6.193 539.13 412.6 0.2466 1.39982 0.0000824 24.93 0.002 0.0001

FS24 VaporIN.Fl_O 25.19 6.461 558.99 -54.53 0.0000 59.47 6.179 551.93 412.6 0.2535 1.39823 0.0101687 24.93 0.254 0.0101

FS25 Bleed2.Fl_O 22.67 6.461 558.99 -54.53 0.0000 53.53 6.234 553.35 412.6 0.2264 1.39823 0.0101687 22.44 0.228 0.0101

FS3 HPC.Fl_O 21.57 38.862 1007.76 55.78 0.0000 11.37 34.170 972.69 49.7 0.4356 1.37866 0.0101687 21.35 0.217 0.0101

FS36 Bleed3.Fl_O 16.71 38.862 1007.76 55.78 0.0000 8.81 36.171 988.06 49.3 0.3241 1.37866 0.0101687 16.55 0.168 0.0101

FS4 Burner.Fl_O 16.91 37.967 1766.18 43.27 0.0115 12.08 35.841 1741.19 74.6 0.2956 1.32742 0.0101687 16.55 0.168 0.0239

FS45 HPT.Fl_O 22.59 9.229 1170.97 -63.61 0.0086 54.06 8.375 1141.07 265.4 0.3796 1.36242 0.0101687 22.18 0.226 0.0204

FS49 LPT.Fl_O 22.86 3.316 928.08 -123.81 0.0085 135.52 3.141 914.38 860.2 0.2814 1.37792 0.0101687 22.44 0.228 0.0203

FS5 TEGV.Fl_O 22.86 3.316 928.15 -123.81 0.0085 135.53 3.141 914.45 860.2 0.2814 1.37792 0.0101687 22.44 0.228 0.0203

FS8 Core_Nozz.Fl_O 22.86 3.316 928.22 -123.81 0.0085 135.53 2.947 898.63 613.4 0.4168 1.37791 0.0101687 22.44 0.228 0.0203

FS17 FanDuctLkg.Fl_O 220.75 4.727 489.42 -13.67 0.0000 666.62 3.988 466.17 2606.7 0.4989 1.40057 0.0000824 220.73 0.018 0.0001

FS171 Bleed15.Fl_O 223.27 4.727 490.21 -14.13 0.0000 674.77 3.862 462.66 2481.9 0.5452 1.40055 0.0001950 223.23 0.044 0.0002

FS172 FanDuct.Fl_O 223.27 4.727 490.21 -14.13 0.0000 674.77 3.862 462.66 2481.9 0.5452 1.40055 0.0001950 223.23 0.044 0.0002

FS173 Byp_Nozz.Fl_O 223.27 4.727 490.21 -14.13 0.0000 674.77 2.947 428.20 2006.9 0.8500 1.40055 0.0001950 223.23 0.044 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 736.57 1.126 0.9057 2525.346 1.0381 0.9073 -1343.2 1950.43 54.42

LPC 83.20 1.539 0.8328 2525.346 1.1574 0.8426 -627.9 6.84 3.41

HPC 53.53 6.015 0.8173 8942.041 1.8028 0.8558 -3452.0 61.87 58.46

HPT 12.08 4.114 0.8778 220.891 1.3596 0.8561 3452.0 

LPT 54.06 2.783 0.8534 70.361 1.2598 0.8346 1971.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 855.83 1.123 0.9075 2501.267 0.0415 0.8607 1.0235 0.9980 0.9905

LPC 72.05 1.503 0.7779 0.667 0.0000 1.1547 1.0710 1.0706 0.0003

HPC 48.68 5.779 0.8257 8703.652 10.9516 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.028 0.8778 1.328 4.0278 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.341 0.8598 0.791 2.3413 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–81
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2564.47 5642.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8341 785.45 0.62 9.229

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2652 785.45 0.62 3.316

TEGV 0.0000 0.2814 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 762.96 -4.89 13.589

FanDuct 0.0000 0.5452 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 901.70 29.30 26.550

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 762.96 -4.89 13.589

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1007.76 55.78 38.862

Splitter 8.8534 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 762.96 -4.89 13.589

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9283.1 1953.0 3452.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5185 558.99 -54.53 6.461

LP_Shaft 2407.7 4299.6 1971.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.5881 1007.76 55.78 37.967

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2647 1007.76 55.78 21.529

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.76 55.78 38.862

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.76 55.78 38.862

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.76 55.78 38.862

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 489.42 -13.67 4.727

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 489.42 -13.67 4.727

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 489.42 -13.67 4.727

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 489.42 -13.67 4.727

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1766.13 0.9995 0.0230 0.19090 0.01154 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.125 0.9801 1.0000 0.9800 613.40 0.417 597.7 424.6

Byp_Nozz 1.604 0.9800 1.0000 0.9800 2006.86 0.850 845.3 5866.2

NASA/TM—2013-218094 K–82
************************************************************************************************************************************ 

Date:07/05/13 Time:11:40:55 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 475.18 Stator 1 exit: 482.41 Stator 2 inlet: 491.46 Stator 2 exit: 496.13 

 Stator 3 inlet: 505.38 Stator 3 exit: 509.60 Stator 4 inlet: 518.16 Stator 4 exit: 521.66 

 Stator 5 inlet: 528.65 Stator 5 exit: 531.75 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.64 

Fan Bypass Relative Humidity 1.92 

LPC Inlet Relative Humidity 1.75 

LPC Exit Relative Humidity 0.18 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 722.68 Fan/LPC Inlet Flow Velocity 180.06 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 466.80 

Additional Water at LPC Exit 0.0091788 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 36.00 252.23 659.2 1.0582 697.55 8.8837 722.68 9.121 0.772 10.000 1752.6 1657.6 1158.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.23 4.339 469.50 -18.42 0.0000 812.74 3.088 425.97 2568.3 0.7140 1.40075 0.0000786 252.21 0.020 0.0001

FS1 Inlet.Fl_O 252.23 4.339 469.50 -18.42 0.0000 812.74 3.979 457.99 4168.2 0.3541 1.40075 0.0000786 252.21 0.020 0.0001

FS12 Splitter.Fl_02 226.71 4.337 469.50 -18.42 0.0000 730.87 3.925 456.30 3531.8 0.3801 1.40075 0.0000786 226.69 0.018 0.0001

FS2 Splitter.Fl_01 25.52 4.337 469.50 -18.42 0.0000 82.27 4.250 466.80 830.5 0.1700 1.40075 0.0000786 25.52 0.002 0.0001

FS14 Fan.Fl_O 226.71 4.867 486.90 -14.25 0.0000 663.20 4.116 464.09 2606.7 0.4953 1.40060 0.0000786 226.69 0.018 0.0001

FS23 LPC.Fl_O 25.52 6.610 541.65 -1.12 0.0000 57.98 6.338 535.19 412.6 0.2457 1.39989 0.0000786 25.52 0.002 0.0001

FS24 VaporIN.Fl_O 25.75 6.610 553.85 -50.63 0.0000 59.17 6.325 546.93 412.6 0.2520 1.39844 0.0092574 25.52 0.236 0.0092

FS25 Bleed2.Fl_O 23.18 6.610 553.85 -50.63 0.0000 53.25 6.381 548.31 412.6 0.2251 1.39844 0.0092574 22.97 0.213 0.0092

FS3 HPC.Fl_O 22.05 39.578 997.72 58.33 0.0000 11.36 34.812 963.06 49.7 0.4348 1.37943 0.0092574 21.85 0.202 0.0092

FS36 Bleed3.Fl_O 17.09 39.578 997.72 58.33 0.0000 8.80 36.844 978.25 49.3 0.3236 1.37943 0.0092574 16.94 0.157 0.0092

FS4 Burner.Fl_O 17.29 38.666 1752.62 45.89 0.0114 12.08 36.501 1727.80 74.6 0.2955 1.32824 0.0092574 16.94 0.157 0.0229

FS45 HPT.Fl_O 23.10 9.441 1162.36 -59.66 0.0085 53.83 8.577 1132.96 265.4 0.3775 1.36315 0.0092574 22.70 0.210 0.0194

FS49 LPT.Fl_O 23.37 3.455 925.40 -118.27 0.0084 132.79 3.281 912.33 860.2 0.2751 1.37825 0.0092574 22.97 0.213 0.0193

FS5 TEGV.Fl_O 23.37 3.455 925.47 -118.27 0.0084 132.80 3.281 912.40 860.2 0.2751 1.37825 0.0092574 22.97 0.213 0.0193

FS8 Core_Nozz.Fl_O 23.37 3.455 925.54 -118.27 0.0084 132.80 3.088 897.46 613.4 0.4062 1.37824 0.0092574 22.97 0.213 0.0193

FS17 FanDuctLkg.Fl_O 226.71 4.867 486.90 -14.25 0.0000 663.20 4.116 464.09 2606.7 0.4953 1.40060 0.0000786 226.69 0.018 0.0001

FS171 Bleed15.Fl_O 229.28 4.867 487.66 -14.66 0.0000 671.26 3.989 460.66 2481.9 0.5409 1.40058 0.0001808 229.24 0.041 0.0002

FS172 FanDuct.Fl_O 229.28 4.867 487.66 -14.66 0.0000 671.26 3.989 460.66 2481.9 0.5409 1.40058 0.0001808 229.24 0.041 0.0002

FS173 Byp_Nozz.Fl_O 229.28 4.867 487.66 -14.66 0.0000 671.26 3.088 428.15 2006.9 0.8328 1.40058 0.0001808 229.24 0.041 0.0002 

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 730.87 1.122 0.9052 2496.952 1.0371 0.9068 -1337.7 2278.73 54.38

LPC 82.27 1.524 0.8333 2496.952 1.1537 0.8429 -624.7 6.75 3.33

HPC 53.25 5.987 0.8168 8933.068 1.8014 0.8554 -3486.5 61.89 58.46

HPT 12.08 4.095 0.8771 220.499 1.3585 0.8554 3486.5 

LPT 53.83 2.733 0.8510 69.681 1.2540 0.8322 1962.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 849.20 1.119 0.9071 2473.144 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 70.82 1.490 0.7766 0.660 0.0000 1.1617 1.0693 1.0730 0.0003

HPC 48.43 5.752 0.8253 8694.918 10.9534 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.010 0.8771 1.325 4.0097 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.303 0.8573 0.784 2.3032 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–83
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2568.27 5665.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8530 777.78 3.85 9.441

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2712 777.78 3.85 3.455

TEGV 0.0000 0.2751 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 755.53 -1.60 13.863

FanDuct 0.0000 0.5409 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 892.77 32.18 27.050

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 755.53 -1.60 13.863

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 997.72 58.33 39.578

Splitter 8.8837 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 755.53 -1.60 13.863

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt 

HP_Shaft 9231.0 1983.7 3486.5 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5754 553.85 -50.63 6.610

LP_Shaft 2375.7 4338.5 1962.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6465 997.72 58.33 38.666

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3158 997.72 58.33 21.949

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 997.72 58.33 39.578

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 997.72 58.33 39.578

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 997.72 58.33 39.578

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.90 -14.25 4.867

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.90 -14.25 4.867

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.90 -14.25 4.867

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.90 -14.25 4.867

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1752.56 0.9995 0.0230 0.19376 0.01144 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.119 0.9801 1.0000 0.9800 613.40 0.406 582.0 422.8

Byp_Nozz 1.576 0.9800 1.0000 0.9800 2006.86 0.833 828.2 5901.8

NASA/TM—2013-218094 K–84
************************************************************************************************************************************ 

Date:07/05/13 Time:11:41:11 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.52 Stator 1 exit: 483.28 Stator 2 inlet: 491.72 Stator 2 exit: 496.06 

 Stator 3 inlet: 504.69 Stator 3 exit: 508.58 Stator 4 inlet: 516.57 Stator 4 exit: 519.79 

 Stator 5 inlet: 526.29 Stator 5 exit: 529.14 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.25 

Fan Bypass Relative Humidity 2.45 

LPC Inlet Relative Humidity 2.21 

LPC Exit Relative Humidity 0.27 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 682.24 Fan/LPC Inlet Flow Velocity 173.98 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 432.42 Fan/LPC Inlet Static Temperature 468.69 

Additional Water at LPC Exit 0.0082762 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 36.00 273.09 704.6 1.0548 743.15 8.9740 682.24 8.747 0.795 10.000 1739.1 1644.4 1151.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 273.09 4.831 471.21 -18.12 0.0000 791.83 3.578 432.42 2581.1 0.6690 1.40074 0.0000968 273.06 0.026 0.0001

FS1 Inlet.Fl_O 273.09 4.831 471.21 -18.12 0.0000 791.83 4.452 460.33 4168.2 0.3435 1.40074 0.0000968 273.06 0.026 0.0001

FS12 Splitter.Fl_02 245.71 4.829 471.21 -18.12 0.0000 712.80 4.395 458.71 3531.8 0.3688 1.40074 0.0000968 245.69 0.024 0.0001

FS2 Splitter.Fl_01 27.38 4.829 471.21 -18.12 0.0000 79.43 4.739 468.69 830.5 0.1639 1.40074 0.0000968 27.38 0.003 0.0001

FS14 Fan.Fl_O 245.71 5.374 487.42 -14.23 0.0000 651.37 4.580 465.64 2606.7 0.4832 1.40059 0.0000968 245.69 0.024 0.0001

FS23 LPC.Fl_O 27.38 7.161 538.52 -1.98 0.0000 57.25 6.875 532.27 412.6 0.2423 1.39994 0.0000968 27.38 0.003 0.0001

FS24 VaporIN.Fl_O 27.61 7.161 549.59 -46.65 0.0000 58.32 6.862 542.93 412.6 0.2480 1.39863 0.0083730 27.38 0.229 0.0083

FS25 Bleed2.Fl_O 24.85 7.161 549.59 -46.65 0.0000 52.48 6.921 544.26 412.6 0.2215 1.39863 0.0083730 24.64 0.206 0.0083

FS3 HPC.Fl_O 23.64 42.255 986.70 60.50 0.0000 11.34 37.189 952.53 49.7 0.4337 1.38024 0.0083730 23.44 0.196 0.0083

FS36 Bleed3.Fl_O 18.32 42.255 986.70 60.50 0.0000 8.79 39.347 967.49 49.3 0.3229 1.38024 0.0083730 18.17 0.152 0.0083

FS4 Burner.Fl_O 18.53 41.281 1739.08 48.11 0.0114 12.08 38.971 1714.41 74.6 0.2953 1.32905 0.0083730 18.17 0.152 0.0219

FS45 HPT.Fl_O 24.76 10.194 1155.34 -55.65 0.0085 53.28 9.283 1126.79 265.4 0.3726 1.36376 0.0083730 24.35 0.204 0.0185

FS49 LPT.Fl_O 25.05 3.943 932.36 -110.66 0.0084 125.18 3.768 920.78 860.2 0.2579 1.37799 0.0083730 24.64 0.206 0.0184

FS5 TEGV.Fl_O 25.05 3.943 932.43 -110.66 0.0084 125.18 3.768 920.85 860.2 0.2579 1.37799 0.0083730 24.64 0.206 0.0184

FS8 Core_Nozz.Fl_O 25.05 3.943 932.50 -110.66 0.0084 125.19 3.578 907.91 613.4 0.3780 1.37798 0.0083730 24.64 0.206 0.0184

FS17 FanDuctLkg.Fl_O 245.71 5.374 487.42 -14.23 0.0000 651.37 4.580 465.64 2606.7 0.4832 1.40059 0.0000968 245.69 0.024 0.0001

FS171 Bleed15.Fl_O 248.47 5.374 488.11 -14.59 0.0000 659.16 4.449 462.42 2481.9 0.5265 1.40057 0.0001880 248.42 0.047 0.0002

FS172 FanDuct.Fl_O 248.47 5.374 488.11 -14.59 0.0000 659.16 4.449 462.42 2481.9 0.5265 1.40057 0.0001880 248.42 0.047 0.0002

FS173 Byp_Nozz.Fl_O 248.47 5.374 488.11 -14.59 0.0000 659.16 3.578 434.49 2006.9 0.7848 1.40057 0.0001880 248.42 0.047 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 712.80 1.113 0.9041 2412.821 1.0344 0.9056 -1350.2 4577.10 54.02

LPC 79.43 1.483 0.8351 2412.821 1.1428 0.8440 -625.3 6.47 3.10

HPC 52.48 5.900 0.8154 8907.943 1.7953 0.8541 -3675.2 62.25 58.72

HPT 12.08 4.049 0.8762 219.883 1.3555 0.8546 3675.2 

LPT 53.28 2.585 0.8455 67.660 1.2370 0.8273 1975.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 828.20 1.110 0.9060 2389.815 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 67.18 1.453 0.7726 0.637 0.0000 1.1824 1.0675 1.0809 0.0003

HPC 47.73 5.669 0.8238 8670.463 10.9417 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.965 0.8762 1.321 3.9650 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.192 0.8517 0.761 2.1922 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–85
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2581.09 5790.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9143 770.04 6.93 10.194

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2907 770.04 6.93 3.943

TEGV 0.0000 0.2579 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 748.13 1.57 14.882

FanDuct 0.0000 0.5265 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 883.30 34.78 28.919

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 748.13 1.57 14.882

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 986.70 60.50 42.255

Splitter 8.9740 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 748.13 1.57 14.882

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9169.6 2105.1 3675.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7607 549.59 -46.65 7.161

LP_Shaft 2299.8 4511.4 1975.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8369 986.70 60.50 41.281

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4824 986.70 60.50 23.500

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 986.70 60.50 42.255

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 986.70 60.50 42.255

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 986.70 60.50 42.255

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 487.42 -14.23 5.374

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 487.42 -14.23 5.374

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 487.42 -14.23 5.374

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 487.42 -14.23 5.374

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1739.03 0.9995 0.0230 0.20643 0.01136 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.378 544.6 424.0

Byp_Nozz 1.502 0.9800 1.0000 0.9800 2006.86 0.785 786.2 6071.3

NASA/TM—2013-218094 K–86
************************************************************************************************************************************ 

Date:07/05/13 Time:11:41:37 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 15/ 43/ 2/12 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.81 Stator 1 exit: 490.63 Stator 2 inlet: 497.82 Stator 2 exit: 501.33 

 Stator 3 inlet: 508.76 Stator 3 exit: 511.83 Stator 4 inlet: 518.73 Stator 4 exit: 521.22 

 Stator 5 inlet: 526.83 Stator 5 exit: 529.00 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.20 

Fan Bypass Relative Humidity 3.33 

LPC Inlet Relative Humidity 3.05 

LPC Exit Relative Humidity 0.54 

HPC Relative Humidity 0.08 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 630.80 Fan/LPC Inlet Flow Velocity 174.79 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 447.58 Fan/LPC Inlet Static Temperature 478.19 

Additional Water at LPC Exit 0.0086245 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 36.00 298.69 752.6 1.0677 803.55 8.5644 630.80 8.134 0.827 10.000 1737.5 1642.5 1153.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 298.69 5.595 480.74 -16.28 0.0000 755.31 4.358 447.58 2594.6 0.6080 1.40064 0.0001750 298.64 0.052 0.0002

FS1 Inlet.Fl_O 298.69 5.595 480.74 -16.28 0.0000 755.31 5.199 470.75 4168.2 0.3254 1.40064 0.0001750 298.64 0.052 0.0002

FS12 Splitter.Fl_02 267.46 5.592 480.74 -16.28 0.0000 676.68 5.145 469.42 3531.8 0.3470 1.40064 0.0001750 267.42 0.047 0.0002

FS2 Splitter.Fl_01 31.23 5.592 480.74 -16.28 0.0000 79.01 5.489 478.19 830.5 0.1630 1.40064 0.0001750 31.22 0.005 0.0002

FS14 Fan.Fl_O 267.46 6.146 495.32 -12.79 0.0000 624.95 5.325 475.42 2606.7 0.4571 1.40049 0.0001750 267.42 0.047 0.0002

FS23 LPC.Fl_O 31.23 7.860 538.42 -2.45 0.0000 59.49 7.519 531.63 412.6 0.2526 1.39993 0.0001750 31.22 0.005 0.0002

FS24 VaporIN.Fl_O 31.50 7.860 549.94 -48.98 0.0000 60.64 7.503 542.70 412.6 0.2587 1.39856 0.0087995 31.22 0.275 0.0087

FS25 Bleed2.Fl_O 26.77 7.860 549.94 -48.98 0.0000 51.55 7.606 544.81 412.6 0.2174 1.39856 0.0087995 26.54 0.234 0.0087

FS3 HPC.Fl_O 25.48 45.513 982.53 57.08 0.0000 11.32 40.077 948.62 49.7 0.4328 1.38043 0.0087995 25.25 0.222 0.0087

FS36 Bleed3.Fl_O 19.74 45.513 982.53 57.08 0.0000 8.77 42.392 963.46 49.3 0.3223 1.38043 0.0087995 19.57 0.172 0.0087

FS4 Burner.Fl_O 19.97 44.465 1737.49 44.68 0.0114 12.08 41.976 1712.83 74.6 0.2954 1.32903 0.0087995 19.57 0.172 0.0224

FS45 HPT.Fl_O 26.68 11.143 1157.45 -57.99 0.0085 52.57 10.176 1129.73 265.4 0.3669 1.36355 0.0087995 26.23 0.231 0.0190

FS49 LPT.Fl_O 27.00 4.715 954.80 -107.91 0.0084 114.18 4.541 945.07 860.2 0.2337 1.37656 0.0087995 26.54 0.234 0.0189

FS5 TEGV.Fl_O 27.00 4.715 954.87 -107.91 0.0084 114.18 4.541 945.14 860.2 0.2337 1.37655 0.0087995 26.54 0.234 0.0189

FS8 Core_Nozz.Fl_O 27.00 4.715 954.94 -107.91 0.0084 114.19 4.358 934.61 613.5 0.3395 1.37655 0.0087995 26.54 0.234 0.0189

FS17 FanDuctLkg.Fl_O 267.46 6.146 495.32 -12.79 0.0000 624.95 5.325 475.42 2606.7 0.4571 1.40049 0.0001750 267.42 0.047 0.0002

FS171 Bleed15.Fl_O 272.19 6.146 496.28 -13.42 0.0000 636.61 5.177 472.52 2481.9 0.5010 1.40046 0.0003234 272.10 0.088 0.0003

FS172 FanDuct.Fl_O 272.19 6.146 496.28 -13.42 0.0000 636.61 5.177 472.52 2481.9 0.5010 1.40046 0.0003234 272.10 0.088 0.0003

FS173 Byp_Nozz.Fl_O 272.19 6.146 496.28 -13.42 0.0000 636.61 4.358 449.80 2006.9 0.7181 1.40046 0.0003234 272.10 0.088 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 676.68 1.099 0.9026 2258.248 1.0303 0.9040 -1323.1 -----.-- 52.65

LPC 79.01 1.406 0.8518 2258.248 1.1200 0.8588 -611.3 5.94 2.65

HPC 51.55 5.790 0.8134 8877.027 1.7866 0.8522 -3920.1 62.78 59.14

HPT 12.08 3.990 0.8759 219.291 1.3510 0.8545 3920.1 

LPT 52.57 2.364 0.8366 63.904 1.2098 0.8195 1934.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 786.23 1.097 0.9045 2236.716 0.0417 0.8607 1.0235 0.9980 0.9905

LPC 60.62 1.385 0.7657 0.596 0.0000 1.3034 1.0536 1.1125 0.0003

HPC 46.88 5.565 0.8218 8640.372 10.9217 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.908 0.8759 1.318 3.9076 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.026 0.8429 0.719 2.0255 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–87
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2594.60 5856.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9853 768.08 4.05 11.143

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3133 768.08 4.05 4.715

TEGV 0.0000 0.2337 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 746.40 -1.25 16.144

FanDuct 0.0000 0.5010 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 880.18 31.62 31.205

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 746.40 -1.25 16.144

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 982.53 57.08 45.513

Splitter 8.5644 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 746.40 -1.25 16.144

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9140.7 2252.4 3920.1 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7248 549.94 -48.98 7.860

LP_Shaft 2174.1 4673.0 1934.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.0571 982.53 57.08 44.465

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.6750 982.53 57.08 25.405

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 982.53 57.08 45.513

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 982.53 57.08 45.513

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 982.53 57.08 45.513

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 495.32 -12.79 6.146

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 495.32 -12.79 6.146

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 495.32 -12.79 6.146

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 495.32 -12.79 6.146

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1737.44 0.9995 0.0230 0.22321 0.01140 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 496.0 416.2

Byp_Nozz 1.410 0.9800 1.0000 0.9800 2006.86 0.718 732.0 6192.5

NASA/TM—2013-218094 K–88
************************************************************************************************************************************ 

Date:07/05/13 Time:11:42:08 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 50/ 2/19 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 492.56 Stator 1 exit: 496.81 Stator 2 inlet: 501.69 Stator 2 exit: 503.65 

 Stator 3 inlet: 508.98 Stator 3 exit: 510.49 Stator 4 inlet: 515.55 Stator 4 exit: 516.62 

 Stator 5 inlet: 520.41 Stator 5 exit: 521.25 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.03 

Fan Bypass Relative Humidity 4.17 

LPC Inlet Relative Humidity 4.02 

LPC Exit Relative Humidity 1.31 

HPC Relative Humidity 0.09 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 582.56 Fan/LPC Inlet Flow Velocity 193.47 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 463.14 Fan/LPC Inlet Static Temperature 488.30 

Additional Water at LPC Exit 0.0078492 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 36.00 322.90 753.8 1.1253 848.25 7.2209 582.56 7.231 0.857 10.000 1738.8 1642.0 1158.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 322.90 6.516 491.41 -14.47 0.0000 708.85 5.297 463.14 2586.1 0.5520 1.40052 0.0003043 322.80 0.098 0.0003

FS1 Inlet.Fl_O 322.90 6.516 491.41 -14.47 0.0000 708.85 6.114 482.55 4168.2 0.3029 1.40052 0.0003043 322.80 0.098 0.0003

FS12 Splitter.Fl_02 283.62 6.513 491.41 -14.47 0.0000 622.94 6.078 481.80 3531.8 0.3156 1.40052 0.0003043 283.54 0.086 0.0003

FS2 Splitter.Fl_01 39.28 6.513 491.41 -14.47 0.0000 86.27 6.369 488.30 830.5 0.1786 1.40052 0.0003043 39.27 0.012 0.0003

FS14 Fan.Fl_O 283.62 7.054 503.98 -11.46 0.0000 582.45 6.256 486.97 2606.7 0.4176 1.40038 0.0003043 283.54 0.086 0.0003

FS23 LPC.Fl_O 39.28 8.252 532.75 -4.56 0.0000 70.89 7.732 522.93 412.6 0.3064 1.39999 0.0003043 39.27 0.012 0.0003

FS24 VaporIN.Fl_O 39.59 8.252 543.34 -46.91 0.0000 72.15 7.709 532.89 412.6 0.3135 1.39876 0.0081535 39.27 0.320 0.0081

FS25 Bleed2.Fl_O 27.71 8.252 543.34 -46.91 0.0000 50.51 7.996 538.48 412.6 0.2127 1.39876 0.0081535 27.49 0.224 0.0081

FS3 HPC.Fl_O 26.37 47.121 967.79 57.00 0.0000 11.23 41.599 934.99 49.7 0.4282 1.38141 0.0081535 26.15 0.213 0.0081

FS36 Bleed3.Fl_O 20.43 47.121 967.79 57.00 0.0000 8.71 43.946 949.31 49.3 0.3192 1.38141 0.0081535 20.27 0.165 0.0081

FS4 Burner.Fl_O 20.67 46.036 1738.85 44.36 0.0116 12.08 43.458 1714.17 74.6 0.2954 1.32892 0.0081535 20.27 0.165 0.0221

FS45 HPT.Fl_O 27.62 11.915 1163.24 -56.09 0.0087 51.02 10.948 1137.27 265.4 0.3542 1.36316 0.0081535 27.16 0.221 0.0185

FS49 LPT.Fl_O 27.95 5.620 984.73 -99.91 0.0086 100.69 5.461 977.06 860.2 0.2047 1.37470 0.0081535 27.49 0.224 0.0184

FS5 TEGV.Fl_O 27.95 5.620 984.80 -99.90 0.0086 100.69 5.461 977.13 860.2 0.2047 1.37470 0.0081535 27.49 0.224 0.0184

FS8 Core_Nozz.Fl_O 27.95 5.620 984.87 -99.90 0.0086 100.70 5.297 969.08 613.4 0.2947 1.37469 0.0081535 27.49 0.224 0.0184

FS17 FanDuctLkg.Fl_O 283.62 7.054 503.98 -11.46 0.0000 582.45 6.256 486.97 2606.7 0.4176 1.40038 0.0003043 283.54 0.086 0.0003

FS171 Bleed15.Fl_O 295.50 7.054 505.57 -12.88 0.0000 607.80 6.062 484.13 2481.9 0.4703 1.40032 0.0006174 295.32 0.182 0.0006

FS172 FanDuct.Fl_O 295.50 7.054 505.57 -12.88 0.0000 607.80 6.062 484.13 2481.9 0.4703 1.40032 0.0006174 295.32 0.182 0.0006

FS173 Byp_Nozz.Fl_O 295.50 7.054 505.57 -12.88 0.0000 607.80 5.297 465.80 2006.9 0.6529 1.40032 0.0006174 295.32 0.182 0.0006

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 622.94 1.083 0.9030 2042.002 1.0256 0.9041 -1209.2 -2741.38 49.90

LPC 86.27 1.267 0.8322 2042.002 1.0841 0.8377 -551.1 6.39 2.41

HPC 50.51 5.710 0.8118 8843.919 1.7812 0.8506 -3975.2 62.22 58.48

HPT 12.08 3.864 0.8766 217.072 1.3418 0.8558 3975.1 

LPT 51.02 2.120 0.8262 58.277 1.1784 0.8106 1760.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 723.79 1.081 0.9048 2022.532 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.38 1.310 0.7607 0.539 0.0000 1.6160 0.8609 1.0940 0.0003

HPC 45.94 5.488 0.8202 8608.145 10.9695 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.784 0.8766 1.305 3.7843 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.842 0.8323 0.656 1.8424 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–89
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2586.05 5846.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0197 757.29 5.04 11.915

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3242 757.29 5.04 5.620

TEGV 0.0000 0.2047 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.02 -0.15 16.803

FanDuct 0.0000 0.4703 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 867.30 32.06 32.351

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.02 -0.15 16.803

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 967.79 57.00 47.121

Splitter 7.2209 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.02 -0.15 16.803

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9051.8 2306.5 3975.1 WB17Y Bleed> 0.3000 1.0000 1.0000 11.8758 543.34 -46.91 8.252

LP_Shaft 1987.6 4651.6 1760.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1640 967.79 57.00 46.036

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7685 967.79 57.00 26.519

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.79 57.00 47.121

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.79 57.00 47.121

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.79 57.00 47.121

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 503.98 -11.46 7.054

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 503.98 -11.46 7.054

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 503.98 -11.46 7.054

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 503.98 -11.46 7.054

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1738.79 0.9995 0.0230 0.23562 0.01163 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.061 0.9801 1.0000 0.9800 613.40 0.295 437.9 380.4

Byp_Nozz 1.332 0.9800 1.0000 0.9800 2006.86 0.653 677.2 6220.1

NASA/TM—2013-218094 K–90
************************************************************************************************************************************ 

Date:07/05/13 Time:11:42:59 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 67/ 95/ 2/64 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 505.52 Stator 1 exit: 508.54 Stator 2 inlet: 511.46 Stator 2 exit: 512.30 

 Stator 3 inlet: 515.80 Stator 3 exit: 516.28 Stator 4 inlet: 519.69 Stator 4 exit: 519.86 

 Stator 5 inlet: 521.92 Stator 5 exit: 521.88 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.02 

Fan Bypass Relative Humidity 5.15 

LPC Inlet Relative Humidity 5.19 

LPC Exit Relative Humidity 2.72 

HPC Relative Humidity 0.11 

Drop Diameter 0.0000050 Inlet Length 40.00 

Ambient Flow Velocity 528.20 Fan/LPC Inlet Flow Velocity 201.18 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.76 

Ambient Static Temperature 483.18 Fan/LPC Inlet Static Temperature 503.04 

Additional Water at LPC Exit 0.0087601 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 36.00 358.54 816.5 1.1432 933.41 6.4284 528.20 6.305 0.888 10.000 1765.8 1665.3 1187.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 358.54 7.943 506.41 -12.46 0.0000 655.46 6.740 483.18 2597.0 0.4900 1.40031 0.0005787 358.33 0.207 0.0006

FS1 Inlet.Fl_O 358.54 7.943 506.41 -12.46 0.0000 655.46 7.529 498.71 4168.2 0.2777 1.40031 0.0005787 358.33 0.207 0.0006

FS12 Splitter.Fl_02 310.27 7.939 506.41 -12.46 0.0000 567.51 7.505 498.34 3531.8 0.2844 1.40031 0.0005787 310.09 0.179 0.0006

FS2 Splitter.Fl_01 48.27 7.939 506.41 -12.46 0.0000 88.28 7.756 503.04 830.5 0.1829 1.40031 0.0005787 48.24 0.028 0.0006

FS14 Fan.Fl_O 310.27 8.498 517.40 -9.82 0.0000 535.92 7.703 503.07 2606.7 0.3772 1.40017 0.0005787 310.09 0.179 0.0006

FS23 LPC.Fl_O 48.27 9.140 535.38 -5.51 0.0000 78.85 8.414 522.86 412.6 0.3460 1.39992 0.0005787 48.24 0.028 0.0006

FS24 VaporIN.Fl_O 48.69 9.140 547.12 -52.71 0.0000 80.40 8.377 533.69 412.6 0.3553 1.39854 0.0093388 48.24 0.450 0.0093

FS25 Bleed2.Fl_O 29.21 9.140 547.12 -52.71 0.0000 48.24 8.882 542.68 412.6 0.2027 1.39854 0.0093388 28.94 0.270 0.0093

FS3 HPC.Fl_O 27.80 50.079 963.81 49.39 0.0000 11.12 44.343 931.92 49.7 0.4229 1.38147 0.0093388 27.54 0.257 0.0093

FS36 Bleed3.Fl_O 21.54 50.079 963.81 49.39 0.0000 8.62 46.776 945.80 49.3 0.3157 1.38147 0.0093388 21.34 0.199 0.0093

FS4 Burner.Fl_O 21.80 48.925 1765.81 36.30 0.0121 12.08 46.183 1740.82 74.6 0.2958 1.32715 0.0093388 21.34 0.199 0.0238

FS45 HPT.Fl_O 29.13 13.356 1191.89 -62.21 0.0091 48.59 12.381 1168.15 265.4 0.3351 1.36090 0.0093388 28.60 0.267 0.0202

FS49 LPT.Fl_O 29.47 7.037 1035.14 -100.64 0.0090 86.95 6.890 1029.23 860.2 0.1759 1.37109 0.0093388 28.94 0.270 0.0200

FS5 TEGV.Fl_O 29.47 7.037 1035.21 -100.64 0.0090 86.96 6.890 1029.30 860.2 0.1759 1.37108 0.0093388 28.94 0.270 0.0200

FS8 Core_Nozz.Fl_O 29.47 7.037 1035.28 -100.64 0.0090 86.96 6.740 1023.27 613.4 0.2514 1.37108 0.0093388 28.94 0.270 0.0200

FS17 FanDuctLkg.Fl_O 310.27 8.498 517.40 -9.82 0.0000 535.92 7.703 503.07 2606.7 0.3772 1.40017 0.0005787 310.09 0.179 0.0006

FS171 Bleed15.Fl_O 329.75 8.498 519.16 -12.36 0.0000 570.53 7.470 500.38 2481.9 0.4331 1.40008 0.0010918 329.39 0.360 0.0011

FS172 FanDuct.Fl_O 329.75 8.498 519.16 -12.36 0.0000 570.53 7.470 500.38 2481.9 0.4331 1.40008 0.0010918 329.39 0.360 0.0011

FS173 Byp_Nozz.Fl_O 329.75 8.498 519.16 -12.36 0.0000 570.53 6.740 485.89 2006.9 0.5849 1.40008 0.0010918 329.39 0.360 0.0011

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 567.51 1.070 0.9047 1834.139 1.0217 0.9056 -1157.2 -1860.24 46.48

LPC 88.28 1.151 0.7179 1834.139 1.0572 0.7235 -474.8 7.04 2.12

HPC 48.24 5.479 0.8075 8767.345 1.7616 0.8464 -4118.0 62.59 58.56 

HPT 12.08 3.663 0.8782 214.285 1.3257 0.8586 4118.1 

LPT 48.59 1.898 0.8184 52.495 1.1481 0.8047 1632.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 659.38 1.069 0.9065 1816.650 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 46.59 1.243 0.7553 0.484 0.0000 1.8950 0.6217 0.9505 0.0003

HPC 43.88 5.268 0.8159 8533.614 10.9802 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.589 0.8782 1.288 3.5895 12.6299 0.9723 1.0000 0.0003

LPT 0.74 1.675 0.8244 0.591 1.6754 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 K–91
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.98 5886.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0750 757.14 -1.66 13.356

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3418 757.14 -1.66 7.037

TEGV 0.0000 0.1759 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.25 -6.77 18.147

FanDuct 0.0000 0.4331 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.13 24.89 34.522

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.25 -6.77 18.147

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 963.81 49.39 50.079

Splitter 6.4284 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 736.25 -6.77 18.147

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9004.6 2402.0 4118.1 WB17Y Bleed> 0.4000 1.0000 1.0000 19.4753 547.12 -52.71 9.140

LP_Shaft 1812.3 4729.6 1632.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3355 963.81 49.39 48.925

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9187 963.81 49.39 28.579

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 963.81 49.39 50.079

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 963.81 49.39 50.079

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 963.81 49.39 50.079

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 517.40 -9.82 8.498

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 517.40 -9.82 8.498

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 517.40 -9.82 8.498

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 517.40 -9.82 8.498

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1765.76 0.9995 0.0230 0.25928 0.01215 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.044 0.9801 1.0000 0.9800 613.40 0.251 383.5 351.3

Byp_Nozz 1.261 0.9800 1.0000 0.9800 2006.86 0.585 619.7 6351.3

NASA/TM—2013-218094 K–92
Appendix L: Compressor code analysis for the descent conditions 

 5μm, 2 g/m3

, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.473 EfDer = 0.954 SH = 0.606659E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.560 2415.987 4.265 457.731 1.000 1.000 0.980

 W Kg/sec = 12.073 Wdry = 26.543 WH2O = 0.016 lbm/sec H2O = 0.241g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.001 2571.835 1.381 0.249 53.368 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64409.922 20835.012 3.302 831.557 251.814 619.754 2.461

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 185.90 -0.06 185.90 0.18 0.46 463.00

 MEAN 17.06 0.00 -0.02 185.90 -0.06 185.90 0.18 0.39

 HUB 12.51 0.00 -0.02 185.90 -0.06 185.90 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.86 50.47 16.39 434.95 473.07 4.17 454.96 450.39 23.17

 MEAN 62.67 47.20 15.47 359.69 404.94 4.17 454.96 450.39 23.17

 HUB 54.83 38.62 16.21 263.75 322.73 4.17 454.96 450.39 23.17

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 389.83 300.15 248.76 1051.70 0.37 7.29 6.52 16.04

 MEAN 18.04 394.43 303.39 252.05 1048.62 0.38 7.43 6.80 12.53

 HUB 15.00 427.13 341.46 256.60 1044.83 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 434.95 282.94 134.80 0.27 6193.36 0.92 0.87

 MEAN 380.26 263.51 76.87 0.25 5473.03 0.92 0.87 0.87 1.76

 HUB 316.25 257.84 25.21 0.25 5122.66 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.92 1.15 4.48 478.70 1.05 466.50 466.12 21.36

 MEAN 4.84 1.13 4.39 476.27 1.04 463.77 464.73 23.74

 HUB 4.80 1.13 4.28 475.08 1.04 460.43 464.37 27.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.35 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.28 16.96 12.70 4.26 0.95 0.52 2.22

 HUB 53.08 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 405.9388 302.7999 270.3674 1048.2174 0.3873 -0.0359 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8463 4.3761 463.4603 465.2511 25.0193 48.2386 35.4000 -12.8386

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 268.2721 65.6275 260.1210 1056.5876 0.2539 0.5158 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8343 4.6251 470.9082 464.3790 554.9116 0.0358 0.6085

 

NASA/TM—2013-218094 L–1
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 267.1900 0.0000 267.1900 1056.6049 0.2529 0.4854 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6043 470.9562 465.0048 0.0000 0.0600 0.0862 0.4712

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8149 4.8108 1.1281 476.6820 18.9521 167.8481 1.3011

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 118107.352 0.624 177.268 278605.438 0.118527E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.034 EfDer = 0.958 SH = 0.183952E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.560 2415.987 4.811 476.681 1.000 1.000 0.980

 W Kg/sec = 12.073 Wdry = 26.511 WH2O = 0.049 lbm/sec H2O = 0.782g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.800 2520.220 1.379 0.250 53.408 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60140.781 20824.904 2.590 590.487 227.969 468.502 2.055

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 244.43 -0.08 244.43 0.23 0.47 451.94

 MEAN 18.08 0.00 -0.02 244.43 -0.08 244.43 0.23 0.43

 HUB 15.21 0.00 -0.02 244.43 -0.08 244.43 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.58 46.36 14.22 433.27 497.53 4.64 471.90 467.00 35.74

 MEAN 57.33 42.30 15.03 381.15 452.86 4.64 471.90 467.00 35.74

 HUB 52.69 37.84 14.85 320.68 403.28 4.64 471.90 467.00 35.74

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 358.57 249.73 257.30 1070.57 0.33 2.33 2.04 9.02

 MEAN 18.01 358.12 246.37 259.91 1068.12 0.34 2.40 2.13 7.35

 HUB 15.22 379.48 273.74 262.82 1065.71 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 430.52 314.47 180.79 0.29 5101.26 0.92 0.88

 MEAN 379.71 292.12 133.34 0.27 4438.62 0.92 0.88 0.88 1.71

 HUB 320.95 267.03 47.22 0.25 4168.39 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.12 4.99 493.89 1.04 483.60 477.81 24.72

 MEAN 5.31 1.10 4.92 491.65 1.03 481.39 476.67 26.74

 HUB 5.28 1.10 4.84 490.74 1.03 479.22 476.50 28.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.14 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.47 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.17 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 382.9458 247.0606 292.5894 1066.9365 0.3589 -0.1068 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3217 4.8746 480.3694 477.2952 27.9882 40.1775 30.6000 -9.5775

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 283.0020 59.9984 276.5688 1072.8234 0.2638 0.3692 2.4513

 

NASA/TM—2013-218094 L–2
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3154 5.0680 485.6915 476.2392 491.5697 0.0254 0.4653

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 293.3608 0.0000 293.3608 1072.2755 0.2736 0.3568 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0341 485.2152 476.6186 0.0000 0.0600 0.0660 0.2864

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8318 5.2988 1.1014 492.0951 15.4144 188.8754 1.4642

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 96396.734 0.520 144.683 253040.859 0.212478E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.047 EfDer = 0.973 SH = 0.252869E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.560 2415.987 5.299 492.095 1.000 1.000 0.980

 W Kg/sec = 12.073 Wdry = 26.492 WH2O = 0.067 lbm/sec H2O = 1.147g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.767 2480.437 1.378 0.250 53.430 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56388.152 20819.234 2.593 545.479 210.393 424.468 2.018

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 248.09 -0.09 248.09 0.23 0.46 434.42

 MEAN 17.74 0.00 -0.02 248.09 -0.09 248.09 0.23 0.42

 HUB 15.05 0.00 -0.02 248.09 -0.09 248.09 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.62 46.36 13.26 423.15 490.58 5.11 487.18 477.31 28.18

 MEAN 56.45 43.40 13.05 373.99 448.86 5.11 487.18 477.31 28.18

 HUB 51.99 38.84 13.15 317.31 402.85 5.11 487.18 477.31 28.18

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 350.44 233.75 261.10 1086.09 0.32 2.26 1.98 8.75

 MEAN 17.51 352.00 233.50 263.40 1084.00 0.32 2.34 2.07 6.78

 HUB 14.85 375.32 264.83 265.95 1081.95 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 417.66 319.37 183.92 0.29 4632.25 0.92 0.89 

 MEAN 369.10 296.26 135.60 0.27 4089.31 0.92 0.89 0.89 1.66

 HUB 313.09 270.29 48.26 0.25 3934.03 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.86 1.11 5.46 507.68 1.03 497.88 486.39 20.89

 MEAN 5.80 1.09 5.39 505.86 1.03 495.97 485.57 22.25

 HUB 5.78 1.09 5.32 505.33 1.03 494.09 485.66 23.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.84 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.56 27.24 23.50 3.74 0.94 0.50 1.62

 HUB 44.88 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 377.9918 235.0329 296.0361 1082.7866 0.3491 -0.1148 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8080 5.3453 494.8949 486.2103 23.2779 38.4472 31.5000 -6.9472

 

NASA/TM—2013-218094 L–3
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 291.2300 63.5299 284.2162 1087.8354 0.2677 0.3185 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8039 5.5261 499.5269 485.2468 451.3937 0.0197 0.4401

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 296.1781 0.0000 296.1781 1087.5675 0.2723 0.3422 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5036 499.2961 485.6118 0.0000 0.0600 0.0526 0.2649

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8527 5.7901 1.0927 506.2917 14.1976 194.1708 1.5052

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89002.281 0.510 133.584 251496.797 0.291614E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.460 EfDer = 0.984 SH = 0.345483E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.560 2415.987 5.790 506.291 1.000 1.000 0.980

 W Kg/sec = 12.073 Wdry = 26.468 WH2O = 0.092 lbm/sec H2O = 1.665g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.619 2445.414 1.377 0.251 53.460 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53084.563 20811.600 2.627 513.330 195.414 395.845 2.026

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 248.18 -0.09 248.18 0.23 0.44 411.00

 MEAN 16.97 0.00 -0.02 248.18 -0.09 248.18 0.23 0.40

 HUB 14.32 0.00 -0.02 248.18 -0.09 248.18 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.57 46.36 12.21 406.07 475.98 5.59 501.39 486.38 23.89

 MEAN 55.26 43.80 11.46 357.80 435.52 5.59 501.39 486.38 23.89

 HUB 50.59 37.84 12.75 301.92 390.89 5.59 501.39 486.38 23.89

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 337.28 214.34 260.41 1099.93 0.31 2.16 1.89 8.34

 MEAN 16.57 338.78 214.17 262.49 1098.05 0.31 2.24 1.97 6.35

 HUB 13.89 360.65 244.89 264.76 1096.20 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.06 318.70 183.72 0.29 4048.39 0.92 0.90

 MEAN 349.43 295.30 135.26 0.27 3551.11 0.92 0.90 0.90 1.62

 HUB 292.85 269.07 47.96 0.25 3402.69 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.32 1.09 5.92 519.88 1.03 510.82 493.85 18.85

 MEAN 6.25 1.08 5.86 518.21 1.02 509.07 493.17 19.89

 HUB 6.23 1.08 5.79 517.71 1.02 507.36 493.27 20.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.46 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.21 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.77 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 359.5267 215.3763 287.8758 1097.1886 0.3277 -0.0909 2.1803

 

NASA/TM—2013-218094 L–4
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2623 5.8205 508.3182 493.7100 20.5602 36.8023 32.4000 -4.4023

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 289.0038 64.8151 281.6419 1101.0990 0.2625 0.2815 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2602 5.9721 511.9560 492.9276 432.2457 0.0152 0.4185

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.7267 0.0000 286.7267 1101.1975 0.2604 0.3285 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9656 512.0614 493.2445 0.0000 0.0600 0.0432 0.2657

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8666 6.2487 1.0792 518.5973 12.3066 209.2354 1.6220

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 77383.781 0.488 116.146 257395.641 0.395095E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.000 EfDer = 0.991 SH = 0.464951E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.560 2415.987 6.249 518.597 1.000 1.000 0.980

 W Kg/sec = 12.073 Wdry = 26.436 WH2O = 0.123 lbm/sec H2O = 2.366g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.475 2416.227 1.375 0.252 53.499 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 50274.684 20801.719 2.779 509.668 183.393 384.739 2.098

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.73 -0.08 236.73 0.21 0.41 386.28

 MEAN 15.91 0.00 -0.02 236.73 -0.08 236.73 0.21 0.37

 HUB 13.07 0.00 -0.02 236.73 -0.08 236.73 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.50 47.36 11.14 386.25 453.09 6.05 514.15 494.11 21.57

 MEAN 54.80 44.80 10.00 335.50 410.68 6.05 514.15 494.11 21.57

 HUB 49.34 38.84 10.50 275.56 363.34 6.05 514.15 494.11 21.57

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 320.25 201.41 248.98 1112.27 0.29 2.05 1.78 7.43

 MEAN 15.50 318.91 196.72 251.01 1110.33 0.29 2.13 1.86 5.75

 HUB 12.59 335.08 219.52 253.17 1108.42 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.24 305.38 176.82 0.27 3614.85 0.92 0.91

 MEAN 326.74 282.68 130.02 0.25 3049.99 0.92 0.91 0.91 1.61

 HUB 265.44 257.30 45.92 0.23 2764.77 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.75 1.08 6.38 530.68 1.02 522.55 500.46 17.72

 MEAN 6.67 1.07 6.30 528.79 1.02 520.73 499.70 18.67

 HUB 6.63 1.06 6.23 527.84 1.02 518.94 499.56 19.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.97 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 38.09 27.38 23.50 3.88 0.94 0.46 1.64

 HUB 40.93 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.495 73.000

 

NASA/TM—2013-218094 L–5
 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 348.9193 200.3273 285.6810 1108.9277 0.3146 -0.1705 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6725 6.2373 519.4558 500.3346 19.5371 35.0392 33.0000 -2.0392

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 291.8725 66.6493 284.1609 1112.0034 0.2625 0.1641 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6703 6.3634 522.3494 499.6414 410.5396 0.0256 0.3940

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 283.9220 0.0000 283.9220 1112.3629 0.2552 0.3174 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3754 522.6993 499.8043 0.0000 0.0600 0.0380 0.1958

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8784 6.6656 1.0667 529.0839 10.5072 228.6056 1.7721

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66317.984 0.464 99.537 270028.719 0.515160E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10474E+00 0.14799E+00 0.30129E+00

 trTOT = 1.1559 Tt4 = 529.0839 T1 = 457.7312

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 447208.13 671.2178 86.0007 1.5630 0.8352 15.4729 1.1559 37.3740

NASA/TM—2013-218094 L–6
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.521 EfDer = 0.954 SH = 0.525093E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.637 2339.179 4.199 451.558 1.000 1.000 0.980

 W Kg/sec = 11.653 Wdry = 25.624 WH2O = 0.013 lbm/sec H2O = 0.208g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.737 2507.039 1.381 0.249 53.365 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62233.523 20112.225 3.392 831.557 245.171 619.754 2.528

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 179.62 -0.06 179.62 0.17 0.44 451.33

 MEAN 17.06 0.00 -0.02 179.62 -0.06 179.62 0.17 0.38

 HUB 12.51 0.00 -0.02 179.62 -0.06 179.62 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.90 50.47 16.43 421.12 457.89 4.11 448.97 445.81 26.48

 MEAN 62.72 47.20 15.52 348.25 391.90 4.11 448.97 445.81 26.48

 HUB 54.89 38.62 16.27 255.37 312.26 4.11 448.97 445.81 26.48

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 377.49 290.60 240.94 1044.12 0.36 7.29 6.52 16.04

 MEAN 18.04 381.88 293.80 243.96 1041.22 0.37 7.43 6.80 12.53

 HUB 15.00 413.35 330.60 248.13 1037.65 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 421.12 274.02 130.53 0.26 5996.31 0.92 0.87

 MEAN 368.17 255.04 74.37 0.24 5300.10 0.92 0.87 0.87 1.76

 HUB 306.20 249.32 24.40 0.24 4959.74 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.14 4.40 471.23 1.04 459.78 461.16 24.18

 MEAN 4.73 1.13 4.32 468.94 1.04 457.23 459.76 26.79

 HUB 4.70 1.12 4.22 467.83 1.04 454.10 459.36 30.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.34 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.30 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 53.11 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 392.9876 293.2325 261.6371 1040.8489 0.3776 -0.0360 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7420 4.3032 456.9316 460.2479 28.1568 48.2590 35.4000 -12.8590

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 260.1176 63.6327 252.2143 1048.7365 0.2480 0.5156 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7312 4.5356 463.8984 459.4772 554.9116 0.0349 0.6076

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 259.0318 0.0000 259.0318 1048.7528 0.2470 0.4843 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5158 463.9449 460.0240 0.0000 0.0600 0.0863 0.4701

NASA/TM—2013-218094 L–7
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8146 4.7088 1.1213 469.3294 17.7728 167.6924 1.2999

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 110701.625 0.624 160.384 271492.875 0.989312E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.997 EfDer = 0.958 SH = 0.150855E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.637 2339.179 4.709 469.329 1.000 1.000 0.980

 W Kg/sec = 11.653 Wdry = 25.599 WH2O = 0.039 lbm/sec H2O = 0.639g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.131 2459.137 1.380 0.249 53.397 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58312.637 20104.445 2.648 590.487 223.031 468.502 2.101 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 237.00 -0.08 237.00 0.23 0.46 440.99

 MEAN 18.08 0.00 -0.02 237.00 -0.08 237.00 0.23 0.42

 HUB 15.21 0.00 -0.02 237.00 -0.08 237.00 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.54 46.36 14.18 419.49 481.88 4.55 464.83 461.75 39.52

 MEAN 57.30 42.30 15.00 369.03 438.65 4.55 464.83 461.75 39.52

 HUB 52.65 37.84 14.81 310.48 390.67 4.55 464.83 461.75 39.52

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 347.44 241.15 250.12 1061.94 0.33 2.33 2.04 9.02

 MEAN 18.01 347.10 238.15 252.52 1059.64 0.33 2.40 2.13 7.35

 HUB 15.22 367.87 264.96 255.19 1057.37 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 416.84 305.65 175.68 0.29 4926.04 0.92 0.88

 MEAN 367.64 283.78 129.49 0.27 4290.52 0.92 0.88 0.88 1.70

 HUB 310.75 259.27 45.79 0.25 4034.75 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.24 1.11 4.87 485.44 1.03 475.77 472.43 27.61

 MEAN 5.17 1.10 4.81 483.36 1.03 473.71 471.29 29.79

 HUB 5.14 1.09 4.74 482.52 1.03 471.68 471.09 32.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.95 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.32 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.08 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.2020 238.8170 284.1784 1058.5104 0.3507 -0.1074 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1836 4.7667 472.7407 471.8717 31.1569 40.0429 30.6000 -9.4429

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 275.2576 58.3566 269.0005 1064.0476 0.2587 0.3661 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1780 4.9459 477.7062 470.9476 491.5697 0.0245 0.4623

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 285.2620 0.0000 285.2620 1063.5250 0.2682 0.3541 0.5911

NASA/TM—2013-218094 L–8
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9143 477.2583 471.2844 0.0000 0.0600 0.0653 0.2831

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8325 5.1625 1.0964 483.7713 14.4432 189.2462 1.4670

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90216.125 0.519 130.704 246803.563 0.173571E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.924 EfDer = 0.974 SH = 0.205751E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.637 2339.179 5.163 483.771 1.000 1.000 0.980

 W Kg/sec = 11.653 Wdry = 25.585 WH2O = 0.053 lbm/sec H2O = 0.926g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.500 2422.153 1.379 0.250 53.415 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54851.598 20100.094 2.640 545.479 206.617 424.468 2.054

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 241.33 -0.08 241.33 0.23 0.45 424.21

 MEAN 17.74 0.00 -0.02 241.33 -0.08 241.33 0.23 0.41

 HUB 15.05 0.00 -0.02 241.33 -0.08 241.33 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.50 46.36 13.14 409.69 475.56 4.98 479.12 471.89 31.39

 MEAN 56.32 43.40 12.92 362.10 435.22 4.98 479.12 471.89 31.39

 HUB 51.86 38.84 13.02 307.22 390.74 4.98 479.12 471.89 31.39

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.85 225.15 254.57 1076.57 0.32 2.26 1.98 8.75

 MEAN 17.51 341.51 225.25 256.69 1074.61 0.32 2.34 2.07 6.78

 HUB 14.85 364.31 256.17 259.04 1072.69 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.39 311.34 179.24 0.29 4461.79 0.92 0.89

 MEAN 357.36 288.70 132.11 0.27 3944.89 0.92 0.89 0.89 1.65

 HUB 303.14 263.26 46.97 0.25 3805.33 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.68 1.10 5.31 498.33 1.03 489.10 480.85 23.47

 MEAN 5.62 1.09 5.25 496.64 1.03 487.32 480.04 24.95

 HUB 5.61 1.09 5.18 496.19 1.03 485.58 480.11 26.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.49 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 41.27 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.68 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.8695 226.7319 288.4196 1073.4431 0.3418 -0.1157 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6337 5.2024 486.3018 480.6352 26.0924 38.1715 31.5000 -6.6715

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 284.1002 61.9745 277.2581 1078.1783 0.2635 0.3124 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6302 5.3688 490.6068 479.7896 451.3937 0.0188 0.4349

 

NASA/TM—2013-218094 L–9
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.8762 0.0000 288.8762 1077.9221 0.2680 0.3375 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3479 490.3892 480.1172 0.0000 0.0600 0.0514 0.2591

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8542 5.6175 1.0881 497.0549 13.2845 195.1314 1.5126

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83145.398 0.508 120.460 245587.328 0.236783E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.255 EfDer = 0.985 SH = 0.279714E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.637 2339.179 5.617 497.054 1.000 1.000 0.980

 W Kg/sec = 11.653 Wdry = 25.566 WH2O = 0.072 lbm/sec H2O = 1.334g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.674 2389.568 1.378 0.250 53.439 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51790.215 20094.219 2.666 513.330 192.565 395.845 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 242.13 -0.08 242.13 0.22 0.43 401.62

 MEAN 16.97 0.00 -0.02 242.13 -0.08 242.13 0.22 0.39

 HUB 14.32 0.00 -0.02 242.13 -0.08 242.13 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.38 46.36 12.02 393.16 461.81 5.43 492.38 480.80 26.80

 MEAN 55.06 43.80 11.26 346.43 422.72 5.43 492.38 480.80 26.80

 HUB 50.37 37.84 12.53 292.32 379.64 5.43 492.38 480.80 26.80

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.40 205.85 254.59 1089.61 0.30 2.16 1.89 8.34

 MEAN 16.57 329.09 206.17 256.50 1087.85 0.30 2.24 1.97 6.35

 HUB 13.89 350.60 236.75 258.59 1086.12 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 385.40 311.53 179.55 0.29 3888.11 0.92 0.90

 MEAN 338.33 288.55 132.16 0.27 3418.43 0.92 0.90 0.90 1.61

 HUB 283.54 262.79 46.79 0.24 3289.62 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.10 1.09 5.74 509.71 1.03 501.16 488.14 21.28

 MEAN 6.04 1.08 5.68 508.18 1.02 499.55 487.47 22.42

 HUB 6.03 1.07 5.61 507.76 1.02 497.96 487.56 23.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.96 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.79 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.47 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.4142 207.3283 281.2565 1087.0186 0.3214 -0.0920 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0527 5.6408 498.8231 487.9801 23.1786 36.3958 32.4000 -3.9958

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 282.6620 63.3928 275.4617 1090.6696 0.2592 0.2729 2.2705

 

NASA/TM—2013-218094 L–10
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0510 5.7791 502.1862 487.2925 432.2457 0.0145 0.4114

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.4081 0.0000 280.4081 1090.7667 0.2571 0.3218 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7733 502.2882 487.5758 0.0000 0.0600 0.0420 0.2577

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8683 6.0405 1.0753 508.5531 11.4991 210.8906 1.6348

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72149.695 0.486 104.530 251610.672 0.319301E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.724 EfDer = 0.993 SH = 0.374510E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.637 2339.179 6.040 508.553 1.000 1.000 0.980

 W Kg/sec = 11.653 Wdry = 25.541 WH2O = 0.096 lbm/sec H2O = 1.881g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.778 2362.400 1.377 0.251 53.470 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49174.984 20086.668 2.812 509.668 181.246 384.739 2.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.55 -0.08 231.55 0.21 0.40 377.67

 MEAN 15.91 0.00 -0.02 231.55 -0.08 231.55 0.21 0.37

 HUB 13.07 0.00 -0.02 231.55 -0.08 231.55 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.24 47.36 10.88 373.97 439.92 5.86 504.29 488.34 24.28

 MEAN 54.52 44.80 9.72 324.84 398.98 5.86 504.29 488.34 24.28

 HUB 49.05 38.84 10.21 266.80 353.33 5.86 504.29 488.34 24.28

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 311.06 192.96 243.98 1101.25 0.28 2.05 1.78 7.43

 MEAN 15.50 310.11 189.01 245.85 1099.44 0.28 2.13 1.86 5.75

 HUB 12.59 326.18 212.05 247.85 1097.66 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.21 299.24 173.26 0.27 3463.12 0.92 0.91

 MEAN 316.36 276.88 127.35 0.25 2930.44 0.92 0.91 0.91 1.59

 HUB 257.00 251.89 44.95 0.23 2670.76 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.50 1.08 6.15 519.79 1.02 512.10 494.60 20.16

 MEAN 6.42 1.06 6.08 518.06 1.02 510.42 493.86 21.22

 HUB 6.39 1.06 6.02 517.22 1.02 508.76 493.72 22.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.34 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.55 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.55 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.5710 192.4738 279.7540 1098.0837 0.3092 -0.1725 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4294 6.0234 509.1985 494.4615 22.2171 34.5284 33.0000 -1.5284

 

NASA/TM—2013-218094 L–11
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 286.0689 65.3241 278.5107 1100.9413 0.2598 0.1530 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4277 6.1377 511.8587 493.8746 410.5396 0.0248 0.3855

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.3039 0.0000 278.3039 1101.3036 0.2527 0.3086 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1487 512.2079 494.1189 0.0000 0.0600 0.0374 0.1843

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8779 6.4233 1.0634 518.3599 9.8076 231.0067 1.7907

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 61726.660 0.460 89.429 264194.156 0.422858E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1479 Tt4 = 518.3599 T1 = 451.5578

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 417939.50 605.5077 83.7369 1.5296 0.8363 15.5212 1.1479 37.3740

NASA/TM—2013-218094 L–12
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.536 EfDer = 0.954 SH = 0.474490E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.247 2309.625 4.337 449.669 1.000 1.000 0.980

 W Kg/sec = 11.931 Wdry = 26.235 WH2O = 0.012 lbm/sec H2O = 0.195g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.829 2480.558 1.381 0.249 53.364 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61407.070 20590.938 3.429 831.557 242.505 619.754 2.556

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 177.23 -0.06 177.23 0.17 0.44 446.56

 MEAN 17.06 0.00 -0.02 177.23 -0.06 177.23 0.17 0.38

 HUB 12.51 0.00 -0.02 177.23 -0.06 177.23 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.92 50.47 16.45 415.80 452.05 4.25 447.14 444.47 27.07

 MEAN 62.74 47.20 15.54 343.85 386.89 4.25 447.14 444.47 27.07

 HUB 54.90 38.62 16.28 252.14 308.25 4.25 447.14 444.47 27.07

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 372.75 286.90 237.97 1041.74 0.36 7.29 6.52 16.04

 MEAN 18.04 377.07 290.10 240.88 1038.91 0.36 7.43 6.80 12.53

 HUB 15.00 408.07 326.41 244.91 1035.43 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.80 270.64 128.91 0.26 5919.97 0.92 0.87

 MEAN 363.52 251.83 73.42 0.24 5233.25 0.92 0.87 0.87 1.76

 HUB 302.33 246.09 24.08 0.24 4896.89 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.54 468.84 1.04 457.68 459.66 24.72

 MEAN 4.88 1.12 4.46 466.62 1.04 455.19 458.26 27.35

 HUB 4.84 1.12 4.36 465.53 1.04 452.15 457.82 30.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.33 28.44 24.20 4.24 0.93 0.58 1.80

 MEAN 50.30 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 53.12 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 388.0211 289.5343 258.3220 1038.5487 0.3736 -0.0361 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8854 4.4421 454.9065 458.7192 28.7176 48.2607 35.4000 -12.8607

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 257.0236 62.8758 249.2143 1046.2495 0.2457 0.5154 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8746 4.6767 461.6917 458.0149 554.9116 0.0346 0.6072

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.9350 0.0000 255.9350 1046.2672 0.2446 0.4838 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6566 461.7376 458.5148 0.0000 0.0600 0.0863 0.4695

NASA/TM—2013-218094 L–13
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8145 4.8518 1.1187 466.9955 17.3281 167.6538 1.2996

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 107908.008 0.624 160.054 278742.094 0.884372E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.977 EfDer = 0.959 SH = 0.134262E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.247 2309.625 4.852 466.995 1.000 1.000 0.980

 W Kg/sec = 11.931 Wdry = 26.212 WH2O = 0.035 lbm/sec H2O = 0.589g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.456 2434.127 1.380 0.249 53.392 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57618.277 20583.910 2.671 590.487 221.032 468.502 2.120

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 234.18 -0.08 234.18 0.22 0.45 436.51

 MEAN 18.08 0.00 -0.02 234.18 -0.08 234.18 0.22 0.41

 HUB 15.21 0.00 -0.02 234.18 -0.08 234.18 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.52 46.36 14.16 414.19 475.88 4.69 462.60 460.09 40.18

 MEAN 57.28 42.30 14.98 364.37 433.20 4.69 462.60 460.09 40.18

 HUB 52.63 37.84 14.79 306.56 385.84 4.69 462.60 460.09 40.18

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 343.17 237.84 247.39 1059.16 0.32 2.33 2.04 9.02

 MEAN 18.01 342.86 234.94 249.71 1056.91 0.32 2.40 2.13 7.35

 HUB 15.22 363.42 261.57 252.30 1054.70 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 411.57 302.30 173.74 0.29 4858.25 0.92 0.88

 MEAN 363.00 280.63 128.05 0.27 4232.78 0.92 0.88 0.88 1.70

 HUB 306.82 256.32 45.25 0.24 3983.10 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.11 5.02 482.69 1.03 473.25 470.77 28.23

 MEAN 5.32 1.10 4.95 480.67 1.03 471.25 469.62 30.42

 HUB 5.29 1.09 4.88 479.86 1.03 469.28 469.39 32.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.87 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.25 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.03 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.959 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.6893 235.6029 280.9845 1055.8052 0.3473 -0.1076 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3305 4.9095 470.3016 470.1701 31.8046 39.9795 30.6000 -9.3795

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 272.3209 57.7340 266.1305 1061.2063 0.2566 0.3647 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3251 5.0900 475.1318 469.3230 491.5697 0.0241 0.4609

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 282.1897 0.0000 282.1897 1060.6942 0.2660 0.3528 0.5911

NASA/TM—2013-218094 L–14
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0580 474.6944 469.6338 0.0000 0.0600 0.0649 0.2816

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8328 5.3094 1.0943 481.0714 14.0771 189.4269 1.4684

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87882.336 0.519 130.351 253485.516 0.154306E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.870 EfDer = 0.975 SH = 0.182724E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.247 2309.625 5.309 481.071 1.000 1.000 0.980

 W Kg/sec = 11.931 Wdry = 26.199 WH2O = 0.048 lbm/sec H2O = 0.851g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.984 2398.252 1.379 0.250 53.408 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54268.566 20579.979 2.660 545.479 205.077 424.468 2.070

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 238.77 -0.08 238.77 0.22 0.44 420.03

 MEAN 17.74 0.00 -0.02 238.77 -0.08 238.77 0.22 0.40

 HUB 15.05 0.00 -0.02 238.77 -0.08 238.77 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.45 46.36 13.09 404.52 469.80 5.13 476.51 470.20 32.09

 MEAN 56.27 43.40 12.87 357.52 429.99 5.13 476.51 470.20 32.09

 HUB 51.80 38.84 12.96 303.34 386.10 5.13 476.51 470.20 32.09

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.77 221.78 252.10 1073.44 0.31 2.26 1.98 8.75

 MEAN 17.51 337.51 222.08 254.15 1071.53 0.31 2.34 2.07 6.78

 HUB 14.85 360.09 252.82 256.42 1069.66 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 399.28 308.32 177.50 0.29 4395.04 0.92 0.89

 MEAN 352.85 285.82 130.77 0.27 3889.33 0.92 0.89 0.89 1.65

 HUB 299.31 260.60 46.49 0.24 3755.56 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.83 1.10 5.46 495.24 1.03 486.22 479.14 24.10

 MEAN 5.77 1.09 5.39 493.61 1.03 484.50 478.32 25.59

 HUB 5.76 1.08 5.33 493.18 1.03 482.81 478.37 27.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.34 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 41.15 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.59 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 362.6283 223.5383 285.5345 1070.3843 0.3388 -0.1163 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7836 5.3481 483.4976 478.8947 26.7633 38.0566 31.5000 -6.5566

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 281.4019 61.3859 274.6248 1074.9990 0.2618 0.3098 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7803 5.5152 487.6805 478.1164 451.3937 0.0185 0.4327

 

NASA/TM—2013-218094 L–15
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 286.1122 0.0000 286.1122 1074.7474 0.2662 0.3355 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4942 487.4676 478.4207 0.0000 0.0600 0.0510 0.2566

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8548 5.7675 1.0863 494.0114 12.9409 195.5527 1.5159

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 80934.438 0.508 120.046 252355.641 0.210134E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.169 EfDer = 0.985 SH = 0.248032E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.247 2309.625 5.767 494.011 1.000 1.000 0.980

 W Kg/sec = 11.931 Wdry = 26.182 WH2O = 0.065 lbm/sec H2O = 1.222g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.287 2366.634 1.378 0.250 53.429 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51300.188 20574.670 2.682 513.330 191.391 395.845 2.068

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 239.84 -0.08 239.84 0.22 0.42 397.76

 MEAN 16.97 0.00 -0.02 239.84 -0.08 239.84 0.22 0.39

 HUB 14.32 0.00 -0.02 239.84 -0.08 239.84 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.30 46.36 11.94 388.19 456.38 5.57 489.42 479.06 27.51

 MEAN 54.97 43.80 11.17 342.05 417.82 5.57 489.42 479.06 27.51

 HUB 50.28 37.84 12.44 288.62 375.33 5.57 489.42 479.06 27.51

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.61 202.55 252.39 1086.17 0.30 2.16 1.89 8.34

 MEAN 16.57 325.40 203.10 254.24 1084.46 0.30 2.24 1.97 6.35

 HUB 13.89 346.74 233.57 256.26 1082.78 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 380.53 308.83 177.98 0.28 3825.69 0.92 0.90

 MEAN 334.05 285.98 130.96 0.26 3367.48 0.92 0.90 0.90 1.60

 HUB 279.96 260.42 46.38 0.24 3245.52 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.25 1.08 5.89 506.32 1.02 497.96 486.38 21.93

 MEAN 6.19 1.07 5.82 504.85 1.02 496.39 485.70 23.08

 HUB 6.18 1.07 5.76 504.45 1.02 494.86 485.78 24.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.75 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.62 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.35 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 345.5694 204.2378 278.7564 1083.6422 0.3189 -0.0926 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2048 5.7888 495.6795 486.1928 23.8648 36.2293 32.4000 -3.8293

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 280.2689 62.8561 273.1296 1087.1938 0.2578 0.2692 2.2705

 

NASA/TM—2013-218094 L–16
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2032 5.9273 498.9402 485.5586 432.2457 0.0142 0.4086

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 278.0236 0.0000 278.0236 1087.2904 0.2557 0.3190 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9215 499.0410 485.8219 0.0000 0.0600 0.0416 0.2543

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8690 6.1927 1.0737 505.2062 11.1957 211.5966 1.6403

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 70175.383 0.485 104.087 258652.172 0.282959E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.609 EfDer = 0.993 SH = 0.331577E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.247 2309.625 6.193 505.206 1.000 1.000 0.980

 W Kg/sec = 11.931 Wdry = 26.160 WH2O = 0.087 lbm/sec H2O = 1.719g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.489 2340.266 1.377 0.251 53.456 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48759.922 20567.867 2.826 509.668 180.353 384.739 2.133

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 229.60 -0.08 229.60 0.21 0.40 374.13

 MEAN 15.91 0.00 -0.02 229.60 -0.08 229.60 0.21 0.36

 HUB 13.07 0.00 -0.02 229.60 -0.08 229.60 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.13 47.36 10.77 369.24 434.87 6.01 501.01 486.53 25.01

 MEAN 54.41 44.80 9.61 320.73 394.51 6.01 501.01 486.53 25.01

 HUB 48.93 38.84 10.09 263.43 349.50 6.01 501.01 486.53 25.01

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 307.55 189.67 242.10 1097.55 0.28 2.05 1.78 7.43

 MEAN 15.50 306.75 186.02 243.91 1095.79 0.28 2.13 1.86 5.75

 HUB 12.59 322.81 209.20 245.84 1094.05 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 361.59 296.93 171.92 0.27 3404.06 0.92 0.91

 MEAN 312.36 274.69 126.34 0.25 2884.15 0.92 0.91 0.91 1.59

 HUB 253.75 249.85 44.56 0.23 2634.85 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.65 1.07 6.30 516.13 1.02 508.60 492.77 20.81

 MEAN 6.58 1.06 6.23 514.46 1.02 506.97 492.02 21.89

 HUB 6.54 1.06 6.17 513.66 1.02 505.37 491.87 23.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.08 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.33 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.40 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 336.0084 189.4326 277.5192 1094.4509 0.3070 -0.1734 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5828 6.1728 505.7682 492.5963 22.9252 34.3172 33.0000 -1.3172

 

NASA/TM—2013-218094 L–17
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 283.8880 64.8261 276.3874 1097.2225 0.2587 0.1481 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5812 6.2866 508.3392 492.0547 410.5396 0.0245 0.3820

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 276.1844 0.0000 276.1844 1097.5820 0.2516 0.3050 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2978 508.6833 492.2807 0.0000 0.0600 0.0372 0.1796

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8784 6.5767 1.0620 514.7505 9.5450 232.0312 1.7987

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59992.230 0.459 88.983 271682.719 0.374084E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1447 Tt4 = 514.7505 T1 = 449.6686 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 406892.38 603.5221 82.8288 1.5163 0.8368 15.5364 1.1447 37.3740

NASA/TM—2013-218094 L–18
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34381 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.576 EfDer = 0.954 SH = 0.469029E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.226 2242.253 4.829 451.603 1.000 1.000 0.980

 W Kg/sec = 12.830 Wdry = 28.213 WH2O = 0.013 lbm/sec H2O = 0.214g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.180 2403.042 1.381 0.249 53.364 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59513.656 22143.674 3.542 831.557 234.752 619.754 2.640

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 171.77 -0.06 171.77 0.17 0.43 432.61

 MEAN 17.06 0.00 -0.02 171.77 -0.06 171.77 0.17 0.36

 HUB 12.51 0.00 -0.02 171.77 -0.06 171.77 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.95 50.47 16.48 403.67 438.75 4.74 449.23 446.42 26.89

 MEAN 62.78 47.20 15.58 333.82 375.47 4.74 449.23 446.42 26.89

 HUB 54.95 38.62 16.33 244.79 299.09 4.74 449.23 446.42 26.89

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 361.97 278.46 231.27 1043.38 0.35 7.29 6.52 16.04

 MEAN 18.04 366.12 281.64 233.92 1040.73 0.35 7.43 6.80 12.53

 HUB 15.00 396.02 316.85 237.57 1037.46 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 403.67 262.99 125.22 0.25 5745.78 0.92 0.87

 MEAN 352.92 244.53 71.27 0.23 5080.76 0.92 0.87 0.87 1.76

 HUB 293.51 238.71 23.34 0.23 4753.47 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 469.67 1.04 459.14 460.84 24.89

 MEAN 5.39 1.12 4.95 467.58 1.04 456.81 459.49 27.34

 HUB 5.35 1.11 4.85 466.55 1.03 453.95 459.06 30.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.29 28.43 24.20 4.23 0.93 0.58 1.80

 MEAN 50.29 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 53.14 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 376.7225 281.0977 250.8065 1040.3842 0.3621 -0.0363 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3996 4.9378 456.5353 459.9243 28.6589 48.2594 35.4000 -12.8594

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 250.1091 61.1843 242.5099 1047.6058 0.2387 0.5148 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3889 5.1820 462.9077 459.2938 554.9116 0.0335 0.6058

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 249.0055 0.0000 249.0055 1047.6262 0.2377 0.4824 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1606 462.9528 459.7516 0.0000 0.0600 0.0863 0.4680

NASA/TM—2013-218094 L–19
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8142 5.3647 1.1110 467.9297 16.3282 167.5300 1.2987

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 101688.375 0.624 162.202 298492.000 0.848283E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.914 EfDer = 0.959 SH = 0.126947E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.226 2242.253 5.365 467.929 1.000 1.000 0.980

 W Kg/sec = 12.830 Wdry = 28.190 WH2O = 0.036 lbm/sec H2O = 0.615g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.462 2360.764 1.380 0.249 53.389 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56072.465 22136.705 2.744 590.487 215.186 468.502 2.177

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 227.90 -0.08 227.90 0.22 0.44 423.35

 MEAN 18.08 0.00 -0.02 227.90 -0.08 227.90 0.22 0.40

 HUB 15.21 0.00 -0.02 227.90 -0.08 227.90 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.46 46.36 14.10 402.11 462.27 5.19 463.77 461.22 39.88

 MEAN 57.21 42.30 14.91 353.74 420.86 5.19 463.77 461.22 39.88

 HUB 52.56 37.84 14.72 297.62 374.91 5.19 463.77 461.22 39.88

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 333.51 230.07 241.45 1059.71 0.31 2.33 2.04 9.02

 MEAN 18.01 333.34 227.57 243.57 1057.61 0.32 2.40 2.13 7.35

 HUB 15.22 353.37 253.76 245.92 1055.55 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 399.57 295.01 169.50 0.28 4699.58 0.92 0.88

 MEAN 352.41 273.70 124.84 0.26 4099.92 0.92 0.88 0.88 1.69

 HUB 297.87 249.85 44.12 0.24 3864.12 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.92 1.10 5.54 482.67 1.03 473.75 471.41 28.74

 MEAN 5.85 1.09 5.47 480.79 1.03 471.88 470.31 30.81

 HUB 5.82 1.09 5.39 480.05 1.03 470.04 470.09 32.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.62 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 43.06 27.14 23.50 3.64 0.95 0.52 1.63

 HUB 45.90 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.959 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 356.5721 228.2076 273.9798 1056.5616 0.3375 -0.1084 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8606 5.4223 470.9820 470.8289 32.1452 39.7921 30.6000 -9.1921

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 265.9677 56.3870 259.9218 1061.6117 0.2505 0.3604 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8553 5.6086 475.5006 470.0739 491.5697 0.0231 0.4568

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 275.5255 0.0000 275.5255 1061.1287 0.2597 0.3492 0.5911

NASA/TM—2013-218094 L–20
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5753 475.0867 470.3568 0.0000 0.0600 0.0639 0.2772

 

 STAGE EXIT CONDITIONS, STAGE 2 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8337 5.8390 1.0884 481.1671 13.2386 189.9893 1.4728

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 82636.063 0.518 131.812 271802.719 0.145060E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.706 EfDer = 0.976 SH = 0.170557E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.226 2242.253 5.839 481.167 1.000 1.000 0.980

 W Kg/sec = 12.830 Wdry = 28.178 WH2O = 0.048 lbm/sec H2O = 0.875g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.442 2328.064 1.379 0.250 53.404 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53012.156 22132.902 2.720 545.479 200.544 424.468 2.117

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 233.24 -0.08 233.24 0.22 0.43 407.73

 MEAN 17.74 0.00 -0.02 233.24 -0.08 233.24 0.22 0.39

 HUB 15.05 0.00 -0.02 233.24 -0.08 233.24 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.30 46.36 12.94 392.72 456.83 5.65 476.81 470.88 32.56

 MEAN 56.11 43.40 12.71 347.10 418.25 5.65 476.81 470.88 32.56

 HUB 51.63 38.84 12.79 294.49 375.73 5.65 476.81 470.88 32.56

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 326.65 213.85 246.92 1073.08 0.30 2.26 1.98 8.75

 MEAN 17.51 328.54 214.58 248.79 1071.31 0.31 2.34 2.07 6.78

 HUB 14.85 350.73 245.11 250.86 1069.57 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 387.63 301.94 173.78 0.28 4238.01 0.92 0.89

 MEAN 342.56 279.77 127.98 0.26 3757.97 0.92 0.89 0.89 1.64

 HUB 290.58 254.95 45.46 0.24 3641.12 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.38 1.09 5.99 494.44 1.03 485.90 479.44 24.95

 MEAN 6.32 1.08 5.92 492.93 1.02 484.30 478.66 26.38

 HUB 6.30 1.08 5.85 492.57 1.02 482.73 478.71 27.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.90 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 40.78 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.34 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.1718 215.9873 279.4277 1070.2128 0.3300 -0.1175 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3279 5.8747 483.3368 479.1955 27.5369 37.7027 31.5000 -6.2027

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 275.7898 60.1617 269.1479 1074.5090 0.2567 0.3020 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3249 6.0457 487.2297 478.5026 451.3937 0.0175 0.4262

 

NASA/TM—2013-218094 L–21
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 280.3497 0.0000 280.3497 1074.2706 0.2610 0.3295 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0240 487.0276 478.7791 0.0000 0.0600 0.0495 0.2492

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8565 6.3117 1.0810 493.3127 12.1465 196.8181 1.5257

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75940.727 0.505 121.133 271009.813 0.194823E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.909 EfDer = 0.987 SH = 0.228221E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.226 2242.253 6.312 493.312 1.000 1.000 0.980

 W Kg/sec = 12.830 Wdry = 28.162 WH2O = 0.064 lbm/sec H2O = 1.234g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.110 2299.226 1.378 0.250 53.422 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50286.730 22127.863 2.732 513.330 187.921 395.845 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 235.10 -0.08 235.10 0.22 0.41 386.43

 MEAN 16.97 0.00 -0.02 235.10 -0.08 235.10 0.22 0.38

 HUB 14.32 0.00 -0.02 235.10 -0.08 235.10 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.05 46.36 11.69 376.87 444.26 6.11 488.90 479.36 28.34

 MEAN 54.71 43.80 10.91 332.07 406.94 6.11 488.90 479.36 28.34

 HUB 50.01 37.84 12.17 280.20 365.83 6.11 488.90 479.36 28.34

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 315.22 194.59 247.99 1084.99 0.29 2.16 1.89 8.34

 MEAN 16.57 317.25 195.74 249.67 1083.41 0.29 2.24 1.97 6.35

 HUB 13.89 338.34 226.29 251.52 1081.86 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 369.43 303.43 174.84 0.28 3675.37 0.92 0.90 

 MEAN 324.31 280.83 128.57 0.26 3245.52 0.92 0.90 0.90 1.59

 HUB 271.79 255.60 45.50 0.24 3144.40 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.81 1.08 6.43 504.80 1.02 496.86 486.37 22.94

 MEAN 6.75 1.07 6.36 503.46 1.02 495.42 485.73 24.06

 HUB 6.74 1.07 6.30 503.14 1.02 494.00 485.82 25.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.12 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.10 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 41.98 10.25 6.50 3.75 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 337.1349 196.8394 273.7046 1082.6199 0.3114 -0.0941 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7603 6.3272 494.7251 486.1926 24.8493 35.7225 32.4000 -3.3224

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 275.5294 61.7932 268.5108 1085.9061 0.2537 0.2583 2.2705

 

NASA/TM—2013-218094 L–22
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7590 6.4674 497.7382 485.6314 432.2457 0.0135 0.3999

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 273.2949 0.0000 273.2949 1086.0015 0.2517 0.3106 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4617 497.8368 485.8696 0.0000 0.0600 0.0404 0.2442

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8709 6.7482 1.0691 503.7977 10.4859 213.7209 1.6568

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65687.422 0.481 104.778 278157.750 0.258720E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.263 EfDer = 0.995 SH = 0.301009E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.226 2242.253 6.748 503.797 1.000 1.000 0.980

 W Kg/sec = 12.830 Wdry = 28.141 WH2O = 0.085 lbm/sec H2O = 1.707g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.597 2275.175 1.377 0.251 53.446 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 47944.465 22121.494 2.868 509.668 177.707 384.739 2.165

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 225.76 -0.08 225.76 0.21 0.39 363.73

 MEAN 15.91 0.00 -0.02 225.76 -0.08 225.76 0.21 0.35

 HUB 13.07 0.00 -0.02 225.76 -0.08 225.76 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.80 47.36 10.44 358.47 423.71 6.55 499.74 486.51 26.02

 MEAN 54.06 44.80 9.26 311.38 384.67 6.55 499.74 486.51 26.02

 HUB 48.57 38.84 9.73 255.75 341.19 6.55 499.74 486.51 26.02

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.86 181.67 238.56 1095.64 0.27 2.05 1.78 7.43

 MEAN 15.50 299.47 178.83 240.21 1094.02 0.27 2.13 1.86 5.75

 HUB 12.59 315.51 202.47 241.98 1092.41 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.04 292.57 169.37 0.27 3260.55 0.92 0.91

 MEAN 303.25 270.52 124.41 0.25 2772.74 0.92 0.91 0.91 1.57

 HUB 246.35 245.93 43.89 0.23 2550.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.21 1.07 6.85 513.96 1.02 506.80 492.48 21.93

 MEAN 7.14 1.06 6.78 512.44 1.02 505.30 491.77 22.98

 HUB 7.11 1.05 6.71 511.75 1.02 503.82 491.64 24.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.29 35.37 31.50 3.87 0.93 0.46 1.40

 MEAN 36.67 27.38 23.50 3.88 0.93 0.44 1.64

 HUB 39.92 10.28 6.50 3.78 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.3711 182.1136 273.2439 1092.7198 0.3005 -0.1760 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1463 6.7189 504.1317 492.3119 24.0386 33.6829 33.0000 -0.6829

 

NASA/TM—2013-218094 L–23
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 279.8107 63.8950 272.4178 1095.2605 0.2555 0.1333 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1449 6.8328 506.4841 491.8383 410.5396 0.0237 0.3716

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 272.2267 0.0000 272.2267 1095.6107 0.2485 0.2940 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8446 506.8182 492.0401 0.0000 0.0600 0.0368 0.1652

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8795 7.1401 1.0581 512.7184 8.9214 235.1470 1.8228

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 56020.492 0.455 89.358 292527.719 0.337738E-02

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1353 Tt4 = 512.7184 T1 = 451.6027

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 381973.06 609.2828 80.1797 1.4787 0.8382 15.5764 1.1353 37.3740

NASA/TM—2013-218094 L–24
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.070 EfDer = 0.966 SH = 0.637685E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.367 2129.014 5.592 461.412 1.000 1.000 0.980

 W Kg/sec = 14.712 Wdry = 32.346 WH2O = 0.021 lbm/sec H2O = 0.330g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.243 2257.303 1.381 0.249 53.369 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60211.762 25390.154 3.539 831.557 234.968 619.754 2.638

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.78 -0.06 173.78 0.17 0.40 406.37

 MEAN 17.06 0.00 -0.02 173.78 -0.06 173.78 0.17 0.35

 HUB 12.51 0.00 -0.02 173.78 -0.06 173.78 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.61 50.47 15.14 383.29 420.90 5.49 458.99 454.81 26.44

 MEAN 61.27 47.20 14.07 316.96 361.53 5.49 458.99 454.81 26.44

 HUB 53.22 38.62 14.60 232.43 290.26 5.49 458.99 454.81 26.44

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 347.96 256.41 235.22 1052.74 0.33 7.29 6.52 16.04

 MEAN 18.04 354.47 263.09 237.55 1050.49 0.34 7.43 6.80 12.53

 HUB 15.00 386.79 302.65 240.85 1047.63 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.29 267.26 126.88 0.25 5290.93 0.92 0.88 

 MEAN 335.09 248.22 72.00 0.24 4746.17 0.92 0.88 0.88 1.67

 HUB 278.69 242.04 23.96 0.23 4540.51 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.78 477.20 1.03 467.47 467.18 25.30

 MEAN 6.16 1.10 5.70 475.57 1.03 465.48 466.20 27.31

 HUB 6.14 1.10 5.59 474.96 1.03 462.95 466.10 30.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.47 28.34 24.20 4.14 0.93 0.53 1.80

 MEAN 47.92 16.86 12.70 4.16 0.95 0.48 2.22

 HUB 51.49 -5.68 -9.30 3.62 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.966 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.8358 262.5821 254.7283 1050.1018 0.3484 -0.0416 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1716 5.6810 465.1697 466.6391 28.5775 45.8698 35.4000 -10.4698

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 255.2309 62.4373 247.4760 1056.2913 0.2416 0.4737 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1635 5.9214 470.6809 466.0282 554.9116 0.0266 0.5628

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 253.8385 0.0000 253.8385 1056.3297 0.2403 0.4530 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9032 470.7387 466.4857 0.0000 0.0600 0.0712 0.4362

NASA/TM—2013-218094 L–25
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8324 6.1419 1.0983 475.9065 14.4959 174.8333 1.3553

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90350.523 0.615 165.258 336749.094 0.106268E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.038 EfDer = 0.973 SH = 0.151858E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.367 2129.014 6.142 475.906 1.000 1.000 0.980

 W Kg/sec = 14.712 Wdry = 32.318 WH2O = 0.049 lbm/sec H2O = 0.828g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.202 2222.674 1.379 0.249 53.398 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57156.277 25381.357 2.716 590.487 217.394 468.502 2.155

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 232.30 -0.08 232.30 0.22 0.42 398.59

 MEAN 18.08 0.00 -0.02 232.30 -0.08 232.30 0.22 0.39

 HUB 15.21 0.00 -0.02 232.30 -0.08 232.30 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.69 46.36 12.33 381.80 446.99 5.94 471.59 467.97 38.34

 MEAN 55.34 42.30 13.04 335.88 408.45 5.94 471.59 467.97 38.34

 HUB 50.59 37.84 12.75 282.59 365.88 5.94 471.59 467.97 38.34

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.98 206.01 247.45 1066.72 0.30 2.33 2.04 9.02

 MEAN 18.01 324.07 207.11 249.25 1065.02 0.30 2.40 2.13 7.35

 HUB 15.22 346.05 237.95 251.26 1063.35 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 379.39 302.14 173.38 0.28 4208.31 0.92 0.89

 MEAN 334.61 279.97 127.50 0.26 3731.56 0.92 0.89 0.89 1.60

 HUB 282.83 255.23 44.88 0.24 3623.50 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.68 1.09 6.28 488.43 1.03 480.13 476.45 29.44

 MEAN 6.62 1.08 6.21 487.01 1.02 478.60 475.67 31.10

 HUB 6.60 1.08 6.14 486.69 1.02 477.10 475.72 32.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.78 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 39.72 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.44 10.13 6.50 3.63 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 348.9792 207.6956 280.4444 1063.9066 0.3280 -0.1219 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6305 6.1609 477.6254 476.1961 32.4695 36.5234 30.6000 -5.9234

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 273.3297 57.9478 267.1164 1068.0906 0.2559 0.2960 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6276 6.3366 481.3932 475.5210 491.5697 0.0170 0.4027

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 282.9444 0.0000 282.9444 1067.6007 0.2650 0.3037 0.5911

NASA/TM—2013-218094 L–26
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3035 480.9659 475.8089 0.0000 0.0600 0.0484 0.2178

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8542 6.6143 1.0769 487.3721 11.4666 202.7077 1.5714

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71644.281 0.498 131.043 307906.594 0.170732E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.610 EfDer = 0.988 SH = 0.196282E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.367 2129.014 6.614 487.372 1.000 1.000 0.980

 W Kg/sec = 14.712 Wdry = 32.303 WH2O = 0.064 lbm/sec H2O = 1.124g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.728 2196.374 1.379 0.250 53.412 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 54416.758 25376.910 2.669 545.479 204.349 424.468 2.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 239.42 -0.08 239.42 0.22 0.41 384.67

 MEAN 17.74 0.00 -0.02 239.42 -0.08 239.42 0.22 0.38

 HUB 15.05 0.00 -0.02 239.42 -0.08 239.42 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.30 46.36 10.94 372.88 443.20 6.39 482.79 476.25 32.85

 MEAN 54.01 43.40 10.61 329.57 407.42 6.39 482.79 476.25 32.85

 HUB 49.44 38.84 10.60 279.62 368.17 6.39 482.79 476.25 32.85

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 317.19 188.82 254.86 1078.01 0.29 2.26 1.98 8.75

 MEAN 17.51 321.20 193.44 256.41 1076.63 0.30 2.34 2.07 6.78

 HUB 14.85 345.19 229.18 258.13 1075.28 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 368.05 311.57 179.23 0.29 3742.26 0.92 0.90

 MEAN 325.26 288.31 131.81 0.27 3387.96 0.92 0.90 0.90 1.54

 HUB 275.90 262.32 46.72 0.24 3404.58 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.12 1.08 6.71 498.49 1.02 490.44 483.38 26.51

 MEAN 7.08 1.07 6.66 497.44 1.02 489.19 482.87 27.67

 HUB 7.08 1.07 6.60 497.48 1.02 487.96 483.17 28.83

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.53 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 37.03 27.21 23.50 3.71 0.94 0.44 1.62

 HUB 41.60 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 347.7197 194.7113 288.0911 1075.4469 0.3233 -0.1321 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0880 6.5998 488.1407 483.4295 28.9149 34.0535 31.5000 -2.5535

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 285.4508 62.2692 278.5763 1078.9086 0.2646 0.2258 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0864 6.7548 491.2915 482.8319 451.3937 0.0135 0.3673

 

NASA/TM—2013-218094 L–27
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 290.0312 0.0000 290.0312 1078.6655 0.2689 0.2743 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7337 491.0815 483.0980 0.0000 0.0600 0.0388 0.1776

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8726 7.0754 1.0697 497.8022 10.4308 212.0986 1.6442

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65274.102 0.482 119.391 308121.469 0.219937E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.580 EfDer = 0.997 SH = 0.251558E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.367 2129.014 7.075 497.802 1.000 1.000 0.980

 W Kg/sec = 14.712 Wdry = 32.285 WH2O = 0.081 lbm/sec H2O = 1.508g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.877 2173.243 1.378 0.250 53.430 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51988.602 25371.369 2.658 513.330 193.133 395.845 2.050 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 243.06 -0.08 243.06 0.22 0.40 365.26

 MEAN 16.97 0.00 -0.02 243.06 -0.08 243.06 0.22 0.37

 HUB 14.32 0.00 -0.02 243.06 -0.08 243.06 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.82 46.36 9.46 357.83 432.65 6.83 493.09 483.55 29.49

 MEAN 52.38 43.80 8.58 315.30 398.18 6.83 493.09 483.55 29.49

 HUB 47.60 37.84 9.76 266.05 360.43 6.83 493.09 483.55 29.49

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 308.22 168.96 257.79 1088.00 0.28 2.16 1.89 8.34

 MEAN 16.57 312.35 174.37 259.14 1086.81 0.29 2.24 1.97 6.35

 HUB 13.89 335.21 210.80 260.64 1085.64 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 350.77 315.45 181.82 0.29 3191.55 0.92 0.91

 MEAN 307.93 291.53 133.55 0.27 2891.48 0.92 0.91 0.91 1.49

 HUB 258.06 264.89 47.27 0.24 2929.16 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.53 1.06 7.13 507.26 1.02 499.68 489.36 24.93

 MEAN 7.49 1.06 7.08 506.38 1.02 498.59 488.97 25.82

 HUB 7.49 1.06 7.02 506.49 1.02 497.52 489.30 26.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.24 35.20 31.50 3.70 0.93 0.41 1.40

 MEAN 33.94 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.96 10.28 6.50 3.78 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 333.9382 175.3551 284.1924 1085.9348 0.3075 -0.1066 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.5012 7.0321 497.8143 489.4576 26.7043 31.6758 32.4000 0.7242

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 287.1395 64.3970 279.8252 1088.4563 0.2638 0.1739 2.2705

 

NASA/TM—2013-218094 L–28
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.5003 7.1514 500.1330 489.0060 432.2457 0.0121 0.3367

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 284.7411 0.0000 284.7411 1088.5657 0.2616 0.2450 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1470 500.2430 489.2150 0.0000 0.0600 0.0368 0.1637

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8788 7.4897 1.0586 506.7087 8.9073 233.0533 1.8066

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55842.703 0.454 102.140 317289.594 0.279980E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.727 EfDer = 1.000 SH = 0.318533E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.367 2129.014 7.490 506.708 1.000 1.000 0.980

 W Kg/sec = 14.712 Wdry = 32.264 WH2O = 0.103 lbm/sec H2O = 1.990g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.787 2154.058 1.377 0.251 53.452 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49908.781 25364.643 2.768 509.668 184.151 384.739 2.089

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 235.01 -0.08 235.01 0.22 0.38 344.36

 MEAN 15.91 0.00 -0.02 235.01 -0.08 235.01 0.22 0.35

 HUB 13.07 0.00 -0.02 235.01 -0.08 235.01 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.38 47.36 8.02 340.37 413.69 7.26 502.31 489.70 27.60

 MEAN 51.53 44.80 6.73 295.65 377.74 7.26 502.31 489.70 27.60

 HUB 45.95 38.84 7.11 242.83 337.99 7.26 502.31 489.70 27.60

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.30 155.80 249.67 1096.98 0.27 2.05 1.78 7.43

 MEAN 15.50 296.43 157.69 251.01 1095.75 0.27 2.13 1.86 5.75

 HUB 12.59 314.72 187.93 252.45 1094.54 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 333.31 306.34 177.51 0.28 2796.57 0.92 0.91

 MEAN 287.93 282.79 130.25 0.26 2445.04 0.92 0.91 0.91 1.47

 HUB 233.91 256.60 45.98 0.23 2367.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.91 1.06 7.53 514.98 1.02 508.09 494.63 24.12

 MEAN 7.85 1.05 7.47 513.94 1.01 506.95 494.17 24.98

 HUB 7.84 1.05 7.41 513.71 1.01 505.82 494.29 25.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.97 35.41 31.50 3.91 0.93 0.39 1.40

 MEAN 32.14 27.42 23.50 3.92 0.93 0.38 1.64

 HUB 36.67 10.32 6.50 3.82 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 327.7162 160.5772 285.6797 1094.3342 0.2995 -0.1948 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8590 7.3923 505.6649 494.7520 26.1898 29.3398 33.0000 3.6602

 

NASA/TM—2013-218094 L–29
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 293.6122 67.0466 285.8547 1096.1534 0.2679 0.0283 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8565 7.4803 507.3519 494.4043 410.5396 0.0264 0.3057

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 285.6216 0.0000 285.6216 1096.5438 0.2605 0.2191 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4945 507.7209 494.5605 0.0000 0.0600 0.0412 0.0641

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8751 7.8506 1.0482 514.2125 7.5043 259.2421 2.0096

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47149.500 0.424 86.240 334585.844 0.351694E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1144 Tt4 = 514.2125 T1 = 461.4116

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 330261.13 604.0712 80.2428 1.4038 0.8528 14.0701 1.1144 37.3740

NASA/TM—2013-218094 L–30
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.214 EfDer = 0.995 SH = 0.835716E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.890 1957.502 6.513 472.322 1.000 1.000 0.980

 W Kg/sec = 18.587 Wdry = 40.856 WH2O = 0.034 lbm/sec H2O = 0.491g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.069 2051.350 1.380 0.249 53.375 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 67066.156 32074.182 3.224 831.557 257.924 619.754 2.403

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 193.56 -0.07 193.56 0.18 0.38 369.30

 MEAN 17.06 0.00 -0.02 193.56 -0.07 193.56 0.18 0.33

 HUB 12.51 0.00 -0.02 193.56 -0.07 193.56 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.23 50.47 10.76 352.41 402.13 6.36 469.32 463.78 25.00

 MEAN 56.41 47.20 9.21 291.43 349.91 6.36 469.32 463.78 25.00

 HUB 47.84 38.62 9.22 213.70 288.38 6.36 469.32 463.78 25.00

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 337.98 210.14 264.71 1061.15 0.32 7.29 6.52 16.04

 MEAN 18.04 350.56 227.71 266.54 1059.67 0.33 7.43 6.80 12.53

 HUB 15.00 391.16 283.39 269.63 1057.41 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 352.41 300.52 142.27 0.28 4336.62 0.92 0.91

 MEAN 308.10 278.40 80.39 0.26 4108.07 0.92 0.91 0.91 1.42

 HUB 256.24 270.99 27.15 0.26 4251.68 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.60 484.21 1.03 475.04 473.12 25.88

 MEAN 7.04 1.08 6.53 483.58 1.02 473.72 472.85 27.16

 HUB 7.06 1.08 6.43 483.97 1.02 471.70 473.49 29.23

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.44 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.51 16.78 12.70 4.08 0.93 0.36 2.22

 HUB 46.43 -5.75 -9.30 3.55 0.93 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.3791 227.2649 286.0988 1059.0692 0.3450 -0.0594 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0517 6.5016 473.2187 473.3285 28.5305 38.4622 35.4000 -3.0622

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 288.9114 70.6766 280.1332 1063.5377 0.2717 0.3373 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0491 6.7015 477.2296 472.8461 554.9116 0.0147 0.4374

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 286.8137 0.0000 286.8137 1063.6273 0.2697 0.3492 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6937 477.3274 473.2630 0.0000 0.0600 0.0398 0.3227

NASA/TM—2013-218094 L–31
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8745 7.0357 1.0803 483.9196 11.5986 200.4025 1.5535

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72355.570 0.583 167.196 419227.375 0.127524E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.383 EfDer = 0.999 SH = 0.171215E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.890 1957.502 7.036 483.919 1.000 1.000 0.980

 W Kg/sec = 18.587 Wdry = 40.820 WH2O = 0.070 lbm/sec H2O = 1.046g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.521 2026.627 1.379 0.250 53.404 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64496.695 32063.113 2.442 590.487 241.801 468.502 1.938 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.13 -0.09 262.13 0.25 0.41 363.43

 MEAN 18.08 0.00 -0.02 262.13 -0.09 262.13 0.25 0.38

 HUB 15.21 0.00 -0.02 262.13 -0.09 262.13 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.26 46.36 6.90 351.04 438.19 6.75 478.42 474.58 36.44

 MEAN 49.68 42.30 7.38 308.82 405.14 6.75 478.42 474.58 36.44

 HUB 44.76 37.84 6.92 259.82 369.15 6.75 478.42 474.58 36.44

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 320.09 150.83 282.33 1071.10 0.30 2.33 2.04 9.02

 MEAN 18.01 326.69 162.47 283.43 1070.26 0.31 2.40 2.13 7.35

 HUB 15.22 353.18 208.98 284.71 1069.44 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 348.82 344.83 197.99 0.32 3081.88 0.92 0.91

 MEAN 307.65 318.45 145.19 0.30 2927.62 0.92 0.91 0.91 1.38

 HUB 260.05 289.25 51.06 0.27 3182.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.45 1.06 7.01 492.34 1.02 484.15 480.28 31.05

 MEAN 7.43 1.06 6.97 491.92 1.02 483.38 480.11 31.89

 HUB 7.47 1.06 6.93 492.62 1.02 482.64 480.81 32.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.11 35.04 31.50 3.54 0.93 0.34 1.40

 MEAN 29.82 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.28 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 358.7127 162.9210 319.5803 1068.7067 0.3357 -0.1636 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4444 6.8937 482.0027 480.7528 33.7162 27.0123 30.6000 3.5877

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 313.7781 66.5232 306.6454 1071.3823 0.2929 0.0990 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4422 7.0181 484.4195 480.2902 491.5697 0.0147 0.2570

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 324.9622 0.0000 324.9622 1070.7406 0.3035 0.1500 0.5911

NASA/TM—2013-218094 L–32
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9763 483.8490 480.5872 0.0000 0.0600 0.0410 0.0116

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8715 7.4296 1.0560 492.2934 8.3745 250.4666 1.9416

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 52362.820 0.430 120.998 386512.063 0.188386E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.482 EfDer = 0.995 SH = 0.209924E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.890 1957.502 7.430 492.293 1.000 1.000 0.980

 W Kg/sec = 18.587 Wdry = 40.805 WH2O = 0.086 lbm/sec H2O = 1.327g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.819 2009.317 1.379 0.250 53.416 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62289.262 32058.219 2.361 545.479 231.015 424.468 1.837

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 274.06 -0.09 274.06 0.26 0.41 351.91

 MEAN 17.74 0.00 -0.02 274.06 -0.09 274.06 0.26 0.38

 HUB 15.05 0.00 -0.02 274.06 -0.09 274.06 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.37 46.36 5.01 342.84 438.99 7.11 486.29 480.75 33.75

 MEAN 47.88 43.40 4.48 303.02 408.64 7.11 486.29 480.75 33.75

 HUB 43.18 38.84 4.34 257.09 375.83 7.11 486.29 480.75 33.75

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.79 129.80 295.54 1078.57 0.30 2.26 1.98 8.75

 MEAN 17.51 330.26 146.05 296.22 1078.09 0.31 2.34 2.07 6.78

 HUB 14.85 357.67 199.18 297.08 1077.64 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 338.40 361.74 208.60 0.34 2573.30 0.92 0.91

 MEAN 299.05 333.40 153.00 0.31 2558.51 0.92 0.91 0.91 1.32

 HUB 253.67 302.04 54.49 0.28 2959.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.79 1.05 7.32 499.32 1.01 490.99 485.36 29.94

 MEAN 7.78 1.05 7.30 499.28 1.01 490.56 485.43 30.37

 HUB 7.84 1.06 7.27 500.37 1.02 490.15 486.35 30.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.71 35.22 31.50 3.72 0.93 0.28 1.40

 MEAN 26.25 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.84 10.39 6.50 3.89 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 364.6234 147.0085 333.6746 1076.3912 0.3387 -0.1762 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7995 7.2125 489.0358 486.1301 32.2011 23.7771 31.5000 7.7229

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 333.2809 72.7030 325.2544 1078.3124 0.3091 0.0038 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7943 7.3019 490.7832 485.7724 451.3937 0.0204 0.2151

 

NASA/TM—2013-218094 L–33
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 339.0685 0.0000 339.0685 1077.9641 0.3145 0.0948 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2682 490.4731 486.0091 0.0000 0.0600 0.0562 -0.0631

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8422 7.7762 1.0467 499.6547 7.3618 270.8624 2.0997

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46090.621 0.402 106.504 389257.156 0.229152E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.906 EfDer = 0.975 SH = 0.253255E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.890 1957.502 7.776 499.654 1.000 1.000 0.980

 W Kg/sec = 18.587 Wdry = 40.787 WH2O = 0.104 lbm/sec H2O = 1.648g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.866 1994.461 1.378 0.250 53.430 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60517.816 32052.727 2.308 513.330 222.424 395.845 1.780

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 282.94 -0.10 282.94 0.26 0.40 335.21

 MEAN 16.97 0.00 -0.02 282.94 -0.10 282.94 0.26 0.37

 HUB 14.32 0.00 -0.02 282.94 -0.10 282.94 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.31 46.36 2.95 329.01 434.01 7.42 493.27 486.07 32.01

 MEAN 45.71 43.80 1.91 289.90 405.16 7.42 493.27 486.07 32.01

 HUB 40.86 37.84 3.02 244.62 374.09 7.42 493.27 486.07 32.01

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 322.53 106.60 304.41 1084.89 0.30 2.16 1.89 8.34

 MEAN 16.57 329.36 124.87 304.77 1084.67 0.30 2.24 1.97 6.35

 HUB 13.89 354.89 180.84 305.36 1084.46 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.52 373.21 215.91 0.34 2014.52 0.92 0.89

 MEAN 283.12 343.40 158.25 0.32 2071.31 0.92 0.89 0.89 1.27

 HUB 237.27 310.53 56.43 0.29 2513.29 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.04 7.59 505.15 1.01 496.85 489.62 29.50

 MEAN 8.07 1.04 7.57 505.30 1.01 496.65 489.79 29.68

 HUB 8.13 1.05 7.56 506.51 1.01 496.46 490.73 29.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.30 35.35 31.50 3.85 0.93 0.23 1.40

 MEAN 22.28 27.44 23.50 3.94 0.91 0.25 1.62

 HUB 30.64 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 357.7982 125.5771 335.0372 1083.3296 0.3303 -0.1438 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0790 7.4998 495.4394 490.4094 31.0883 20.5468 32.4000 11.8532

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 341.3812 76.5618 332.6852 1084.3292 0.3148 -0.0584 2.2705

 

NASA/TM—2013-218094 L–34
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0696 7.5417 496.3554 490.2257 432.2457 0.0282 0.1787

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 339.1375 0.0000 339.1375 1084.4576 0.3127 0.0414 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5238 496.4778 490.3412 0.0000 0.0600 0.0798 -0.0935

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7749 8.0432 1.0343 505.6503 5.9961 311.0760 2.4114

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37592.535 0.361 86.867 403297.250 0.274317E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.483 EfDer = 0.942 SH = 0.301552E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.890 1957.502 8.043 505.650 1.000 1.000 0.980

 W Kg/sec = 18.587 Wdry = 40.767 WH2O = 0.123 lbm/sec H2O = 2.008g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.787 1982.601 1.377 0.251 53.446 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59142.027 32046.602 2.355 509.668 216.392 384.739 1.778

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 278.49 -0.10 278.49 0.26 0.39 316.95

 MEAN 15.91 0.00 -0.02 278.49 -0.10 278.49 0.26 0.36

 HUB 13.07 0.00 -0.02 278.49 -0.10 278.49 0.26 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.34 47.36 0.98 312.95 418.99 7.69 499.47 490.33 30.91

 MEAN 44.32 44.80 -0.48 271.83 389.23 7.69 499.47 490.33 30.91

 HUB 38.73 38.84 -0.11 223.27 357.00 7.69 499.47 490.33 30.91

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 313.90 91.36 300.31 1090.70 0.29 2.05 1.78 7.43

 MEAN 15.50 319.22 107.26 300.66 1090.48 0.29 2.13 1.86 5.75

 HUB 12.59 340.59 158.90 301.25 1090.25 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 306.46 369.40 215.10 0.34 1640.73 0.92 0.86

 MEAN 264.74 339.40 157.47 0.31 1663.85 0.92 0.86 0.86 1.24

 HUB 215.07 306.44 56.17 0.28 2001.81 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.27 1.03 7.81 510.12 1.01 502.27 493.22 29.23

 MEAN 8.27 1.03 7.80 510.18 1.01 502.06 493.32 29.42

 HUB 8.32 1.03 7.78 511.10 1.01 501.86 494.06 29.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.92 35.61 31.50 4.11 0.93 0.20 1.40

 MEAN 19.63 27.64 23.50 4.14 0.90 0.21 1.64

 HUB 27.81 10.56 6.50 4.06 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.942 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 360.4472 109.2302 343.4981 1088.3417 0.3312 -0.2483 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2771 7.6808 500.1173 494.1104 31.4688 17.6403 33.0000 15.3597

 

NASA/TM—2013-218094 L–35
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 356.7688 81.4685 347.3426 1088.5701 0.3277 -0.2691 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2512 7.6686 500.3281 494.0655 410.5396 0.0731 0.1467

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 347.0812 0.0000 347.0812 1089.1582 0.3187 0.0077 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6854 500.8716 494.0789 0.0000 0.0600 0.1030 -0.2345

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6857 8.2366 1.0240 510.4641 4.8142 362.1430 2.8073

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30229.063 0.322 69.852 427345.594 0.324399E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0808 Tt4 = 510.4641 T1 = 472.3216

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 238630.61 551.4178 88.0686 1.2646 0.8244 9.2145 1.0808 37.3740

NASA/TM—2013-218094 L–36
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.599 EfDer = 0.999 SH = 0.122185E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.675 1799.592 7.939 487.554 1.000 1.000 0.980

 W Kg/sec = 23.034 Wdry = 50.613 WH2O = 0.062 lbm/sec H2O = 0.846g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 90.967 1856.180 1.380 0.249 53.388 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70481.820 39743.344 3.120 831.557 266.488 619.754 2.326

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 203.42 -0.07 203.42 0.19 0.36 334.16

 MEAN 17.06 0.00 -0.02 203.42 -0.07 203.42 0.19 0.31

 HUB 12.51 0.00 -0.02 203.42 -0.07 203.42 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.88 50.47 7.41 323.98 382.61 7.74 484.24 475.83 23.32

 MEAN 52.80 47.20 5.60 267.92 336.45 7.74 484.24 475.83 23.32

 HUB 44.01 38.62 5.39 196.46 282.85 7.74 484.24 475.83 23.32

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.85 172.66 281.05 1075.19 0.31 7.29 6.52 16.04

 MEAN 18.04 344.69 197.86 282.25 1074.32 0.32 7.43 6.80 12.53

 HUB 15.00 388.35 263.96 284.85 1072.57 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 323.98 319.20 151.32 0.30 3563.38 0.92 0.91

 MEAN 283.25 294.88 85.39 0.27 3569.78 0.92 0.91 0.91 1.27

 HUB 235.57 286.26 28.40 0.27 3960.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.91 496.52 1.02 487.80 482.96 25.49

 MEAN 8.44 1.06 7.86 496.54 1.02 487.02 483.11 26.18

 HUB 8.49 1.07 7.77 497.52 1.02 485.44 484.14 27.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.56 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 35.03 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.82 -5.69 -9.30 3.61 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.7915 197.4746 303.1450 1073.5673 0.3370 -0.0738 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4479 7.8180 486.3817 483.6261 27.5295 33.0810 35.4000 2.3190

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 308.1497 75.3828 298.7870 1076.7273 0.2862 0.2290 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4455 7.9851 489.2585 483.2521 554.9116 0.0139 0.3498

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 305.8475 0.0000 305.8475 1076.8383 0.2840 0.2537 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9778 489.3728 483.6711 0.0000 0.0600 0.0384 0.2169

NASA/TM—2013-218094 L–37
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8721 8.4306 1.0619 496.8567 9.3033 222.5688 1.7253

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58130.223 0.554 166.468 507952.156 0.174884E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.174 EfDer = 0.987 SH = 0.225347E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.675 1799.592 8.431 496.856 1.000 1.000 0.980

 W Kg/sec = 23.034 Wdry = 50.561 WH2O = 0.114 lbm/sec H2O = 1.600g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.480 1838.724 1.378 0.250 53.421 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68732.469 39727.172 2.329 590.487 253.494 468.502 1.848

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 279.35 -0.10 279.35 0.26 0.40 329.73

 MEAN 18.08 0.00 -0.02 279.35 -0.10 279.35 0.26 0.37

 HUB 15.21 0.00 -0.02 279.35 -0.10 279.35 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.13 46.36 2.77 322.73 426.91 8.05 490.63 485.00 34.38

 MEAN 45.47 42.30 3.17 283.91 398.36 8.05 490.63 485.00 34.38

 HUB 40.54 37.84 2.70 238.86 367.61 8.05 490.63 485.00 34.38

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.51 106.51 304.41 1081.82 0.30 2.33 2.04 9.02

 MEAN 18.01 329.74 126.07 304.69 1081.67 0.30 2.40 2.13 7.35

 HUB 15.22 356.21 183.71 305.18 1081.53 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 320.68 372.21 214.18 0.34 2176.89 0.92 0.90

 MEAN 282.84 342.65 156.77 0.32 2272.21 0.92 0.90 0.90 1.25

 HUB 239.07 310.16 55.36 0.29 2798.10 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.74 1.04 8.22 502.32 1.01 494.01 488.70 31.85

 MEAN 8.75 1.04 8.21 502.55 1.01 493.87 488.92 31.99

 HUB 8.83 1.05 8.20 503.87 1.01 493.74 489.95 32.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.28 35.13 31.50 3.63 0.93 0.22 1.40

 MEAN 22.48 27.23 23.50 3.73 0.91 0.24 1.63

 HUB 31.05 10.28 6.50 3.78 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.5560 126.4216 344.0652 1079.8021 0.3395 -0.1941 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7682 8.1057 492.1892 489.6611 34.0577 20.1751 30.6000 10.4249

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 339.7860 72.0371 332.0621 1081.4575 0.3142 -0.0433 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7593 8.1884 493.6989 489.3359 491.5697 0.0258 0.1619

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 352.5585 0.0000 352.5585 1080.6780 0.3262 0.0250 0.5911

NASA/TM—2013-218094 L–38
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1223 492.9938 489.6631 0.0000 0.0600 0.0709 -0.1612

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7994 8.7340 1.0360 502.9146 6.0584 302.5974 2.3457

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37952.969 0.369 108.686 471250.781 0.244305E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.192 EfDer = 0.947 SH = 0.267122E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.675 1799.592 8.734 502.914 1.000 1.000 0.980

 W Kg/sec = 23.034 Wdry = 50.540 WH2O = 0.135 lbm/sec H2O = 1.934g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.983 1827.617 1.378 0.250 53.435 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67429.516 39720.613 2.215 545.479 246.246 424.468 1.724

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 296.67 -0.10 296.67 0.27 0.40 320.09

 MEAN 17.74 0.00 -0.02 296.67 -0.10 296.67 0.27 0.38

 HUB 15.05 0.00 -0.02 296.67 -0.10 296.67 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.74 46.36 0.38 315.19 432.92 8.30 495.90 489.62 34.00

 MEAN 43.21 43.40 -0.19 278.57 407.03 8.30 495.90 489.62 34.00

 HUB 38.56 38.84 -0.28 236.35 379.37 8.30 495.90 489.62 34.00

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 334.23 81.30 324.19 1086.15 0.31 2.26 1.98 8.75

 MEAN 17.51 341.02 106.65 323.91 1086.45 0.31 2.34 2.07 6.78

 HUB 14.85 367.23 172.90 323.98 1086.75 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 311.10 397.38 229.80 0.37 1612.63 0.92 0.87

 MEAN 274.93 365.02 168.28 0.34 1868.90 0.92 0.87 0.87 1.19

 HUB 233.21 329.55 60.31 0.30 2569.07 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.96 1.03 8.40 506.95 1.01 498.04 492.43 32.72

 MEAN 8.99 1.03 8.41 507.59 1.01 498.32 492.84 32.41

 HUB 9.09 1.04 8.41 509.35 1.01 498.59 494.10 32.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.08 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.22 27.45 23.50 3.95 0.90 0.18 1.62

 HUB 28.09 10.55 6.50 4.05 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.947 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 381.1101 107.3505 365.6786 1084.3190 0.3515 -0.2086 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0084 8.2817 496.3868 493.7039 34.7119 16.3604 31.5000 15.1396

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 367.5748 80.1840 358.7224 1085.2026 0.3387 -0.1488 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9912 8.3151 497.1952 493.5132 451.3937 0.0382 0.1175

 

NASA/TM—2013-218094 L–39
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 374.9403 0.0000 374.9403 1084.7229 0.3457 -0.0395 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2530 496.7599 493.7518 0.0000 0.0600 0.1015 -0.2508

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6772 8.9527 1.0250 507.9657 5.0514 343.1569 2.6601

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31686.465 0.327 90.741 477185.813 0.286521E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.267 EfDer = 0.888 SH = 0.309960E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.675 1799.592 8.953 507.965 1.000 1.000 0.980

 W Kg/sec = 23.034 Wdry = 50.518 WH2O = 0.157 lbm/sec H2O = 2.268g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.342 1818.507 1.377 0.251 53.449 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66694.266 39713.875 2.126 513.330 241.498 395.845 1.639

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 311.81 -0.11 311.81 0.29 0.40 305.64

 MEAN 16.97 0.00 -0.02 311.81 -0.11 311.81 0.29 0.38

 HUB 14.32 0.00 -0.02 311.81 -0.11 311.81 0.29 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.14 46.36 -2.22 302.47 434.49 8.46 500.22 493.48 33.96

 MEAN 40.53 43.80 -3.27 266.51 410.26 8.46 500.22 493.48 33.96

 HUB 35.81 37.84 -2.03 224.89 384.51 8.46 500.22 493.48 33.96

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 344.39 54.04 340.12 1089.37 0.32 2.16 1.89 8.34

 MEAN 16.57 349.41 82.89 339.43 1090.03 0.32 2.24 1.97 6.35

 HUB 13.89 372.72 154.37 339.25 1090.67 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 296.50 417.69 242.46 0.38 1022.33 0.92 0.81

 MEAN 260.28 382.99 177.39 0.35 1375.70 0.92 0.81 0.81 1.14

 HUB 218.13 345.19 63.76 0.32 2145.78 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.09 1.02 8.49 510.52 1.01 501.08 495.44 33.96

 MEAN 9.13 1.02 8.52 511.41 1.01 501.68 495.93 33.28

 HUB 9.24 1.03 8.53 513.33 1.01 502.27 497.21 32.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.03 35.48 31.50 3.98 0.93 0.08 1.40

 MEAN 13.72 27.59 23.50 4.09 0.89 0.13 1.62

 HUB 24.47 10.64 6.50 4.14 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.888 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 383.2126 83.3605 374.0359 1088.2509 0.3521 -0.1714 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1462 8.4059 500.0623 496.7211 35.2269 12.5640 32.4000 19.8360

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 383.6514 86.0418 373.8786 1088.2228 0.3525 -0.2032 2.2705

 

NASA/TM—2013-218094 L–40
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1210 8.3812 500.0361 496.7426 432.2457 0.0492 0.0813

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 382.1234 0.0000 382.1234 1088.3220 0.3511 -0.0904 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3390 500.1299 496.7956 0.0000 0.0600 0.1305 -0.2690

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4743 9.0689 1.0130 511.7538 3.7885 423.0544 3.2795

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23795.484 0.271 68.143 497144.094 0.329469E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.128 EfDer = 0.825 SH = 0.354143E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.675 1799.592 9.069 511.753 1.000 1.000 0.980

 W Kg/sec = 23.034 Wdry = 50.496 WH2O = 0.179 lbm/sec H2O = 2.606g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.589 1811.764 1.377 0.251 53.463 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66338.273 39706.918 2.129 509.668 239.355 384.739 1.607

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 312.38 -0.11 312.38 0.29 0.39 289.64

 MEAN 15.91 0.00 -0.02 312.38 -0.11 312.38 0.29 0.37

 HUB 13.07 0.00 -0.02 312.38 -0.11 312.38 0.29 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.66 47.36 -4.70 287.70 424.75 8.58 503.99 496.34 34.01

 MEAN 38.67 44.80 -6.13 249.90 400.11 8.58 503.99 496.34 34.01

 HUB 33.32 38.84 -5.52 205.26 373.84 8.58 503.99 496.34 34.01

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 343.20 35.96 341.31 1092.47 0.31 2.05 1.78 7.43

 MEAN 15.50 346.52 63.72 340.61 1093.20 0.32 2.13 1.86 5.75

 HUB 12.59 365.61 133.21 340.48 1093.89 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 281.74 420.60 245.78 0.38 647.03 0.92 0.76

 MEAN 243.38 385.09 179.66 0.35 989.24 0.92 0.76 0.76 1.11

 HUB 197.72 346.53 64.51 0.32 1678.50 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.15 1.01 8.55 513.37 1.00 504.00 497.81 34.86

 MEAN 9.19 1.01 8.58 514.22 1.00 504.67 498.25 34.09

 HUB 9.28 1.02 8.60 515.95 1.01 505.32 499.34 33.33

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.01 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.60 27.81 23.50 4.31 0.87 0.09 1.64

 HUB 21.37 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.825 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 396.0574 64.8895 390.7055 1090.3275 0.3632 -0.2839 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1922 8.4035 502.0420 499.3327 37.1649 9.4298 33.0000 23.5702

 

NASA/TM—2013-218094 L–41
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 409.4097 93.4890 398.5926 1089.4015 0.3758 -0.4433 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1341 8.2985 501.1877 499.5694 410.5396 0.1126 0.0542

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 398.0790 0.0000 398.0790 1090.1921 0.3651 -0.1005 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3242 501.9156 499.4535 0.0000 0.0600 0.1447 -0.4024

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2511 9.1139 1.0050 514.5137 2.7600 534.5090 4.1435

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17359.328 0.219 49.712 529251.188 0.374229E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0553 Tt4 = 514.5137 T1 = 487.5539 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 168924.47 483.7512 90.9675 1.1480 0.6971 5.5992 1.0553 37.3740

NASA/TM—2013-218094 L–42
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.729 EfDer = 1.000 SH = 0.179446E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1590.744 9.337 500.811 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.377 WH2O = 0.089 lbm/sec H2O = 1.430g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.521 1618.904 1.379 0.250 53.406 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59787.051 38785.934 3.708 831.557 224.254 619.754 2.764

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.55 -0.06 172.55 0.16 0.31 291.44

 MEAN 17.06 0.00 -0.02 172.55 -0.06 172.55 0.16 0.27

 HUB 12.51 0.00 -0.02 172.55 -0.06 172.55 0.16 0.23

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.93 50.47 8.46 286.38 334.40 9.18 498.43 486.10 22.86

 MEAN 53.93 47.20 6.73 236.83 293.07 9.18 498.43 486.10 22.86

 HUB 45.19 38.62 6.57 173.66 244.86 9.18 498.43 486.10 22.86

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 286.39 158.01 238.86 1090.02 0.26 7.29 6.52 16.04

 MEAN 18.04 298.58 178.03 239.70 1089.28 0.27 7.43 6.80 12.53

 HUB 15.00 335.05 232.39 241.36 1087.94 0.31 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 286.38 271.17 128.37 0.25 3260.98 0.92 0.91

 MEAN 250.37 250.38 72.34 0.23 3212.01 0.92 0.91 0.91 1.31

 HUB 208.23 242.57 24.16 0.22 3486.59 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.34 508.05 1.01 501.49 492.07 25.70

 MEAN 9.79 1.05 9.30 507.94 1.01 500.81 492.13 26.25

 HUB 9.83 1.05 9.21 508.55 1.02 499.58 492.84 27.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.49 28.26 24.20 4.06 0.93 0.32 1.80

 MEAN 36.60 16.79 12.70 4.09 0.93 0.29 2.22

 HUB 43.92 -5.72 -9.30 3.58 0.93 0.18 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 312.5327 177.6868 257.1071 1088.7396 0.2871 -0.0691 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7977 9.2608 500.3814 492.5965 27.4221 34.6484 35.4000 0.7516

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.1818 64.1377 254.2158 1091.2379 0.2403 0.2577 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7970 9.4169 502.6926 492.3142 554.9116 0.0113 0.3708

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 260.1616 0.0000 260.1616 1091.3138 0.2384 0.2778 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4100 502.7780 492.8768 0.0000 0.0600 0.0368 0.2443

NASA/TM—2013-218094 L–43
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8762 9.7837 1.0478 508.1794 7.3685 215.4346 1.6700

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46151.797 0.563 129.011 483482.938 0.259083E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.208 EfDer = 0.994 SH = 0.336287E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1590.744 9.784 508.179 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.299 WH2O = 0.166 lbm/sec H2O = 2.734g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.565 1607.125 1.377 0.251 53.457 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58599.566 38761.879 2.736 590.487 215.786 468.502 2.171

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.16 -0.08 238.16 0.22 0.34 288.20

 MEAN 18.08 0.00 -0.02 238.16 -0.08 238.16 0.22 0.32

 HUB 15.21 0.00 -0.02 238.16 -0.08 238.16 0.22 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.15 46.36 3.79 285.27 371.68 9.47 503.67 494.70 36.10

 MEAN 46.51 42.30 4.21 250.96 346.04 9.47 503.67 494.70 36.10

 HUB 41.57 37.84 3.73 211.14 318.33 9.47 503.67 494.70 36.10

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 278.94 100.76 260.11 1095.22 0.25 2.33 2.04 9.02

 MEAN 18.01 285.18 116.29 260.39 1095.00 0.26 2.40 2.13 7.35

 HUB 15.22 308.19 164.21 260.80 1094.80 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 283.47 317.87 182.71 0.29 2059.13 0.92 0.91

 MEAN 250.01 292.72 133.72 0.27 2095.84 0.92 0.91 0.91 1.27

 HUB 211.32 265.02 47.11 0.24 2501.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.08 1.03 9.64 512.73 1.01 506.54 497.78 34.23

 MEAN 10.08 1.03 9.63 512.81 1.01 506.34 497.89 34.43

 HUB 10.14 1.04 9.61 513.70 1.01 506.15 498.63 34.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 21.17 35.09 31.50 3.59 0.93 0.24 1.40

 MEAN 24.07 27.18 23.50 3.68 0.92 0.26 1.63

 HUB 32.20 10.24 6.50 3.74 0.92 0.30 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 315.4818 116.6153 293.1376 1093.7086 0.2885 -0.1838 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0960 9.5383 505.1625 498.4972 35.9454 21.6935 30.6000 8.9065

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 289.7955 61.4387 283.2079 1095.0435 0.2646 -0.0101 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0916 9.6196 506.3983 498.2122 491.5697 0.0193 0.1815

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 300.0455 0.0000 300.0455 1094.5126 0.2741 0.0513 0.5911

NASA/TM—2013-218094 L–44
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5669 505.9138 498.5275 0.0000 0.0600 0.0623 -0.1207

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8255 10.0711 1.0294 513.0726 4.9004 288.7702 2.2385

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30811.590 0.383 86.129 448228.406 0.362904E-02

 

Melt Ratio at Stator LE, Throat, TE

0.37432E-01 0.52415E-01 0.10861E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.755 EfDer = 0.961 SH = 0.390785E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1590.744 10.071 513.069 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.272 WH2O = 0.193 lbm/sec H2O = 3.229g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.809 1599.443 1.376 0.251 53.475 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57664.270 38753.492 2.589 545.479 210.714 424.468 2.014

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 253.71 -0.09 253.71 0.23 0.34 280.12

 MEAN 17.74 0.00 -0.02 253.71 -0.09 253.71 0.23 0.32

 HUB 15.05 0.00 -0.02 253.71 -0.09 253.71 0.23 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.69 46.36 1.33 278.61 376.88 9.71 507.96 498.64 36.56

 MEAN 44.15 43.40 0.75 246.24 353.62 9.71 507.96 498.64 36.56

 HUB 39.48 38.84 0.64 208.92 328.71 9.71 507.96 498.64 36.56

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 288.28 78.67 277.34 1098.76 0.26 2.26 1.98 8.75

 MEAN 17.51 294.49 99.19 277.28 1098.87 0.27 2.34 2.07 6.78

 HUB 14.85 317.66 154.77 277.41 1098.99 0.29 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 275.00 339.79 196.32 0.31 1560.30 0.92 0.88

 MEAN 243.02 312.36 143.83 0.28 1738.10 0.92 0.88 0.88 1.21

 HUB 206.15 282.12 51.38 0.26 2299.63 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.29 1.02 9.82 516.50 1.01 509.90 500.94 35.18

 MEAN 10.31 1.02 9.82 516.90 1.01 510.01 501.21 35.06

 HUB 10.39 1.03 9.82 518.13 1.01 510.12 502.12 34.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 15.84 35.29 31.50 3.79 0.93 0.17 1.40

 MEAN 19.68 27.42 23.50 3.92 0.91 0.20 1.62

 HUB 29.16 10.49 6.50 3.99 0.91 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 327.5032 99.8454 311.9122 1097.3962 0.2984 -0.1979 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3279 9.7190 508.6560 501.8715 36.6618 17.7502 31.5000 13.7498

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 313.4297 68.3726 305.8813 1098.1636 0.2854 -0.1157 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3179 9.7591 509.3681 501.6809 451.3937 0.0295 0.1355

 

NASA/TM—2013-218094 L–45
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 319.0372 0.0000 319.0372 1097.8419 0.2906 -0.0156 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7095 509.0733 501.8501 0.0000 0.0600 0.0922 -0.2121

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7252 10.2857 1.0213 517.1550 4.1088 326.5510 2.5314

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25874.248 0.342 72.328 454382.656 0.409221E-02

 

Melt Ratio at Stator LE, Throat, TE

0.40354E+00 0.44551E+00 0.56568E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.347 EfDer = 0.908 SH = 0.428318E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1590.744 10.286 517.148 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.254 WH2O = 0.212 lbm/sec H2O = 3.576g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.590 1593.118 1.376 0.252 53.487 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57072.195 38747.707 2.478 513.330 207.187 395.845 1.911

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 266.83 -0.09 266.83 0.24 0.34 267.76

 MEAN 16.97 0.00 -0.02 266.83 -0.09 266.83 0.24 0.32

 HUB 14.32 0.00 -0.02 266.83 -0.09 266.83 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 45.07 46.36 -1.29 267.36 377.80 9.88 511.50 501.57 35.74

 MEAN 41.45 43.80 -2.35 235.58 356.01 9.88 511.50 501.57 35.74

 HUB 36.70 37.84 -1.14 198.79 332.79 9.88 511.50 501.57 35.74

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 295.85 55.10 290.67 1101.48 0.27 2.16 1.89 8.34

 MEAN 16.57 300.78 78.52 290.35 1101.84 0.27 2.24 1.97 6.35

 HUB 13.89 321.63 138.43 290.31 1102.21 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 262.09 356.84 206.99 0.32 1042.01 0.92 0.83

 MEAN 230.08 327.53 151.55 0.30 1302.96 0.92 0.83 0.83 1.16

 HUB 192.82 295.36 54.39 0.27 1924.16 0.92 0.83

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.42 1.01 9.92 519.43 1.00 512.49 503.16 35.12

 MEAN 10.46 1.02 9.94 520.01 1.01 512.83 503.49 34.74

 HUB 10.54 1.03 9.95 521.38 1.01 513.17 504.41 34.34

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.73 35.46 31.50 3.96 0.93 0.11 1.40

 MEAN 15.13 27.56 23.50 4.06 0.89 0.15 1.62

 HUB 25.49 10.61 6.50 4.11 0.89 0.22 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.908 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 328.5881 78.9631 318.9592 1100.6172 0.2985 -0.1627 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4706 9.8530 511.7008 504.0583 36.0052 13.9048 32.4000 18.4952

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 326.5514 73.2359 318.2331 1100.7242 0.2967 -0.1723 2.2705

 

NASA/TM—2013-218094 L–46
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4548 9.8446 511.8005 504.0273 432.2457 0.0393 0.0983

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 324.7574 0.0000 324.7574 1100.8104 0.2950 -0.0702 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8096 511.8821 504.0658 0.0000 0.0600 0.1230 -0.2373

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5470 10.4097 1.0121 520.2478 3.1245 398.6317 3.0902

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 19696.420 0.287 55.059 473683.656 0.443066E-02

 

Melt Ratio at Stator LE, Throat, TE

0.90365E+00 0.94636E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.205 EfDer = 0.846 SH = 0.478657E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1590.744 10.410 520.247 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.229 WH2O = 0.237 lbm/sec H2O = 4.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.957 1588.375 1.375 0.252 53.504 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 56741.887 38739.945 2.481 509.668 205.391 384.739 1.873

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 267.19 -0.09 267.19 0.24 0.33 253.93

 MEAN 15.91 0.00 -0.02 267.19 -0.09 267.19 0.24 0.31

 HUB 13.07 0.00 -0.02 267.19 -0.09 267.19 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.60 47.36 -3.76 254.32 368.93 10.00 514.59 504.04 36.10

 MEAN 39.59 44.80 -5.21 220.90 346.74 10.00 514.59 504.04 36.10

 HUB 34.19 38.84 -4.65 181.44 323.02 10.00 514.59 504.04 36.10

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 293.95 39.45 291.29 1104.05 0.27 2.05 1.78 7.43

 MEAN 15.50 297.46 61.81 290.97 1104.46 0.27 2.13 1.86 5.75

 HUB 12.59 314.66 119.81 290.96 1104.86 0.28 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 249.04 358.86 209.59 0.33 709.50 0.92 0.77

 MEAN 215.14 328.89 153.32 0.30 959.41 0.92 0.77 0.77 1.12

 HUB 174.77 296.10 54.96 0.27 1509.62 0.92 0.77

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.50 1.01 10.00 521.81 1.00 514.96 505.43 36.70

 MEAN 10.53 1.01 10.02 522.36 1.00 515.35 505.72 36.25

 HUB 10.60 1.02 10.03 523.57 1.01 515.72 506.51 35.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.71 35.73 31.50 4.23 0.93 0.07 1.40

 MEAN 11.99 27.79 23.50 4.29 0.88 0.11 1.64

 HUB 22.38 10.70 6.50 4.20 0.88 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.846 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 338.0267 62.9457 332.1143 1102.4866 0.3066 -0.2713 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5322 9.8786 513.5294 506.5569 38.4497 10.7320 33.0000 22.2680

 

NASA/TM—2013-218094 L–47
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 346.3118 79.0806 337.1619 1102.0038 0.3143 -0.3924 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4940 9.8113 513.0814 506.7212 410.5396 0.0927 0.0697

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 337.2417 0.0000 337.2417 1102.5283 0.3059 -0.0868 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8219 513.5729 506.7130 0.0000 0.0600 0.1411 -0.3722

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3430 10.4685 1.0056 522.5774 2.3301 494.6276 3.8343

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14715.017 0.237 41.134 504882.031 0.508304E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0435 Tt4 = 522.5774 T1 = 500.8113

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 137249.08 383.6602 76.5209 1.1212 0.7304 6.7293 1.0435 37.3740

NASA/TM—2013-218094 L–48
5μm, 4 g/m3

, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.608 EfDer = 0.953 SH = 0.992095E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.451 2420.336 4.265 457.721 1.000 1.000 0.980

 W Kg/sec = 12.023 Wdry = 26.425 WH2O = 0.026 lbm/sec H2O = 0.394g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.650 2576.464 1.380 0.249 53.380 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64152.555 20746.836 3.315 831.557 250.838 619.754 2.471

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 185.15 -0.06 185.15 0.18 0.46 463.83

 MEAN 17.06 0.00 -0.02 185.15 -0.06 185.15 0.18 0.39

 HUB 12.51 0.00 -0.02 185.15 -0.06 185.15 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.98 50.47 16.51 435.73 473.50 4.17 454.97 451.85 37.87

 MEAN 62.81 47.20 15.61 360.33 405.18 4.17 454.97 451.85 37.87

 HUB 54.99 38.62 16.37 264.23 322.70 4.17 454.97 451.85 37.87

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 390.17 301.44 247.72 1051.77 0.37 7.29 6.52 16.04

 MEAN 18.04 394.52 304.36 251.01 1048.67 0.38 7.43 6.80 12.53

 HUB 15.00 426.85 341.90 255.55 1044.87 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 435.73 281.78 134.29 0.27 6220.07 0.92 0.87

 MEAN 380.95 262.43 76.58 0.25 5490.56 0.92 0.87 0.87 1.77

 HUB 316.82 256.78 25.08 0.25 5129.36 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.92 1.15 4.48 478.80 1.05 466.59 468.49 34.41

 MEAN 4.84 1.13 4.39 476.33 1.04 463.84 467.17 38.27

 HUB 4.80 1.13 4.29 475.11 1.04 460.49 467.01 43.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.59 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.49 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.22 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 405.9364 303.7706 269.2726 1048.2499 0.3873 -0.0354 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8484 4.3782 463.5425 467.8000 40.1117 48.4451 35.4000 -13.0451

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 267.1325 65.3488 259.0161 1056.6517 0.2528 0.5190 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8361 4.6287 471.0272 466.4515 554.9116 0.0363 0.6121

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 266.0807 0.0000 266.0807 1056.6504 0.2518 0.4877 1.3089

NASA/TM—2013-218094 L–49
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6075 471.0740 467.4357 0.0000 0.0600 0.0875 0.4736

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8126 4.8122 1.1284 476.7425 19.0240 167.1473 1.2957

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 118735.844 0.625 177.484 277492.250 0.190293E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.182 EfDer = 0.957 SH = 0.283381E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.451 2420.336 4.812 476.741 1.000 1.000 0.980

 W Kg/sec = 12.023 Wdry = 26.376 WH2O = 0.075 lbm/sec H2O = 1.205g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.464 2524.596 1.378 0.250 53.440 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59908.969 20731.762 2.600 590.487 227.120 468.502 2.063

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 243.48 -0.08 243.48 0.23 0.47 452.73

 MEAN 18.08 0.00 -0.02 243.48 -0.08 243.48 0.23 0.43

 HUB 15.21 0.00 -0.02 243.48 -0.08 243.48 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.71 46.36 14.35 434.05 497.75 4.64 472.01 470.11 54.83

 MEAN 57.48 42.30 15.18 381.84 452.93 4.64 472.01 470.11 54.83

 HUB 52.85 37.84 15.01 321.26 403.17 4.64 472.01 470.11 54.83

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 358.85 251.21 256.26 1070.60 0.34 2.33 2.04 9.02

 MEAN 18.01 358.19 247.55 258.88 1068.13 0.34 2.40 2.13 7.35

 HUB 15.22 379.32 274.49 261.80 1065.71 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 431.30 313.21 180.09 0.29 5131.40 0.92 0.88

 MEAN 380.40 290.98 132.84 0.27 4459.90 0.92 0.88 0.88 1.72

 HUB 321.53 265.99 47.04 0.25 4179.84 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.12 5.00 494.03 1.04 483.76 481.11 37.72

 MEAN 5.31 1.10 4.92 491.77 1.03 481.53 480.02 40.81

 HUB 5.28 1.10 4.85 490.83 1.03 479.35 479.98 44.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.43 35.10 31.50 3.60 0.93 0.55 1.40

 MEAN 43.72 27.16 23.50 3.66 0.95 0.53 1.63

 HUB 46.36 10.19 6.50 3.69 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 382.8207 248.2457 291.4202 1066.9484 0.3588 -0.1058 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3256 4.8789 480.5262 480.7886 42.6588 40.4259 30.6000 -9.8259

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 281.8147 59.7467 275.4085 1072.8628 0.2627 0.3739 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3191 5.0738 485.8773 479.2697 491.5697 0.0259 0.4694

 

NASA/TM—2013-218094 L–50
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 292.1463 0.0000 292.1463 1072.3136 0.2724 0.3600 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0397 485.4060 479.8379 0.0000 0.0600 0.0674 0.2905

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8297 5.3022 1.1018 492.2071 15.4676 187.9226 1.4568

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 97030.867 0.522 145.040 252081.109 0.326053E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.198 EfDer = 0.972 SH = 0.386383E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.451 2420.336 5.302 492.206 1.000 1.000 0.980

 W Kg/sec = 12.023 Wdry = 26.349 WH2O = 0.102 lbm/sec H2O = 1.753g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.437 2484.619 1.377 0.251 53.474 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56169.387 20723.295 2.603 545.479 209.595 424.468 2.025

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 247.12 -0.09 247.12 0.23 0.46 435.15

 MEAN 17.74 0.00 -0.02 247.12 -0.09 247.12 0.23 0.42

 HUB 15.05 0.00 -0.02 247.12 -0.09 247.12 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.76 46.36 13.40 423.91 490.75 5.11 487.35 480.80 42.80

 MEAN 56.60 43.40 13.20 374.66 448.89 5.11 487.35 480.80 42.80

 HUB 52.15 38.84 13.31 317.88 402.70 5.11 487.35 480.80 42.80

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 350.65 235.24 260.03 1086.10 0.32 2.26 1.98 8.75

 MEAN 17.51 352.00 234.69 262.34 1084.00 0.32 2.34 2.07 6.78

 HUB 14.85 375.11 265.59 264.90 1081.93 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 418.42 318.07 183.17 0.29 4661.85 0.92 0.89

 MEAN 369.76 295.07 135.07 0.27 4110.21 0.92 0.89 0.89 1.67

 HUB 313.65 269.23 48.06 0.25 3945.26 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.87 1.11 5.47 507.86 1.03 498.09 490.09 31.72

 MEAN 5.80 1.09 5.40 506.01 1.03 496.16 489.32 33.79

 HUB 5.78 1.09 5.33 505.45 1.03 494.27 489.54 35.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 42.14 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.82 27.24 23.50 3.74 0.94 0.50 1.62

 HUB 45.07 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 377.8096 236.2348 294.8444 1082.7828 0.3489 -0.1137 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8140 5.3519 495.1034 490.1216 35.3312 38.7024 31.5000 -7.2024

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 289.9989 63.2613 283.0148 1087.8546 0.2666 0.3235 2.3726

 

NASA/TM—2013-218094 L–51
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8098 5.5343 499.7613 488.7633 451.3937 0.0201 0.4442

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 294.9426 0.0000 294.9426 1087.5857 0.2712 0.3456 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5116 499.5331 489.3123 0.0000 0.0600 0.0538 0.2694

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8508 5.7957 1.0931 506.4398 14.2350 193.1359 1.4972

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89620.492 0.512 133.963 250575.719 0.446908E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.612 EfDer = 0.983 SH = 0.529753E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.451 2420.336 5.796 506.439 1.000 1.000 0.980

 W Kg/sec = 12.023 Wdry = 26.311 WH2O = 0.140 lbm/sec H2O = 2.552g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.293 2449.457 1.375 0.252 53.520 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52880.898 20711.465 2.637 513.330 194.673 395.845 2.033

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 247.22 -0.09 247.22 0.23 0.44 411.68

 MEAN 16.97 0.00 -0.02 247.22 -0.09 247.22 0.23 0.40

 HUB 14.32 0.00 -0.02 247.22 -0.09 247.22 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.72 46.36 12.36 406.80 476.10 5.60 501.60 490.42 36.38

 MEAN 55.41 43.80 11.61 358.45 435.50 5.60 501.60 490.42 36.38

 HUB 50.75 37.84 12.91 302.46 390.71 5.60 501.60 490.42 36.38

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 337.40 215.81 259.35 1099.88 0.31 2.16 1.89 8.34

 MEAN 16.57 338.71 215.34 261.45 1097.99 0.31 2.24 1.97 6.35

 HUB 13.89 360.39 245.61 263.73 1096.13 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.77 317.40 182.96 0.29 4076.08 0.92 0.90

 MEAN 350.06 294.12 134.73 0.27 3570.40 0.92 0.90 0.90 1.62

 HUB 293.38 268.02 47.76 0.24 3412.80 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.33 1.09 5.93 520.07 1.03 511.06 498.10 28.73

 MEAN 6.26 1.08 5.87 518.37 1.02 509.30 497.47 30.32

 HUB 6.24 1.08 5.80 517.85 1.02 507.57 497.69 31.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.76 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.48 27.26 23.50 3.76 0.94 0.48 1.62

 HUB 42.96 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.983 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 359.3188 216.5472 286.7356 1097.1287 0.3275 -0.0901 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2707 5.8294 508.5552 498.1388 31.3306 37.0607 32.4000 -4.6607

 

NASA/TM—2013-218094 L–52
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 287.8034 64.5459 280.4722 1101.0574 0.2614 0.2867 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2685 5.9827 512.2145 497.0464 432.2457 0.0154 0.4226

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 285.5491 0.0000 285.5491 1101.1454 0.2593 0.3322 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9760 512.3137 497.4740 0.0000 0.0600 0.0440 0.2702

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8653 6.2568 1.0796 518.7568 12.3239 208.0641 1.6129

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 77951.180 0.490 116.520 256520.156 0.605392E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.12045E-02 0.34728E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.154 EfDer = 0.991 SH = 0.689085E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.451 2420.336 6.257 518.749 1.000 1.000 0.980

 W Kg/sec = 12.023 Wdry = 26.269 WH2O = 0.182 lbm/sec H2O = 3.506g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.149 2420.203 1.373 0.254 53.572 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50079.063 20698.256 2.790 509.668 182.685 384.739 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 235.81 -0.08 235.81 0.21 0.41 386.91

 MEAN 15.91 0.00 -0.02 235.81 -0.08 235.81 0.21 0.37

 HUB 13.07 0.00 -0.02 235.81 -0.08 235.81 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.65 47.36 11.29 386.94 453.20 6.06 514.37 498.28 31.77

 MEAN 54.95 44.80 10.15 336.11 410.64 6.06 514.37 498.28 31.77

 HUB 49.50 38.84 10.66 276.06 363.12 6.06 514.37 498.28 31.77

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 320.34 202.80 247.97 1112.14 0.29 2.05 1.78 7.43

 MEAN 15.50 318.81 197.83 250.00 1110.20 0.29 2.13 1.86 5.75

 HUB 12.59 334.78 220.20 252.18 1108.28 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.92 304.15 176.12 0.27 3639.72 0.92 0.91

 MEAN 327.33 281.55 129.50 0.25 3067.20 0.92 0.91 0.91 1.61

 HUB 265.92 256.29 45.72 0.23 2773.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.08 6.39 530.84 1.02 522.76 504.52 25.54

 MEAN 6.68 1.07 6.31 528.94 1.02 520.93 503.80 26.92

 HUB 6.64 1.06 6.24 527.96 1.02 519.13 503.74 28.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.28 35.38 31.50 3.88 0.93 0.49 1.40

 MEAN 38.35 27.38 23.50 3.88 0.94 0.46 1.64

 HUB 41.13 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 348.6160 201.4586 284.5128 1108.8124 0.3144 -0.1693 2.0437

 

NASA/TM—2013-218094 L–53
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6826 6.2482 519.6703 504.5282 28.0358 35.3017 33.0000 -2.3017

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 290.6570 66.3718 282.9775 1111.8977 0.2614 0.1676 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6804 6.3751 522.5729 503.5459 410.5396 0.0259 0.3982

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 282.6824 0.0000 282.6824 1112.2209 0.2542 0.3216 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3879 522.8853 503.5757 0.0000 0.0600 0.0384 0.2014

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8825 6.6757 1.0669 529.1733 10.4985 227.5896 1.7643

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66699.406 0.465 99.701 269179.313 0.728921E-02

 

Melt Ratio at Stator LE, Throat, TE

0.40480E+00 0.47199E+00 0.67328E+00

 trTOT = 1.1561 Tt4 = 529.1733 T1 = 457.7213 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 450037.81 672.7081 85.6497 1.5653 0.8338 15.6082 1.1561 37.3740

NASA/TM—2013-218094 L–54
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.657 EfDer = 0.953 SH = 0.841283E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.534 2343.502 4.199 451.549 1.000 1.000 0.980

 W Kg/sec = 11.606 Wdry = 25.512 WH2O = 0.021 lbm/sec H2O = 0.334g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.398 2511.672 1.381 0.249 53.376 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61985.082 20028.389 3.405 831.557 244.219 619.754 2.538

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 178.90 -0.06 178.90 0.17 0.44 452.16

 MEAN 17.06 0.00 -0.02 178.90 -0.06 178.90 0.17 0.38

 HUB 12.51 0.00 -0.02 178.90 -0.06 178.90 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.02 50.47 16.55 421.90 458.32 4.11 448.98 447.09 42.41

 MEAN 62.86 47.20 15.66 348.90 392.14 4.11 448.98 447.09 42.41

 HUB 55.04 38.62 16.42 255.84 312.24 4.11 448.98 447.09 42.41

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 377.83 291.87 239.93 1044.21 0.36 7.29 6.52 16.04

 MEAN 18.04 381.98 294.76 242.95 1041.29 0.37 7.43 6.80 12.53

 HUB 15.00 413.07 331.00 247.11 1037.71 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 421.90 272.91 130.03 0.26 6022.51 0.92 0.87

 MEAN 368.85 254.00 74.09 0.24 5317.38 0.92 0.87 0.87 1.77

 HUB 306.76 248.30 24.24 0.24 4965.78 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.15 4.40 471.32 1.04 459.86 463.22 38.14

 MEAN 4.74 1.13 4.32 469.01 1.04 457.29 461.88 42.28

 HUB 4.70 1.12 4.22 467.85 1.04 454.16 461.64 47.98

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.58 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.50 16.96 12.70 4.26 0.95 0.53 2.22

 HUB 53.26 -5.60 -9.30 3.70 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 392.9966 294.1893 260.5744 1040.9033 0.3776 -0.0356 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7440 4.3052 457.0092 462.4495 44.1894 48.4675 35.4000 -13.0675

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 259.0102 63.3618 251.1405 1048.8247 0.2470 0.5188 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7329 4.5389 464.0140 461.2720 554.9116 0.0355 0.6113

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.9521 0.0000 257.9521 1048.8230 0.2459 0.4866 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5187 464.0594 462.1246 0.0000 0.0600 0.0877 0.4725

NASA/TM—2013-218094 L–55
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8124 4.7102 1.1217 469.3920 17.8457 167.0100 1.2947

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 111282.313 0.625 160.573 270409.125 0.155631E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.147 EfDer = 0.957 SH = 0.227505E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.534 2343.502 4.710 469.391 1.000 1.000 0.980

 W Kg/sec = 11.606 Wdry = 25.476 WH2O = 0.058 lbm/sec H2O = 0.963g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.806 2463.518 1.379 0.250 53.422 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58082.918 20017.072 2.658 590.487 222.179 468.502 2.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.06 -0.08 236.06 0.22 0.46 441.78

 MEAN 18.08 0.00 -0.02 236.06 -0.08 236.06 0.22 0.42

 HUB 15.21 0.00 -0.02 236.06 -0.08 236.06 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.68 46.36 14.32 420.27 482.10 4.55 464.94 464.39 59.34

 MEAN 57.45 42.30 15.15 369.72 438.72 4.55 464.94 464.39 59.34

 HUB 52.81 37.84 14.97 311.06 390.56 4.55 464.94 464.39 59.34

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 347.72 242.62 249.09 1062.02 0.33 2.33 2.04 9.02

 MEAN 18.01 347.17 239.32 251.50 1059.70 0.33 2.40 2.13 7.35

 HUB 15.22 367.67 265.66 254.18 1057.42 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 417.61 304.41 174.99 0.29 4955.93 0.92 0.88

 MEAN 368.32 282.65 129.00 0.27 4311.64 0.92 0.88 0.88 1.71

 HUB 311.32 258.25 45.67 0.24 4045.31 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.25 1.11 4.88 485.59 1.03 475.93 475.26 41.22

 MEAN 5.18 1.10 4.81 483.48 1.03 473.85 474.17 44.50

 HUB 5.15 1.09 4.74 482.61 1.03 471.81 474.07 47.97

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.25 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.58 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.26 10.19 6.50 3.69 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.0754 239.9933 283.0197 1058.5707 0.3505 -0.1064 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1874 4.7707 472.8979 474.8678 46.4742 40.2971 30.6000 -9.6971

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.0819 58.1073 267.8515 1064.1393 0.2576 0.3708 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1816 4.9514 477.8955 473.5490 491.5697 0.0250 0.4665

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.0584 0.0000 284.0584 1063.6130 0.2671 0.3573 0.5911

NASA/TM—2013-218094 L–56
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9196 477.4520 474.0528 0.0000 0.0600 0.0667 0.2873

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8304 5.1658 1.0967 483.8943 14.5052 188.2821 1.4596

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90816.625 0.521 131.042 245843.156 0.260923E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.078 EfDer = 0.973 SH = 0.308302E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.534 2343.502 5.166 483.893 1.000 1.000 0.980

 W Kg/sec = 11.606 Wdry = 25.455 WH2O = 0.079 lbm/sec H2O = 1.388g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.180 2426.321 1.378 0.251 53.448 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54632.195 20010.676 2.650 545.479 205.807 424.468 2.062

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.36 -0.08 240.36 0.23 0.45 424.94

 MEAN 17.74 0.00 -0.02 240.36 -0.08 240.36 0.23 0.41

 HUB 15.05 0.00 -0.02 240.36 -0.08 240.36 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.65 46.36 13.29 410.45 475.72 4.99 479.29 474.89 46.73

 MEAN 56.48 43.40 13.08 362.77 435.24 4.99 479.29 474.89 46.72

 HUB 52.02 38.84 13.18 307.79 390.59 4.99 479.29 474.89 46.73

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 340.02 226.61 253.50 1076.65 0.32 2.26 1.98 8.75

 MEAN 17.51 341.52 226.47 255.63 1074.67 0.32 2.34 2.07 6.78

 HUB 14.85 364.10 256.92 257.99 1072.74 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 405.13 310.05 178.52 0.29 4490.81 0.92 0.89 

 MEAN 358.02 287.50 131.55 0.27 3966.21 0.92 0.89 0.89 1.66

 HUB 303.70 262.19 46.77 0.24 3816.53 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.69 1.10 5.32 498.53 1.03 489.32 484.07 34.93

 MEAN 5.63 1.09 5.25 496.82 1.03 487.53 483.30 37.14

 HUB 5.61 1.09 5.19 496.33 1.03 485.77 483.47 39.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.79 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.54 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.88 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.6914 227.9581 287.2241 1073.5088 0.3416 -0.1148 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6396 5.2087 486.5204 484.0331 38.8323 38.4376 31.5000 -6.9376

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 282.8647 61.7050 276.0525 1078.2736 0.2623 0.3176 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6360 5.3767 490.8566 482.8466 451.3937 0.0193 0.4392

 

NASA/TM—2013-218094 L–57
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 287.6350 0.0000 287.6350 1078.0142 0.2668 0.3411 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3557 490.6411 483.3430 0.0000 0.0600 0.0526 0.2638

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8523 5.6229 1.0885 497.2272 13.3350 194.0667 1.5044

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83735.945 0.510 120.825 244646.547 0.356428E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.414 EfDer = 0.984 SH = 0.421952E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.534 2343.502 5.623 497.226 1.000 1.000 0.980

 W Kg/sec = 11.606 Wdry = 25.426 WH2O = 0.108 lbm/sec H2O = 2.012g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.356 2393.570 1.376 0.252 53.485 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51582.398 20001.648 2.676 513.330 191.797 395.845 2.064

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.15 -0.08 241.15 0.22 0.43 402.29

 MEAN 16.97 0.00 -0.02 241.15 -0.08 241.15 0.22 0.39

 HUB 14.32 0.00 -0.02 241.15 -0.08 241.15 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.53 46.36 12.17 393.88 461.92 5.43 492.61 484.33 40.10

 MEAN 55.21 43.80 11.41 347.07 422.69 5.43 492.61 484.33 40.10

 HUB 50.54 37.84 12.70 292.86 379.43 5.43 492.61 484.33 40.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.48 207.30 253.51 1089.66 0.30 2.16 1.89 8.34

 MEAN 16.57 329.01 207.37 255.43 1087.89 0.30 2.24 1.97 6.35

 HUB 13.89 350.27 237.42 257.54 1086.15 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.11 310.22 178.81 0.28 3915.49 0.92 0.90

 MEAN 338.95 287.33 131.58 0.26 3438.34 0.92 0.90 0.90 1.61

 HUB 284.06 261.73 46.65 0.24 3298.90 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.11 1.09 5.75 509.94 1.03 501.43 491.88 31.89

 MEAN 6.05 1.08 5.68 508.39 1.02 499.80 491.25 33.60

 HUB 6.03 1.07 5.62 507.94 1.02 498.20 491.45 35.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.27 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.07 27.25 23.50 3.75 0.94 0.47 1.62

 HUB 42.67 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.1985 208.5366 280.0929 1087.0554 0.3212 -0.0914 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0609 5.6494 499.0841 491.8822 34.7291 36.6687 32.4000 -4.2687

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 281.4368 63.1180 274.2677 1090.7321 0.2580 0.2782 2.2705

 

NASA/TM—2013-218094 L–58
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0591 5.7895 502.4747 490.9236 432.2457 0.0147 0.4158

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 279.2066 0.0000 279.2066 1090.8239 0.2560 0.3258 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7835 502.5750 491.3500 0.0000 0.0600 0.0428 0.2625

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8667 6.0484 1.0757 508.7572 11.5320 209.6811 1.6254

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72688.445 0.488 104.885 250689.453 0.483867E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.882 EfDer = 0.992 SH = 0.568423E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.534 2343.502 6.048 508.756 1.000 1.000 0.980

 W Kg/sec = 11.606 Wdry = 25.389 WH2O = 0.145 lbm/sec H2O = 2.854g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.460 2366.292 1.374 0.253 53.533 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48980.574 19989.967 2.823 509.668 180.524 384.739 2.131 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 230.63 -0.08 230.63 0.21 0.40 378.29

 MEAN 15.91 0.00 -0.02 230.63 -0.08 230.63 0.21 0.37

 HUB 13.07 0.00 -0.02 230.63 -0.08 230.63 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.39 47.36 11.03 374.66 440.02 5.87 504.55 492.44 36.55

 MEAN 54.68 44.80 9.88 325.44 398.94 5.87 504.55 492.44 36.55

 HUB 49.22 38.84 10.38 267.29 353.10 5.87 504.55 492.44 36.55

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 311.14 194.37 242.96 1101.24 0.28 2.05 1.78 7.43

 MEAN 15.50 309.99 190.12 244.84 1099.42 0.28 2.13 1.86 5.75

 HUB 12.59 325.86 212.73 246.85 1097.63 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.89 297.98 172.52 0.27 3488.47 0.92 0.91

 MEAN 316.94 275.74 126.82 0.25 2947.65 0.92 0.91 0.91 1.60

 HUB 257.48 250.87 44.75 0.23 2679.29 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.51 1.08 6.16 520.03 1.02 512.38 498.89 30.33

 MEAN 6.43 1.06 6.10 518.29 1.02 510.69 498.19 31.93

 HUB 6.40 1.06 6.03 517.42 1.02 509.02 498.14 33.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.66 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.83 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.75 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.2713 193.6047 278.6077 1098.0702 0.3090 -0.1713 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4399 6.0347 509.4888 498.9575 33.4152 34.7955 33.0000 -1.7955

 

NASA/TM—2013-218094 L–59
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 284.8503 65.0458 277.3243 1100.9449 0.2587 0.1588 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4382 6.1505 512.1700 498.1312 410.5396 0.0250 0.3896

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 277.1155 0.0000 277.1155 1101.2870 0.2516 0.3129 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1615 512.5027 498.3821 0.0000 0.0600 0.0377 0.1900

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8782 6.4337 1.0637 518.5642 9.8233 229.6357 1.7801

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 62206.523 0.462 89.760 263304.094 0.636345E-02

 

Melt Ratio at Stator LE, Throat, TE

0.12293E-01 0.27082E-01 0.10431E+00

 trTOT = 1.1484 Tt4 = 518.5642 T1 = 451.5491

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 420729.84 607.0848 83.3982 1.5321 0.8343 15.6573 1.1484 37.3740

NASA/TM—2013-218094 L–60
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.660 EfDer = 0.953 SH = 0.757620E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.153 2313.630 4.337 449.660 1.000 1.000 0.980

 W Kg/sec = 11.888 Wdry = 26.133 WH2O = 0.020 lbm/sec H2O = 0.312g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.531 2484.860 1.381 0.249 53.373 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61189.215 20514.600 3.441 831.557 241.667 619.754 2.564

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 176.60 -0.06 176.60 0.17 0.44 447.34

 MEAN 17.06 0.00 -0.02 176.60 -0.06 176.60 0.17 0.38

 HUB 12.51 0.00 -0.02 176.60 -0.06 176.60 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.03 50.47 16.56 416.52 452.47 4.25 447.16 445.64 43.21

 MEAN 62.86 47.20 15.66 344.45 387.14 4.25 447.16 445.64 43.21

 HUB 55.05 38.62 16.43 252.58 308.25 4.25 447.16 445.64 43.21

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 373.07 288.05 237.09 1041.82 0.36 7.29 6.52 16.04

 MEAN 18.04 377.18 290.97 240.00 1038.97 0.36 7.43 6.80 12.53

 HUB 15.00 407.87 326.83 244.02 1035.48 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 416.52 269.66 128.48 0.26 5943.69 0.92 0.87

 MEAN 364.15 250.91 73.18 0.24 5249.01 0.92 0.87 0.87 1.77

 HUB 302.85 245.20 23.97 0.24 4903.17 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.54 468.93 1.04 457.75 461.57 38.87

 MEAN 4.88 1.12 4.46 466.68 1.04 455.26 460.21 43.03

 HUB 4.84 1.12 4.36 465.56 1.04 452.20 459.92 48.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.54 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.48 16.96 12.70 4.26 0.95 0.53 2.22

 HUB 53.25 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 388.0522 290.4065 257.3879 1038.6014 0.3736 -0.0357 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8873 4.4439 454.9754 460.7486 44.9372 48.4494 35.4000 -13.0494

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.0486 62.6373 248.2689 1046.3334 0.2447 0.5184 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8763 4.6799 461.7953 459.6719 554.9116 0.0351 0.6105

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 254.9843 0.0000 254.9843 1046.3345 0.2437 0.4859 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6594 461.8402 460.4531 0.0000 0.0600 0.0876 0.4718

NASA/TM—2013-218094 L–61
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8126 4.8532 1.1190 467.0529 17.3954 167.0345 1.2948

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 108435.391 0.625 160.258 277753.188 0.138686E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.114 EfDer = 0.957 SH = 0.201867E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.153 2313.630 4.853 467.052 1.000 1.000 0.980

 W Kg/sec = 11.888 Wdry = 26.100 WH2O = 0.053 lbm/sec H2O = 0.886g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.168 2438.198 1.379 0.250 53.414 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 57415.754 20504.412 2.681 590.487 220.277 468.502 2.127

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.35 -0.08 233.35 0.22 0.45 437.24

 MEAN 18.08 0.00 -0.02 233.35 -0.08 233.35 0.22 0.41

 HUB 15.21 0.00 -0.02 233.35 -0.08 233.35 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.65 46.36 14.29 414.91 476.10 4.69 462.70 462.54 60.18

 MEAN 57.41 42.30 15.11 365.00 433.29 4.69 462.70 462.54 60.18

 HUB 52.78 37.84 14.94 307.09 385.76 4.69 462.70 462.54 60.18

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 343.44 239.16 246.48 1059.24 0.32 2.33 2.04 9.02

 MEAN 18.01 342.95 236.03 248.81 1056.98 0.32 2.40 2.13 7.35

 HUB 15.22 363.25 262.20 251.40 1054.75 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 412.28 301.21 173.13 0.28 4885.25 0.92 0.88

 MEAN 363.62 279.62 127.59 0.26 4252.36 0.92 0.88 0.88 1.71

 HUB 307.36 255.42 45.16 0.24 3992.70 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.11 5.02 482.83 1.03 473.39 473.39 42.03

 MEAN 5.32 1.10 4.95 480.78 1.03 471.38 472.28 45.32

 HUB 5.29 1.09 4.88 479.95 1.03 469.39 472.15 48.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.14 35.08 31.50 3.58 0.93 0.55 1.40

 MEAN 43.49 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.20 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.6098 236.6937 279.9622 1055.8656 0.3472 -0.1067 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3341 4.9133 470.4428 472.9457 47.3203 40.2128 30.6000 -9.6128

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 271.2811 57.5135 265.1144 1061.2966 0.2556 0.3690 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3285 5.0952 475.3033 471.7333 491.5697 0.0246 0.4647

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 281.1255 0.0000 281.1255 1060.7803 0.2650 0.3558 0.5911

NASA/TM—2013-218094 L–62
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0630 474.8698 472.2004 0.0000 0.0600 0.0662 0.2854

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8309 5.3125 1.0946 481.1852 14.1349 188.5487 1.4616

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 88424.859 0.520 130.684 252607.484 0.231261E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.011 EfDer = 0.974 SH = 0.272999E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.153 2313.630 5.312 481.184 1.000 1.000 0.980

 W Kg/sec = 11.888 Wdry = 26.081 WH2O = 0.071 lbm/sec H2O = 1.272g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.700 2402.127 1.378 0.250 53.437 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54074.359 20498.648 2.669 545.479 204.355 424.468 2.077 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 237.91 -0.08 237.91 0.22 0.44 420.71

 MEAN 17.74 0.00 -0.02 237.91 -0.08 237.91 0.22 0.40

 HUB 15.05 0.00 -0.02 237.91 -0.08 237.91 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.59 46.36 13.23 405.22 469.97 5.13 476.67 472.98 47.65

 MEAN 56.41 43.40 13.01 358.14 430.03 5.13 476.67 472.98 47.65

 HUB 51.95 38.84 13.11 303.86 385.98 5.13 476.67 472.98 47.65

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.96 223.15 251.15 1073.52 0.31 2.26 1.98 8.75

 MEAN 17.51 337.51 223.16 253.21 1071.60 0.31 2.34 2.07 6.78

 HUB 14.85 359.92 253.51 255.49 1069.71 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 399.97 307.15 176.82 0.29 4422.24 0.92 0.89

 MEAN 353.46 284.77 130.30 0.27 3908.19 0.92 0.89 0.89 1.66

 HUB 299.82 259.65 46.32 0.24 3765.83 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.84 1.10 5.46 495.43 1.03 486.42 482.13 35.78

 MEAN 5.78 1.09 5.40 493.77 1.03 484.69 481.35 38.01

 HUB 5.76 1.08 5.33 493.32 1.03 482.98 481.51 40.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.62 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 41.39 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.78 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 362.4637 224.6231 284.4722 1070.4534 0.3386 -0.1152 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7893 5.3541 483.6986 482.0590 39.7382 38.2951 31.5000 -6.7951

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 280.3048 61.1466 273.5542 1075.0938 0.2607 0.3146 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7858 5.5227 487.9088 480.9637 451.3937 0.0189 0.4366

 

NASA/TM—2013-218094 L–63
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 285.0096 0.0000 285.0096 1074.8395 0.2652 0.3388 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5016 487.6978 481.4278 0.0000 0.0600 0.0520 0.2609

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8531 5.7727 1.0866 494.1719 12.9888 194.5771 1.5083

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 81469.008 0.509 120.404 251493.000 0.315454E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.313 EfDer = 0.985 SH = 0.373237E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.153 2313.630 5.773 494.171 1.000 1.000 0.980

 W Kg/sec = 11.888 Wdry = 26.055 WH2O = 0.098 lbm/sec H2O = 1.839g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.003 2370.353 1.377 0.251 53.469 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51115.332 20490.502 2.692 513.330 190.705 395.845 2.076

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 238.97 -0.08 238.97 0.22 0.42 398.39

 MEAN 16.97 0.00 -0.02 238.97 -0.08 238.97 0.22 0.39

 HUB 14.32 0.00 -0.02 238.97 -0.08 238.97 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.43 46.36 12.07 388.86 456.49 5.58 489.63 482.35 41.10

 MEAN 55.11 43.80 11.31 342.64 417.81 5.58 489.63 482.35 41.10

 HUB 50.43 37.84 12.59 289.12 375.16 5.58 489.63 482.35 41.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.70 203.89 251.42 1086.23 0.30 2.16 1.89 8.34

 MEAN 16.57 325.32 204.16 253.29 1084.51 0.30 2.24 1.97 6.35

 HUB 13.89 346.49 234.24 255.32 1082.81 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 381.19 307.65 177.31 0.28 3850.94 0.92 0.90

 MEAN 334.63 284.92 130.47 0.26 3385.07 0.92 0.90 0.90 1.61

 HUB 280.44 259.47 46.20 0.24 3254.83 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.26 1.08 5.89 506.54 1.03 498.20 489.88 32.80

 MEAN 6.20 1.07 5.83 505.04 1.02 496.62 489.24 34.53

 HUB 6.18 1.07 5.77 504.62 1.02 495.07 489.42 36.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.04 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.87 27.25 23.50 3.75 0.94 0.47 1.62

 HUB 42.53 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 345.3652 205.3054 277.7171 1083.6884 0.3187 -0.0918 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2127 5.7971 495.9216 489.8461 35.6912 36.4741 32.4000 -4.0741

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 279.1756 62.6109 272.0641 1087.2627 0.2568 0.2742 2.2705

 

NASA/TM—2013-218094 L–64
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2110 5.9371 499.2066 488.9585 432.2457 0.0144 0.4124

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 276.9509 0.0000 276.9509 1087.3538 0.2547 0.3226 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9312 499.3059 489.3585 0.0000 0.0600 0.0423 0.2588

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8676 6.2003 1.0741 505.3983 11.2285 210.4799 1.6316

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 70664.789 0.486 104.436 257804.938 0.427863E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.753 EfDer = 0.993 SH = 0.502332E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.153 2313.630 6.200 505.397 1.000 1.000 0.980

 W Kg/sec = 11.888 Wdry = 26.021 WH2O = 0.131 lbm/sec H2O = 2.604g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.204 2343.879 1.375 0.252 53.511 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48586.098 20479.979 2.836 509.668 179.704 384.739 2.141

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 228.78 -0.08 228.78 0.21 0.40 374.71

 MEAN 15.91 0.00 -0.02 228.78 -0.08 228.78 0.21 0.36

 HUB 13.07 0.00 -0.02 228.78 -0.08 228.78 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.27 47.36 10.91 369.89 434.98 6.02 501.25 490.38 37.59

 MEAN 54.55 44.80 9.75 321.29 394.48 6.02 501.25 490.38 37.59

 HUB 49.08 38.84 10.24 263.89 349.31 6.02 501.25 490.38 37.59

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 307.62 190.95 241.19 1097.55 0.28 2.05 1.78 7.43

 MEAN 15.50 306.65 187.03 243.01 1095.79 0.28 2.13 1.86 5.75

 HUB 12.59 322.53 209.82 244.95 1094.04 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 362.21 295.81 171.26 0.27 3427.09 0.92 0.91

 MEAN 312.90 273.67 125.87 0.25 2899.76 0.92 0.91 0.91 1.59

 HUB 254.20 248.94 44.37 0.23 2642.70 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.66 1.07 6.31 516.36 1.02 508.86 496.81 31.32

 MEAN 6.59 1.06 6.24 514.67 1.02 507.22 496.10 32.94

 HUB 6.55 1.06 6.18 513.85 1.02 505.61 496.04 34.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.37 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.58 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.58 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 335.7433 190.4587 276.4942 1094.4520 0.3068 -0.1723 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5929 6.1835 506.0394 496.8408 34.4776 34.5604 33.0000 -1.5604

 

NASA/TM—2013-218094 L–65
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 282.7931 64.5760 275.3214 1097.2427 0.2577 0.1538 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5913 6.2989 508.6317 496.0875 410.5396 0.0246 0.3857

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 275.1285 0.0000 275.1285 1097.5933 0.2507 0.3089 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3099 508.9710 496.4171 0.0000 0.0600 0.0374 0.1848

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8775 6.5867 1.0623 514.9584 9.5619 230.7638 1.7889

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 60426.930 0.461 89.306 270861.156 0.568061E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.58309E-03

 trTOT = 1.1452 Tt4 = 514.9584 T1 = 449.6602

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 409420.97 605.0885 82.5309 1.5187 0.8349 15.6595 1.1452 37.3740

NASA/TM—2013-218094 L–66
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.685 EfDer = 0.953 SH = 0.755954E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.139 2245.949 4.829 451.595 1.000 1.000 0.980

 W Kg/sec = 12.791 Wdry = 28.118 WH2O = 0.021 lbm/sec H2O = 0.345g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.933 2407.002 1.381 0.249 53.373 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 59335.121 22073.090 3.553 831.557 234.065 619.754 2.648

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 171.25 -0.06 171.25 0.17 0.43 433.32

 MEAN 17.06 0.00 -0.02 171.25 -0.06 171.25 0.17 0.36

 HUB 12.51 0.00 -0.02 171.25 -0.06 171.25 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.05 50.47 16.58 404.34 439.16 4.74 449.24 447.61 43.33

 MEAN 62.88 47.20 15.68 334.37 375.73 4.74 449.24 447.61 43.33

 HUB 55.07 38.62 16.45 245.19 299.12 4.74 449.24 447.61 43.33

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 362.29 279.47 230.54 1043.44 0.35 7.29 6.52 16.04

 MEAN 18.04 366.26 282.43 233.19 1040.77 0.35 7.43 6.80 12.53

 HUB 15.00 395.90 317.24 236.84 1037.50 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.34 262.19 124.87 0.25 5766.61 0.92 0.87

 MEAN 353.50 243.78 71.07 0.23 5094.85 0.92 0.87 0.87 1.77

 HUB 293.99 237.98 23.25 0.23 4759.38 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 469.74 1.04 459.20 462.70 39.38

 MEAN 5.39 1.12 4.96 467.63 1.04 456.86 461.39 43.29

 HUB 5.35 1.11 4.85 466.57 1.03 453.99 461.09 48.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.48 28.44 24.20 4.24 0.93 0.58 1.80

 MEAN 50.45 16.95 12.70 4.25 0.95 0.53 2.22

 HUB 53.26 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 376.7956 281.8773 250.0402 1040.4199 0.3622 -0.0360 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.4015 4.9395 456.5926 461.9023 45.1266 48.4253 35.4000 -13.0253

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 249.3058 60.9878 241.7309 1047.6678 0.2380 0.5174 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3905 5.1849 462.9946 460.9288 554.9116 0.0339 0.6087

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 248.2224 0.0000 248.2224 1047.6738 0.2369 0.4842 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1632 463.0389 461.6404 0.0000 0.0600 0.0874 0.4699

NASA/TM—2013-218094 L–67
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8124 5.3660 1.1113 467.9787 16.3860 166.9854 1.2945

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 102150.547 0.625 162.439 297596.563 0.133465E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.035 EfDer = 0.958 SH = 0.191467E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.139 2245.949 5.366 467.978 1.000 1.000 0.980

 W Kg/sec = 12.791 Wdry = 28.086 WH2O = 0.054 lbm/sec H2O = 0.928g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.221 2364.531 1.379 0.250 53.410 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55906.008 22063.020 2.752 590.487 214.563 468.502 2.184

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 227.22 -0.08 227.22 0.22 0.44 424.02

 MEAN 18.08 0.00 -0.02 227.22 -0.08 227.22 0.22 0.40

 HUB 15.21 0.00 -0.02 227.22 -0.08 227.22 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.58 46.36 14.22 402.77 462.51 5.20 463.85 463.58 59.96

 MEAN 57.33 42.30 15.03 354.33 420.99 5.20 463.85 463.58 59.96

 HUB 52.69 37.84 14.85 298.11 374.89 5.20 463.85 463.58 59.96

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 333.78 231.25 240.70 1059.76 0.31 2.33 2.04 9.02

 MEAN 18.01 333.43 228.50 242.82 1057.66 0.32 2.40 2.13 7.35

 HUB 15.22 353.30 254.37 245.18 1055.58 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 400.22 294.09 168.98 0.28 4723.67 0.92 0.88

 MEAN 352.99 272.87 124.49 0.26 4116.69 0.92 0.88 0.88 1.70

 HUB 298.36 249.10 43.99 0.24 3873.48 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.93 1.10 5.54 482.79 1.03 473.88 473.94 42.94

 MEAN 5.85 1.09 5.47 480.89 1.03 471.99 472.88 46.07

 HUB 5.82 1.09 5.39 480.12 1.03 470.14 472.75 49.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.85 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 43.26 27.14 23.50 3.64 0.95 0.52 1.63

 HUB 46.05 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 356.5220 229.1415 273.1338 1056.6024 0.3374 -0.1075 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8641 5.4259 471.1030 473.5016 48.0000 39.9945 30.6000 -9.3945

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 265.1061 56.2044 259.0798 1061.6768 0.2497 0.3642 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8587 5.6136 475.6462 472.4136 491.5697 0.0235 0.4602

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 274.6439 0.0000 274.6439 1061.1901 0.2588 0.3518 0.5911

NASA/TM—2013-218094 L–68
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5801 475.2355 472.8376 0.0000 0.0600 0.0650 0.2806

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8321 5.8421 1.0887 481.2646 13.2885 189.2057 1.4667

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83110.109 0.519 132.161 271011.406 0.217811E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.831 EfDer = 0.975 SH = 0.254969E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.139 2245.949 5.842 481.264 1.000 1.000 0.980

 W Kg/sec = 12.791 Wdry = 28.068 WH2O = 0.072 lbm/sec H2O = 1.308g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.202 2331.665 1.378 0.250 53.431 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52851.129 22057.486 2.728 545.479 199.943 424.468 2.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 232.53 -0.08 232.53 0.22 0.43 408.36

 MEAN 17.74 0.00 -0.02 232.53 -0.08 232.53 0.22 0.39

 HUB 15.05 0.00 -0.02 232.53 -0.08 232.53 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.42 46.36 13.06 393.36 457.02 5.65 476.95 473.55 48.43

 MEAN 56.23 43.40 12.83 347.67 418.33 5.65 476.95 473.55 48.43

 HUB 51.76 38.84 12.92 294.97 375.67 5.65 476.95 473.55 48.43

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 326.83 215.03 246.12 1073.14 0.30 2.26 1.98 8.75

 MEAN 17.51 328.59 215.56 248.00 1071.36 0.31 2.34 2.07 6.78

 HUB 14.85 350.61 245.74 250.08 1069.60 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.27 300.98 173.23 0.28 4261.44 0.92 0.89

 MEAN 343.12 278.89 127.56 0.26 3775.08 0.92 0.89 0.89 1.64

 HUB 291.05 254.16 45.32 0.24 3650.38 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.39 1.09 5.99 494.60 1.03 486.07 482.31 37.08

 MEAN 6.32 1.08 5.93 493.07 1.02 484.46 481.56 39.22

 HUB 6.31 1.08 5.86 492.68 1.02 482.87 481.71 41.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.14 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 41.00 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.50 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.0775 216.9713 278.5448 1070.2582 0.3299 -0.1168 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3335 5.8804 483.5072 482.2227 40.9273 37.9167 31.5000 -6.4167

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 274.8743 59.9620 268.2544 1074.5774 0.2558 0.3063 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3303 6.0529 487.4243 481.2418 451.3937 0.0178 0.4296

 

NASA/TM—2013-218094 L–69
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 279.4295 0.0000 279.4295 1074.3367 0.2601 0.3325 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0311 487.2238 481.6616 0.0000 0.0600 0.0504 0.2531

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8550 6.3169 1.0813 493.4503 12.1876 195.9473 1.5190

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76403.484 0.507 121.496 270231.750 0.292184E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.036 EfDer = 0.986 SH = 0.342643E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.139 2245.949 6.317 493.449 1.000 1.000 0.980

 W Kg/sec = 12.791 Wdry = 28.043 WH2O = 0.096 lbm/sec H2O = 1.852g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.869 2302.695 1.377 0.251 53.459 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50132.250 22049.828 2.740 513.330 187.345 395.845 2.113

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 234.38 -0.08 234.38 0.22 0.41 387.01

 MEAN 16.97 0.00 -0.02 234.38 -0.08 234.38 0.22 0.38

 HUB 14.32 0.00 -0.02 234.38 -0.08 234.38 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.17 46.36 11.81 377.49 444.40 6.11 489.08 482.50 42.28

 MEAN 54.84 43.80 11.04 332.62 406.97 6.11 489.08 482.50 42.28

 HUB 50.14 37.84 12.30 280.67 365.72 6.11 489.08 482.50 42.28

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 315.31 195.76 247.18 1085.03 0.29 2.16 1.89 8.34

 MEAN 16.57 317.20 196.67 248.87 1083.44 0.29 2.24 1.97 6.35

 HUB 13.89 338.15 226.90 250.73 1081.87 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 370.04 302.44 174.28 0.28 3697.50 0.92 0.90

 MEAN 324.84 279.94 128.17 0.26 3260.98 0.92 0.90 0.90 1.59

 HUB 272.24 254.80 45.34 0.24 3152.76 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.82 1.08 6.44 504.98 1.02 497.07 489.69 34.26

 MEAN 6.76 1.07 6.37 503.62 1.02 495.61 489.09 35.93

 HUB 6.74 1.07 6.31 503.28 1.02 494.18 489.27 37.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.38 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.32 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.14 10.25 6.50 3.75 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 336.9770 197.7778 272.8323 1082.6479 0.3113 -0.0934 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7680 6.3352 494.9324 489.6609 37.1029 35.9386 32.4000 -3.5386

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 274.6102 61.5870 267.6150 1085.9529 0.2529 0.2627 2.2705

 

NASA/TM—2013-218094 L–70
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7666 6.4769 497.9662 488.8722 432.2457 0.0136 0.4033

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 272.3922 0.0000 272.3922 1086.0437 0.2508 0.3138 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4710 498.0635 489.2325 0.0000 0.0600 0.0409 0.2482

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8697 6.7557 1.0695 503.9629 10.5145 212.7201 1.6490

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66108.844 0.483 105.126 277392.844 0.389901E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.392 EfDer = 0.994 SH = 0.454115E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.139 2245.949 6.756 503.962 1.000 1.000 0.980

 W Kg/sec = 12.791 Wdry = 28.012 WH2O = 0.128 lbm/sec H2O = 2.575g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.354 2278.551 1.376 0.252 53.496 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 47797.914 22040.063 2.877 509.668 177.157 384.739 2.172

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 225.07 -0.08 225.07 0.21 0.39 364.27

 MEAN 15.91 0.00 -0.02 225.07 -0.08 225.07 0.21 0.35

 HUB 13.07 0.00 -0.02 225.07 -0.08 225.07 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.93 47.36 10.57 359.06 423.84 6.56 499.94 490.15 38.99

 MEAN 54.19 44.80 9.39 311.89 384.68 6.56 499.94 490.15 38.99

 HUB 48.71 38.84 9.87 256.17 341.05 6.56 499.94 490.15 38.99

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.93 182.80 237.78 1095.64 0.27 2.05 1.78 7.43

 MEAN 15.50 299.39 179.72 239.45 1094.00 0.27 2.13 1.86 5.75

 HUB 12.59 315.29 203.03 241.22 1092.39 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.62 291.62 168.82 0.27 3280.83 0.92 0.91

 MEAN 303.75 269.66 124.02 0.25 2786.51 0.92 0.91 0.91 1.58

 HUB 246.76 245.16 43.73 0.22 2557.14 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.22 1.07 6.86 514.16 1.02 507.03 496.30 32.88

 MEAN 7.15 1.06 6.79 512.62 1.02 505.52 495.62 34.47

 HUB 7.12 1.05 6.72 511.91 1.02 504.03 495.58 36.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.55 35.37 31.50 3.87 0.93 0.46 1.40

 MEAN 36.89 27.38 23.50 3.88 0.94 0.44 1.64

 HUB 40.09 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.1533 183.0186 272.3762 1092.7103 0.3003 -0.1750 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1561 6.7293 504.3654 496.3189 36.0309 33.8985 33.0000 -0.8985

 

NASA/TM—2013-218094 L–71
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 278.8824 63.6830 271.5140 1095.2671 0.2546 0.1383 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1548 6.8446 506.7362 495.6577 410.5396 0.0237 0.3749

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 271.3306 0.0000 271.3306 1095.6100 0.2477 0.2975 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8563 507.0663 495.9516 0.0000 0.0600 0.0369 0.1699

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8788 7.1499 1.0584 512.8986 8.9374 233.9989 1.8139

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 56395.438 0.456 89.679 291784.531 0.510429E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1357 Tt4 = 512.8986 T1 = 451.5953

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 384168.44 610.9003 79.9331 1.4807 0.8366 15.6847 1.1357 37.3740

NASA/TM—2013-218094 L–72
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.178 EfDer = 0.965 SH = 0.102505E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.273 2132.713 5.592 461.406 1.000 1.000 0.980

 W Kg/sec = 14.670 Wdry = 32.240 WH2O = 0.033 lbm/sec H2O = 0.531g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.011 2261.226 1.380 0.249 53.382 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60046.512 25312.879 3.549 831.557 234.340 619.754 2.645

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.30 -0.06 173.30 0.17 0.40 407.08

 MEAN 17.06 0.00 -0.02 173.30 -0.06 173.30 0.17 0.35

 HUB 12.51 0.00 -0.02 173.30 -0.06 173.30 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.71 50.47 15.24 383.95 421.31 5.49 459.00 456.30 42.49

 MEAN 61.38 47.20 14.18 317.51 361.78 5.49 459.00 456.30 42.49

 HUB 53.35 38.62 14.73 232.83 290.29 5.49 459.00 456.30 42.49

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 348.25 257.43 234.54 1052.77 0.33 7.29 6.52 16.04

 MEAN 18.04 354.59 263.87 236.86 1050.51 0.34 7.43 6.80 12.53

 HUB 15.00 386.69 303.06 240.17 1047.63 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.95 266.49 126.53 0.25 5311.98 0.92 0.88

 MEAN 335.68 247.51 71.81 0.24 4760.17 0.92 0.88 0.88 1.67

 HUB 279.17 241.36 23.89 0.23 4546.64 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.78 477.26 1.03 467.54 469.34 40.01

 MEAN 6.16 1.10 5.70 475.62 1.03 465.53 468.41 43.21

 HUB 6.14 1.10 5.59 474.98 1.03 462.99 468.46 47.64

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.66 28.35 24.20 4.15 0.93 0.54 1.80

 MEAN 48.09 16.87 12.70 4.17 0.95 0.48 2.22

 HUB 51.60 -5.68 -9.30 3.62 0.95 0.36 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.965 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.8943 263.3567 254.0116 1050.1049 0.3484 -0.0413 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1736 5.6830 465.2258 468.9318 45.0018 46.0348 35.4000 -10.6348

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 254.4744 62.2522 246.7425 1056.3173 0.2409 0.4764 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1654 5.9247 470.7630 467.9897 554.9116 0.0270 0.5656

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 253.1017 0.0000 253.1017 1056.3442 0.2396 0.4550 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9062 470.8199 468.6823 0.0000 0.0600 0.0722 0.4384

NASA/TM—2013-218094 L–73
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8308 6.1435 1.0986 475.9497 14.5463 174.2580 1.3508

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90792.297 0.616 165.585 335824.844 0.166857E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.157 EfDer = 0.973 SH = 0.229818E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.273 2132.713 6.143 475.949 1.000 1.000 0.980

 W Kg/sec = 14.670 Wdry = 32.199 WH2O = 0.074 lbm/sec H2O = 1.253g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.972 2226.435 1.379 0.250 53.423 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57000.926 25300.176 2.723 590.487 216.819 468.502 2.161

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 231.67 -0.08 231.67 0.22 0.42 399.26

 MEAN 18.08 0.00 -0.02 231.67 -0.08 231.67 0.22 0.39

 HUB 15.21 0.00 -0.02 231.67 -0.08 231.67 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.80 46.36 12.44 382.46 447.23 5.94 471.66 470.63 57.85

 MEAN 55.46 42.30 13.16 336.46 408.57 5.94 471.66 470.63 57.85

 HUB 50.71 37.84 12.87 283.08 365.85 5.94 471.66 470.63 57.85

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.18 207.17 246.73 1066.74 0.30 2.33 2.04 9.02

 MEAN 18.01 324.14 208.06 248.54 1065.03 0.30 2.40 2.13 7.35

 HUB 15.22 345.97 238.57 250.56 1063.34 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 380.05 301.26 172.87 0.28 4232.14 0.92 0.89

 MEAN 335.19 279.17 127.13 0.26 3748.66 0.92 0.89 0.89 1.61

 HUB 283.32 254.53 44.76 0.24 3632.90 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.69 1.09 6.28 488.53 1.03 480.24 479.26 44.17

 MEAN 6.62 1.08 6.22 487.09 1.02 478.70 478.51 46.68

 HUB 6.61 1.08 6.15 486.75 1.02 477.19 478.67 49.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.02 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 39.93 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.60 10.13 6.50 3.63 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 348.9034 208.6477 279.6422 1063.9092 0.3279 -0.1210 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6346 6.1652 477.7390 479.1632 48.6774 36.7275 30.6000 -6.1275

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 272.5067 57.7733 266.3121 1068.1151 0.2551 0.3000 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6315 6.3423 481.5292 478.1886 491.5697 0.0173 0.4060

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 282.0991 0.0000 282.0991 1067.6243 0.2642 0.3066 0.5911

NASA/TM—2013-218094 L–74
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3091 481.1052 478.6047 0.0000 0.0600 0.0492 0.2216

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8529 6.6180 1.0772 487.4575 11.5100 201.8451 1.5647

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72088.484 0.499 131.474 307097.844 0.256802E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.734 EfDer = 0.988 SH = 0.293266E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.273 2132.713 6.618 487.457 1.000 1.000 0.980

 W Kg/sec = 14.670 Wdry = 32.178 WH2O = 0.095 lbm/sec H2O = 1.680g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.493 2199.998 1.378 0.251 53.443 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54262.543 25293.826 2.677 545.479 203.781 424.468 2.083

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 238.74 -0.08 238.74 0.22 0.41 385.30

 MEAN 17.74 0.00 -0.02 238.74 -0.08 238.74 0.22 0.38

 HUB 15.05 0.00 -0.02 238.74 -0.08 238.74 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.42 46.36 11.06 373.53 443.38 6.40 482.91 479.18 48.87

 MEAN 54.13 43.40 10.73 330.14 407.48 6.40 482.91 479.18 48.87

 HUB 49.57 38.84 10.73 280.10 368.10 6.40 482.91 479.18 48.87

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 317.27 190.00 254.09 1078.03 0.29 2.26 1.98 8.75

 MEAN 17.51 321.18 194.42 255.65 1076.64 0.30 2.34 2.07 6.78

 HUB 14.85 345.04 229.81 257.38 1075.27 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 368.69 310.63 178.69 0.29 3765.56 0.92 0.90

 MEAN 325.82 287.44 131.40 0.27 3405.05 0.92 0.90 0.90 1.55

 HUB 276.38 261.56 46.57 0.24 3413.88 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.13 1.08 6.72 498.63 1.02 490.60 486.47 39.37

 MEAN 7.08 1.07 6.66 497.56 1.02 489.34 486.00 41.10

 HUB 7.08 1.07 6.60 497.59 1.02 488.10 486.40 42.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.79 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 37.25 27.20 23.50 3.70 0.94 0.44 1.62

 HUB 41.76 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 347.5592 195.6939 287.2304 1075.4583 0.3232 -0.1313 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0944 6.6067 488.3008 486.6943 42.9234 34.2671 31.5000 -2.7671

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 284.5536 62.0734 277.7006 1078.9407 0.2637 0.2303 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0929 6.7632 491.4736 485.8498 451.3937 0.0136 0.3707

 

NASA/TM—2013-218094 L–75
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 289.1237 0.0000 289.1237 1078.6975 0.2680 0.2776 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7421 491.2656 486.2375 0.0000 0.0600 0.0392 0.1819

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8717 7.0817 1.0701 497.9233 10.4674 211.1212 1.6366

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65704.789 0.483 119.831 307325.156 0.328582E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.709 EfDer = 0.997 SH = 0.375114E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.273 2132.713 7.082 497.922 1.000 1.000 0.980

 W Kg/sec = 14.670 Wdry = 32.152 WH2O = 0.121 lbm/sec H2O = 2.249g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.636 2176.754 1.377 0.251 53.470 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51835.949 25285.619 2.666 513.330 192.571 395.845 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 242.34 -0.08 242.34 0.22 0.40 365.85

 MEAN 16.97 0.00 -0.02 242.34 -0.08 242.34 0.22 0.37

 HUB 14.32 0.00 -0.02 242.34 -0.08 242.34 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.94 46.36 9.58 358.46 432.76 6.84 493.25 486.86 43.74

 MEAN 52.51 43.80 8.71 315.85 398.18 6.84 493.25 486.86 43.74

 HUB 47.73 37.84 9.89 266.52 360.28 6.84 493.25 486.86 43.74

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 308.19 170.14 256.97 1088.01 0.28 2.16 1.89 8.34

 MEAN 16.57 312.21 175.32 258.34 1086.81 0.29 2.24 1.97 6.35

 HUB 13.89 334.98 211.41 259.85 1085.63 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.38 314.46 181.24 0.29 3213.93 0.92 0.91

 MEAN 308.46 290.63 133.15 0.27 2907.09 0.92 0.91 0.91 1.49

 HUB 258.51 264.08 47.11 0.24 2937.64 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.54 1.07 7.14 507.43 1.02 499.88 492.83 36.95

 MEAN 7.50 1.06 7.09 506.52 1.02 498.78 492.47 38.29

 HUB 7.50 1.06 7.03 506.62 1.02 497.69 492.90 39.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.51 35.19 31.50 3.69 0.93 0.41 1.40

 MEAN 34.16 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 39.13 10.28 6.50 3.78 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 333.6907 176.3025 283.3141 1085.9364 0.3073 -0.1058 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.5103 7.0419 498.0107 493.0740 39.5779 31.8934 32.4000 0.5066

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 286.2094 64.1884 278.9188 1088.4767 0.2629 0.1785 2.2705

 

NASA/TM—2013-218094 L–76
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.5094 7.1627 500.3495 492.4425 432.2457 0.0121 0.3399

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 283.8207 0.0000 283.8207 1088.5833 0.2607 0.2486 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1583 500.4585 492.7473 0.0000 0.0600 0.0367 0.1683

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8785 7.4989 1.0589 506.8568 8.9351 231.8862 1.7976

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 56237.313 0.455 102.565 316501.688 0.417924E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.860 EfDer = 1.000 SH = 0.474877E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.273 2132.713 7.499 506.856 1.000 1.000 0.980

 W Kg/sec = 14.670 Wdry = 32.120 WH2O = 0.153 lbm/sec H2O = 2.967g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.538 2157.486 1.375 0.252 53.502 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49758.523 25275.584 2.776 509.668 183.595 384.739 2.096

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 234.30 -0.08 234.30 0.21 0.38 344.91

 MEAN 15.91 0.00 -0.02 234.30 -0.08 234.30 0.21 0.35

 HUB 13.07 0.00 -0.02 234.30 -0.08 234.30 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.51 47.36 8.15 340.96 413.77 7.27 502.50 493.41 40.90

 MEAN 51.66 44.80 6.86 296.16 377.70 7.27 502.50 493.41 40.90

 HUB 46.08 38.84 7.24 243.25 337.80 7.27 502.50 493.41 40.90

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.24 156.99 248.86 1096.97 0.27 2.05 1.78 7.43

 MEAN 15.50 296.24 158.60 250.21 1095.72 0.27 2.13 1.86 5.75

 HUB 12.59 314.44 188.51 251.67 1094.50 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 333.89 305.32 176.89 0.28 2817.96 0.92 0.91

 MEAN 288.43 281.89 129.84 0.26 2459.14 0.92 0.91 0.91 1.47

 HUB 234.32 255.80 45.81 0.23 2374.33 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.92 1.06 7.54 515.17 1.02 508.31 498.49 35.68

 MEAN 7.87 1.05 7.48 514.11 1.01 507.15 498.06 36.97

 HUB 7.85 1.05 7.42 513.86 1.01 506.02 498.25 38.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.25 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.37 27.43 23.50 3.93 0.93 0.38 1.64

 HUB 36.83 10.32 6.50 3.82 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 327.3796 161.5040 284.7699 1094.3137 0.2992 -0.1937 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8710 7.4050 505.8898 498.7950 38.7290 29.5592 33.0000 3.4408

 

NASA/TM—2013-218094 L–77
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 292.6356 66.8236 284.9039 1096.1503 0.2670 0.0334 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8686 7.4946 507.5953 498.3036 410.5396 0.0261 0.3089

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 284.6649 0.0000 284.6649 1096.5254 0.2596 0.2230 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5090 507.9527 498.4632 0.0000 0.0600 0.0407 0.0695

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8769 7.8628 1.0485 514.3688 7.5236 257.8513 1.9988

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47502.938 0.426 86.635 333811.438 0.520546E-02

 

Melt Ratio at Stator LE, Throat, TE

0.14900E-01 0.25139E-01 0.77776E-01

 trTOT = 1.1148 Tt4 = 514.3688 T1 = 461.4056

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 332325.81 606.0900 80.0108 1.4060 0.8519 14.1782 1.1148 37.3740

NASA/TM—2013-218094 L–78
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.307 EfDer = 0.994 SH = 0.133955E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.803 1960.632 6.513 472.317 1.000 1.000 0.980

 W Kg/sec = 18.547 Wdry = 40.748 WH2O = 0.055 lbm/sec H2O = 0.786g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.879 2054.629 1.380 0.249 53.392 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66937.508 31998.811 3.230 831.557 257.446 619.754 2.407

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 193.19 -0.07 193.19 0.18 0.38 369.89

 MEAN 17.06 0.00 -0.02 193.19 -0.07 193.19 0.18 0.33

 HUB 12.51 0.00 -0.02 193.19 -0.07 193.19 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.31 50.47 10.84 352.97 402.44 6.36 469.33 465.58 40.06

 MEAN 56.51 47.20 9.31 291.89 350.09 6.36 469.33 465.58 40.06

 HUB 47.94 38.62 9.32 214.04 288.38 6.36 469.33 465.58 40.06

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 338.06 210.99 264.14 1061.14 0.32 7.29 6.52 16.04

 MEAN 18.04 350.58 228.37 265.99 1059.65 0.33 7.43 6.80 12.53

 HUB 15.00 391.01 283.70 269.08 1057.38 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 352.97 299.89 141.99 0.28 4354.02 0.92 0.91

 MEAN 308.59 277.82 80.22 0.26 4120.05 0.92 0.91 0.91 1.42

 HUB 256.65 270.44 27.05 0.26 4256.29 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.60 484.25 1.03 475.10 475.59 40.97

 MEAN 7.04 1.08 6.54 483.61 1.02 473.76 475.37 43.00

 HUB 7.06 1.08 6.43 483.98 1.02 471.74 476.20 46.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.62 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.65 16.78 12.70 4.08 0.93 0.36 2.22

 HUB 46.51 -5.74 -9.30 3.56 0.93 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.3434 227.9281 285.5251 1059.0339 0.3450 -0.0592 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0537 6.5038 473.2683 475.9644 45.0072 38.5996 35.4000 -3.1996

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 288.2955 70.5259 279.5360 1063.5182 0.2711 0.3398 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0511 6.7050 477.2980 475.2170 554.9116 0.0148 0.4397

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 286.2093 0.0000 286.2093 1063.6001 0.2691 0.3514 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6971 477.3951 475.8236 0.0000 0.0600 0.0401 0.3251

NASA/TM—2013-218094 L–79
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8736 7.0375 1.0805 483.9465 11.6310 199.8359 1.5491

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72690.945 0.583 167.610 418423.125 0.200155E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.483 EfDer = 0.999 SH = 0.260535E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.803 1960.632 7.038 483.945 1.000 1.000 0.980

 W Kg/sec = 18.547 Wdry = 40.696 WH2O = 0.106 lbm/sec H2O = 1.591g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.324 2029.810 1.378 0.250 53.433 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64372.004 31982.828 2.447 590.487 241.353 468.502 1.941

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 261.63 -0.09 261.63 0.25 0.41 364.00

 MEAN 18.08 0.00 -0.02 261.63 -0.09 261.63 0.25 0.38

 HUB 15.21 0.00 -0.02 261.63 -0.09 261.63 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.35 46.36 6.99 351.61 438.33 6.75 478.48 477.54 55.32

 MEAN 49.78 42.30 7.48 309.31 405.19 6.75 478.48 477.54 55.32

 HUB 44.86 37.84 7.02 260.24 369.08 6.75 478.48 477.54 55.32

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 320.03 151.84 281.72 1071.08 0.30 2.33 2.04 9.02

 MEAN 18.01 326.58 163.28 282.84 1070.22 0.31 2.40 2.13 7.35

 HUB 15.22 353.03 209.52 284.13 1069.38 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.38 344.07 197.54 0.32 3102.42 0.92 0.91

 MEAN 308.15 317.78 144.86 0.30 2942.34 0.92 0.91 0.91 1.38

 HUB 260.46 288.66 50.94 0.27 3190.90 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.46 1.06 7.02 492.42 1.02 484.24 483.35 46.89

 MEAN 7.43 1.06 6.98 491.98 1.02 483.47 483.22 48.17

 HUB 7.47 1.06 6.93 492.66 1.02 482.71 484.02 49.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.32 35.04 31.50 3.54 0.93 0.34 1.40

 MEAN 30.00 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.41 10.16 6.50 3.66 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 358.4814 163.7406 318.9011 1068.6694 0.3354 -0.1628 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4488 6.8987 482.1011 484.0263 50.8663 27.1784 30.6000 3.4216

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 313.0713 66.3733 305.9546 1071.3605 0.2922 0.1025 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4466 7.0244 484.5334 483.3547 491.5697 0.0146 0.2594

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 324.2202 0.0000 324.2202 1070.7222 0.3028 0.1529 0.5911

NASA/TM—2013-218094 L–80
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9828 483.9676 483.7681 0.0000 0.0600 0.0406 0.0156

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8720 7.4341 1.0564 492.3499 8.4049 249.4256 1.9335

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 52698.277 0.432 121.511 385825.906 0.284415E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.589 EfDer = 0.995 SH = 0.313946E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.803 1960.632 7.434 492.349 1.000 1.000 0.980

 W Kg/sec = 18.547 Wdry = 40.674 WH2O = 0.128 lbm/sec H2O = 1.985g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.605 2012.414 1.377 0.251 53.450 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62155.180 31976.066 2.366 545.479 230.537 424.468 1.841

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 273.46 -0.09 273.46 0.25 0.41 352.45

 MEAN 17.74 0.00 -0.02 273.46 -0.09 273.46 0.25 0.38

 HUB 15.05 0.00 -0.02 273.46 -0.09 273.46 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.48 46.36 5.12 343.39 439.05 7.11 486.39 483.92 50.31

 MEAN 47.99 43.40 4.59 303.50 408.60 7.11 486.39 483.92 50.31

 HUB 43.29 38.84 4.45 257.50 375.68 7.11 486.39 483.92 50.31

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.56 130.87 294.82 1078.55 0.30 2.26 1.98 8.75

 MEAN 17.51 330.02 146.91 295.52 1078.06 0.31 2.34 2.07 6.78

 HUB 14.85 357.42 199.73 296.40 1077.60 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 338.94 360.85 208.07 0.33 2594.50 0.92 0.91 

 MEAN 299.53 332.60 152.62 0.31 2573.60 0.92 0.91 0.91 1.32

 HUB 254.08 301.35 54.35 0.28 2967.41 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.80 1.05 7.33 499.42 1.01 491.13 488.66 44.47

 MEAN 7.79 1.05 7.31 499.36 1.01 490.69 488.76 45.13

 HUB 7.85 1.06 7.28 500.44 1.02 490.26 489.77 45.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.94 35.21 31.50 3.71 0.93 0.28 1.40

 MEAN 26.43 27.31 23.50 3.81 0.92 0.30 1.62

 HUB 33.97 10.39 6.50 3.89 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 364.2469 147.8764 332.8790 1076.3717 0.3384 -0.1755 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8069 7.2210 489.1771 489.6396 47.8174 23.9524 31.5000 7.5476

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 332.4394 72.5194 324.4331 1078.3101 0.3083 0.0075 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8018 7.3118 490.9417 489.1336 451.3937 0.0201 0.2175

 

NASA/TM—2013-218094 L–81
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 338.1968 0.0000 338.1968 1077.9635 0.3137 0.0981 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2785 490.6353 489.4637 0.0000 0.0600 0.0554 -0.0586

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8441 7.7840 1.0471 499.7396 7.3907 269.5492 2.0895

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46422.258 0.404 107.040 388576.219 0.341364E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 2.021 EfDer = 0.976 SH = 0.375041E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.803 1960.632 7.784 499.739 1.000 1.000 0.980

 W Kg/sec = 18.547 Wdry = 40.649 WH2O = 0.153 lbm/sec H2O = 2.441g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.633 1997.479 1.376 0.251 53.470 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60371.988 31968.314 2.313 513.330 221.906 395.845 1.784

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 282.25 -0.10 282.25 0.26 0.40 335.72

 MEAN 16.97 0.00 -0.02 282.25 -0.10 282.25 0.26 0.37

 HUB 14.32 0.00 -0.02 282.25 -0.10 282.25 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.43 46.36 3.07 329.53 433.96 7.43 493.41 489.49 47.20

 MEAN 45.82 43.80 2.02 290.36 405.01 7.43 493.41 489.49 47.20

 HUB 40.97 37.84 3.13 245.01 373.82 7.43 493.41 489.49 47.20

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 322.13 107.73 303.58 1084.89 0.30 2.16 1.89 8.34

 MEAN 16.57 328.96 125.77 303.97 1084.65 0.30 2.24 1.97 6.35

 HUB 13.89 354.50 181.39 304.57 1084.43 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 323.03 372.18 215.30 0.34 2035.77 0.92 0.89

 MEAN 283.57 342.49 157.81 0.32 2086.13 0.92 0.89 0.89 1.27

 HUB 237.65 309.73 56.26 0.29 2520.91 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.07 1.04 7.60 505.28 1.01 497.03 493.19 43.39

 MEAN 8.08 1.04 7.59 505.41 1.01 496.81 493.37 43.69

 HUB 8.14 1.05 7.57 506.60 1.01 496.61 494.40 43.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.54 35.34 31.50 3.84 0.93 0.23 1.40

 MEAN 22.48 27.44 23.50 3.94 0.91 0.25 1.62

 HUB 30.78 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 357.2826 126.4764 334.1475 1083.3203 0.3298 -0.1432 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0898 7.5121 495.6189 494.1432 45.7228 20.7319 32.4000 11.6681

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 340.4245 76.3473 331.7528 1084.3392 0.3139 -0.0547 2.2705

 

NASA/TM—2013-218094 L–82
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0807 7.5555 496.5542 493.8870 432.2457 0.0278 0.1811

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 338.1694 0.0000 338.1694 1084.4659 0.3118 0.0448 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5380 496.6766 494.0530 0.0000 0.0600 0.0786 -0.0891

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7788 8.0547 1.0348 505.7616 6.0231 309.2666 2.3974

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37905.641 0.363 87.402 402608.031 0.405254E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.361 EfDer = 0.944 SH = 0.443486E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.803 1960.632 8.055 505.761 1.000 1.000 0.980

 W Kg/sec = 18.547 Wdry = 40.622 WH2O = 0.181 lbm/sec H2O = 2.955g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.531 1985.552 1.376 0.252 53.492 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 58984.168 31959.619 2.361 509.668 215.829 384.739 1.783

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 277.74 -0.10 277.74 0.26 0.39 317.43

 MEAN 15.91 0.00 -0.02 277.74 -0.10 277.74 0.26 0.36

 HUB 13.07 0.00 -0.02 277.74 -0.10 277.74 0.26 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.46 47.36 1.10 313.45 418.87 7.70 499.64 494.00 45.24

 MEAN 44.44 44.80 -0.36 272.27 389.00 7.70 499.64 494.00 45.24

 HUB 38.85 38.84 0.01 223.62 356.64 7.70 499.64 494.00 45.24

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 313.39 92.51 299.42 1090.70 0.29 2.05 1.78 7.43

 MEAN 15.50 318.70 108.17 299.79 1090.46 0.29 2.13 1.86 5.75

 HUB 12.59 340.08 159.43 300.40 1090.22 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 306.95 368.29 214.44 0.34 1661.37 0.92 0.86

 MEAN 265.16 338.41 156.99 0.31 1677.85 0.92 0.86 0.86 1.24

 HUB 215.41 305.57 55.98 0.28 2008.46 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.28 1.03 7.83 510.27 1.01 502.48 497.04 42.69

 MEAN 8.29 1.03 7.82 510.31 1.01 502.26 497.15 42.98

 HUB 8.33 1.03 7.80 511.21 1.01 502.04 497.95 43.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 17.17 35.61 31.50 4.11 0.93 0.20 1.40

 MEAN 19.84 27.64 23.50 4.14 0.90 0.21 1.64

 HUB 27.96 10.56 6.50 4.06 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.944 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 359.7658 110.1503 342.4885 1088.3433 0.3306 -0.2475 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2915 7.6971 500.3371 498.1535 45.9343 17.8287 33.0000 15.1713

 

NASA/TM—2013-218094 L–83
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 355.6500 81.2130 346.2533 1088.5957 0.3267 -0.2644 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2662 7.6868 500.5716 498.0955 410.5396 0.0721 0.1490

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 345.9942 0.0000 345.9942 1089.1759 0.3177 0.0109 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7036 501.1093 498.1128 0.0000 0.0600 0.1017 -0.2299

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6917 8.2518 1.0245 510.5993 4.8385 359.6746 2.7882

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30516.439 0.324 70.364 426646.594 0.475987E-02

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0811 Tt4 = 510.5993 T1 = 472.3171

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 240233.55 553.9273 87.8791 1.2670 0.8257 9.3073 1.0811 37.3740

NASA/TM—2013-218094 L–84
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.688 EfDer = 0.999 SH = 0.193758E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.585 1802.880 7.939 487.551 1.000 1.000 0.980

 W Kg/sec = 22.993 Wdry = 50.487 WH2O = 0.098 lbm/sec H2O = 1.341g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 90.806 1859.571 1.379 0.250 53.411 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70383.422 39661.488 3.125 831.557 266.132 619.754 2.329

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 203.14 -0.07 203.14 0.19 0.36 334.77

 MEAN 17.06 0.00 -0.02 203.14 -0.07 203.14 0.19 0.31

 HUB 12.51 0.00 -0.02 203.14 -0.07 203.14 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.96 50.47 7.49 324.57 382.96 7.75 484.25 478.08 36.96

 MEAN 52.89 47.20 5.69 268.41 336.67 7.75 484.25 478.08 36.96

 HUB 44.11 38.62 5.49 196.82 282.90 7.75 484.25 478.08 36.96

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.90 173.50 280.59 1075.13 0.31 7.29 6.52 16.04

 MEAN 18.04 344.71 198.52 281.80 1074.25 0.32 7.43 6.80 12.53

 HUB 15.00 388.30 264.36 284.41 1072.50 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.57 318.67 151.07 0.30 3580.85 0.92 0.91 

 MEAN 283.76 294.41 85.24 0.27 3581.72 0.92 0.91 0.91 1.28

 HUB 236.00 285.82 28.36 0.27 3966.25 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.44 1.06 7.91 496.56 1.02 487.86 485.92 40.12

 MEAN 8.44 1.06 7.87 496.56 1.02 487.06 486.13 41.21

 HUB 8.49 1.07 7.77 497.53 1.02 485.47 487.37 43.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.73 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 35.16 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.91 -5.69 -9.30 3.61 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.7742 198.1355 302.6928 1073.4830 0.3370 -0.0735 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4504 7.8207 486.4337 486.7867 43.2274 33.2078 35.4000 2.1922

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.6534 75.2614 298.3058 1076.6567 0.2857 0.2315 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4481 7.9893 489.3265 486.2127 554.9116 0.0138 0.3518

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 305.3557 0.0000 305.3557 1076.7620 0.2836 0.2561 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9819 489.4404 486.8054 0.0000 0.0600 0.0383 0.2195

NASA/TM—2013-218094 L–85
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8721 8.4332 1.0622 496.8796 9.3297 221.9092 1.7202

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58448.453 0.555 167.082 507242.969 0.273325E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.267 EfDer = 0.988 SH = 0.343295E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.585 1802.880 8.433 496.878 1.000 1.000 0.980

 W Kg/sec = 22.993 Wdry = 50.412 WH2O = 0.174 lbm/sec H2O = 2.437g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.301 1842.041 1.377 0.251 53.460 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68635.156 39638.027 2.333 590.487 253.152 468.502 1.851

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.95 -0.10 278.95 0.26 0.40 330.33

 MEAN 18.08 0.00 -0.02 278.95 -0.10 278.95 0.26 0.37

 HUB 15.21 0.00 -0.02 278.95 -0.10 278.95 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.22 46.36 2.86 323.32 427.09 8.06 490.69 488.51 52.27

 MEAN 45.57 42.30 3.27 284.43 398.45 8.06 490.69 488.51 52.27

 HUB 40.64 37.84 2.80 239.30 367.59 8.06 490.69 488.51 52.27

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.35 107.50 303.90 1081.74 0.30 2.33 2.04 9.02

 MEAN 18.01 329.59 126.85 304.20 1081.57 0.30 2.40 2.13 7.35

 HUB 15.22 356.08 184.25 304.71 1081.41 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.27 371.56 213.77 0.34 2197.06 0.92 0.90

 MEAN 283.35 342.09 156.50 0.32 2286.31 0.92 0.90 0.90 1.25

 HUB 239.50 309.68 55.25 0.29 2806.32 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.75 1.04 8.23 502.38 1.01 494.11 492.34 48.17

 MEAN 8.76 1.04 8.22 502.60 1.01 493.96 492.58 48.41

 HUB 8.83 1.05 8.20 503.90 1.01 493.82 493.71 48.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.48 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.64 27.22 23.50 3.72 0.92 0.24 1.63

 HUB 31.16 10.28 6.50 3.78 0.92 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.3010 127.2067 343.5038 1079.7161 0.3393 -0.1934 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7736 8.1122 492.2903 493.5315 51.4627 20.3206 30.6000 10.2794

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 339.1938 71.9115 331.4832 1081.3824 0.3137 -0.0404 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7649 8.1960 493.8117 493.0635 491.5697 0.0255 0.1638

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 351.9251 0.0000 351.9251 1080.6091 0.3257 0.0276 0.5911

NASA/TM—2013-218094 L–86
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1304 493.1129 493.5090 0.0000 0.0600 0.0701 -0.1575

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8020 8.7399 1.0364 502.9617 6.0832 301.1798 2.3347

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38247.953 0.371 109.336 470686.906 0.369099E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.091 EfDer = 0.949 SH = 0.399296E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.585 1802.880 8.740 502.961 1.000 1.000 0.980

 W Kg/sec = 22.993 Wdry = 50.383 WH2O = 0.202 lbm/sec H2O = 2.890g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.781 1830.870 1.376 0.251 53.478 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67316.453 39629.215 2.219 545.479 245.852 424.468 1.727 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 296.17 -0.10 296.17 0.27 0.40 320.66

 MEAN 17.74 0.00 -0.02 296.17 -0.10 296.17 0.27 0.38

 HUB 15.05 0.00 -0.02 296.17 -0.10 296.17 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.84 46.36 0.48 315.76 433.00 8.31 495.99 493.35 50.67

 MEAN 43.31 43.40 -0.09 279.08 407.01 8.31 495.99 493.35 50.67

 HUB 38.65 38.84 -0.19 236.78 379.25 8.31 495.99 493.35 50.67

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.87 82.33 323.56 1086.09 0.31 2.26 1.98 8.75

 MEAN 17.51 340.70 107.49 323.30 1086.37 0.31 2.34 2.07 6.78

 HUB 14.85 366.96 173.45 323.38 1086.65 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 311.67 396.60 229.34 0.37 1632.96 0.92 0.87

 MEAN 275.43 364.32 167.95 0.34 1883.50 0.92 0.87 0.87 1.19

 HUB 233.64 328.94 60.18 0.30 2577.29 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.97 1.03 8.41 507.04 1.01 498.19 496.30 48.55

 MEAN 9.00 1.03 8.42 507.67 1.01 498.45 496.73 48.12

 HUB 9.10 1.04 8.42 509.40 1.01 498.71 498.06 47.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.28 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.39 27.45 23.50 3.95 0.90 0.19 1.62

 HUB 28.21 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.949 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.6712 108.1903 364.9731 1084.2577 0.3511 -0.2080 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0173 8.2922 496.5322 497.8180 51.4721 16.5116 31.5000 14.9884

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 366.8205 80.0194 357.9863 1085.1552 0.3380 -0.1459 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0004 8.3269 497.3549 497.5509 451.3937 0.0378 0.1194

 

NASA/TM—2013-218094 L–87
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 374.1470 0.0000 374.1470 1084.6801 0.3449 -0.0369 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2654 496.9249 497.8715 0.0000 0.0600 0.1005 -0.2472

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6824 8.9623 1.0254 508.0374 5.0764 341.1821 2.6448

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31973.135 0.329 91.399 476627.844 0.425585E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.160 EfDer = 0.891 SH = 0.456299E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.585 1802.880 8.962 508.036 1.000 1.000 0.980

 W Kg/sec = 22.993 Wdry = 50.354 WH2O = 0.231 lbm/sec H2O = 3.340g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.113 1821.701 1.375 0.252 53.496 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66562.656 39620.227 2.130 513.330 241.043 395.845 1.642

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 311.20 -0.11 311.20 0.29 0.40 306.17

 MEAN 16.97 0.00 -0.02 311.20 -0.11 311.20 0.29 0.38

 HUB 14.32 0.00 -0.02 311.20 -0.11 311.20 0.29 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.25 46.36 -2.11 303.02 434.43 8.48 500.36 497.40 49.80

 MEAN 40.64 43.80 -3.16 267.00 410.11 8.48 500.36 497.40 49.80

 HUB 35.92 37.84 -1.92 225.30 384.25 8.48 500.36 497.40 49.80

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 343.81 55.13 339.36 1089.34 0.32 2.16 1.89 8.34

 MEAN 16.57 348.89 83.77 338.69 1089.98 0.32 2.24 1.97 6.35

 HUB 13.89 372.28 154.92 338.52 1090.59 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 297.04 416.75 241.91 0.38 1042.95 0.92 0.81

 MEAN 260.76 382.15 176.99 0.35 1390.19 0.92 0.81 0.81 1.14

 HUB 218.53 344.44 63.61 0.32 2153.41 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.10 1.02 8.50 510.64 1.01 501.27 499.53 49.59

 MEAN 9.15 1.02 8.53 511.50 1.01 501.85 500.02 48.64

 HUB 9.25 1.03 8.54 513.41 1.01 502.42 501.35 47.66

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.23 35.48 31.50 3.98 0.93 0.09 1.40

 MEAN 13.89 27.59 23.50 4.09 0.89 0.13 1.62

 HUB 24.59 10.64 6.50 4.14 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.891 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.5934 84.2397 373.2042 1088.2128 0.3516 -0.1709 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1586 8.4205 500.2491 501.0012 51.4197 12.7196 32.4000 19.6804

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 382.7505 85.8398 373.0007 1088.2025 0.3517 -0.2008 2.2705

 

NASA/TM—2013-218094 L–88
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1337 8.3971 500.2406 501.0273 432.2457 0.0488 0.0830

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 381.2060 0.0000 381.2060 1088.3018 0.3503 -0.0883 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3553 500.3349 501.0995 0.0000 0.0600 0.1297 -0.2661

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4831 9.0821 1.0134 511.8507 3.8141 419.8521 3.2547

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 24064.551 0.273 68.791 496569.906 0.482393E-02

 

Melt Ratio at Stator LE, Throat, TE

0.85372E-03 0.85372E-03 0.85372E-03

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.014 EfDer = 0.828 SH = 0.511517E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.585 1802.880 9.082 511.848 1.000 1.000 0.980

 W Kg/sec = 22.993 Wdry = 50.327 WH2O = 0.259 lbm/sec H2O = 3.765g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.334 1814.902 1.375 0.252 53.514 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66188.477 39611.508 2.134 509.668 238.837 384.739 1.611

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 311.67 -0.11 311.67 0.29 0.39 290.14

 MEAN 15.91 0.00 -0.02 311.67 -0.11 311.67 0.29 0.37

 HUB 13.07 0.00 -0.02 311.67 -0.11 311.67 0.29 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.77 47.36 -4.59 288.23 424.59 8.59 504.16 500.33 48.89

 MEAN 38.79 44.80 -6.01 250.36 399.84 8.59 504.16 500.33 48.89

 HUB 33.43 38.84 -5.41 205.63 373.45 8.59 504.16 500.33 48.89

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 342.48 37.09 340.46 1092.46 0.31 2.05 1.78 7.43

 MEAN 15.50 345.87 64.61 339.78 1093.16 0.32 2.13 1.86 5.75

 HUB 12.59 365.04 133.74 339.66 1093.83 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.25 419.55 245.16 0.38 667.35 0.92 0.76

 MEAN 243.83 384.15 179.21 0.35 1003.09 0.92 0.76 0.76 1.11

 HUB 198.08 345.70 64.34 0.32 1685.13 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.16 1.01 8.57 513.51 1.00 504.22 501.88 49.54

 MEAN 9.21 1.01 8.60 514.34 1.00 504.87 502.30 48.48

 HUB 9.29 1.02 8.61 516.04 1.01 505.49 503.42 47.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.22 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.77 27.81 23.50 4.31 0.87 0.09 1.64

 HUB 21.49 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.828 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 395.2317 65.7998 389.7159 1090.3190 0.3625 -0.2833 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2075 8.4216 502.2646 503.6270 52.6636 9.5835 33.0000 23.4165

 

NASA/TM—2013-218094 L–89
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 408.3179 93.2397 397.5297 1089.4160 0.3748 -0.4413 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1498 8.3178 501.4315 503.9286 410.5396 0.1121 0.0557

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 397.0071 0.0000 397.0071 1090.1945 0.3642 -0.0992 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3436 502.1483 503.7329 0.0000 0.0600 0.1444 -0.4001

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2632 9.1297 1.0052 514.6199 2.7806 530.0331 4.1088

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17571.299 0.221 50.230 528644.188 0.530777E-02

 

Melt Ratio at Stator LE, Throat, TE

0.13813E+00 0.14733E+00 0.17387E+00

 trTOT = 1.0555 Tt4 = 514.6199 T1 = 487.5511

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 170305.39 486.8386 90.8058 1.1499 0.7008 5.6880 1.0555 37.3740

NASA/TM—2013-218094 L–90
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.821 EfDer = 1.000 SH = 0.280907E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.379 1594.205 9.337 500.810 1.000 1.000 0.980

 W Kg/sec = 22.445 Wdry = 49.240 WH2O = 0.139 lbm/sec H2O = 2.237g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.386 1622.427 1.378 0.251 53.439 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 59717.055 38702.273 3.712 831.557 224.000 619.754 2.767

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.35 -0.06 172.35 0.16 0.31 292.08

 MEAN 17.06 0.00 -0.02 172.35 -0.06 172.35 0.16 0.27

 HUB 12.51 0.00 -0.02 172.35 -0.06 172.35 0.16 0.23

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.02 50.47 8.55 287.01 334.83 9.18 498.44 488.84 35.77

 MEAN 54.02 47.20 6.82 237.34 293.37 9.18 498.44 488.84 35.77

 HUB 45.29 38.62 6.67 174.04 244.98 9.18 498.44 488.84 35.77

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 286.57 158.81 238.54 1089.90 0.26 7.29 6.52 16.04

 MEAN 18.04 298.72 178.68 239.39 1089.15 0.27 7.43 6.80 12.53

 HUB 15.00 335.13 232.82 241.05 1087.80 0.31 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 287.01 270.80 128.20 0.25 3277.48 0.92 0.91

 MEAN 250.92 250.05 72.24 0.23 3223.66 0.92 0.91 0.91 1.32

 HUB 208.68 242.26 24.14 0.22 3493.04 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.80 1.05 9.34 508.08 1.01 501.53 495.54 39.92

 MEAN 9.79 1.05 9.30 507.96 1.01 500.85 495.65 40.79

 HUB 9.83 1.05 9.21 508.56 1.02 499.60 496.51 42.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.65 28.25 24.20 4.05 0.93 0.32 1.80

 MEAN 36.74 16.79 12.70 4.09 0.93 0.29 2.22

 HUB 44.00 -5.72 -9.30 3.58 0.93 0.18 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 312.6525 178.3314 256.8064 1088.5790 0.2872 -0.0688 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.8000 9.2631 500.4215 496.2357 42.4927 34.7769 35.4000 0.6231

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 261.8520 64.0570 253.8960 1091.0848 0.2400 0.2601 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7994 9.4204 502.7439 495.8019 554.9116 0.0113 0.3728

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 259.8379 0.0000 259.8379 1091.1547 0.2381 0.2801 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4135 502.8279 496.5464 0.0000 0.0600 0.0367 0.2468

NASA/TM—2013-218094 L–91
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8759 9.7861 1.0481 508.1947 7.3873 214.7624 1.6648

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46442.723 0.564 129.596 482916.750 0.398062E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.79073E-02

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.304 EfDer = 0.994 SH = 0.479743E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.379 1594.205 9.786 508.181 1.000 1.000 0.980

 W Kg/sec = 22.445 Wdry = 49.142 WH2O = 0.237 lbm/sec H2O = 3.898g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.418 1610.599 1.375 0.252 53.504 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58530.781 38671.719 2.739 590.487 215.547 468.502 2.174

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 237.88 -0.08 237.88 0.22 0.34 288.82

 MEAN 18.08 0.00 -0.02 237.88 -0.08 237.88 0.22 0.32

 HUB 15.21 0.00 -0.02 237.88 -0.08 237.88 0.22 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.25 46.36 3.89 285.89 371.98 9.47 503.70 498.27 51.46

 MEAN 46.60 42.30 4.30 251.51 346.24 9.47 503.70 498.27 51.46

 HUB 41.66 37.84 3.82 211.60 318.43 9.47 503.70 498.27 51.46

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 278.94 101.63 259.76 1095.04 0.25 2.33 2.04 9.02

 MEAN 18.01 285.18 117.02 260.06 1094.82 0.26 2.40 2.13 7.35

 HUB 15.22 308.21 164.74 260.48 1094.60 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 284.08 317.44 182.46 0.29 2076.95 0.92 0.91

 MEAN 250.56 292.34 133.54 0.27 2108.99 0.92 0.91 0.91 1.28

 HUB 211.78 264.69 47.04 0.24 2509.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.08 1.03 9.65 512.75 1.01 506.58 501.27 47.87

 MEAN 10.09 1.03 9.63 512.82 1.01 506.38 501.40 48.17

 HUB 10.15 1.04 9.61 513.70 1.01 506.18 502.20 48.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 21.37 35.08 31.50 3.58 0.93 0.24 1.40

 MEAN 24.23 27.18 23.50 3.68 0.92 0.26 1.63

 HUB 32.31 10.24 6.50 3.74 0.92 0.30 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 315.3905 117.3477 292.7469 1093.5277 0.2884 -0.1832 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.1003 9.5431 505.2029 502.0889 50.0895 21.8434 30.6000 8.7566

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 289.4114 61.3573 282.8325 1094.8628 0.2643 -0.0096 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0960 9.6243 506.4384 501.6612 491.5697 0.0190 0.1836

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 299.5848 0.0000 299.5848 1094.3157 0.2738 0.0540 0.5911

NASA/TM—2013-218094 L–92
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5732 505.9365 501.9206 0.0000 0.0600 0.0615 -0.1168

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8343 10.0758 1.0296 513.0439 4.9079 287.9884 2.2325

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30988.785 0.384 86.473 447791.406 0.497943E-02

 

Melt Ratio at Stator LE, Throat, TE

0.33557E+00 0.38047E+00 0.50814E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.863 EfDer = 0.962 SH = 0.513942E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.379 1594.205 10.076 513.031 1.000 1.000 0.980

 W Kg/sec = 22.445 Wdry = 49.125 WH2O = 0.254 lbm/sec H2O = 4.246g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.647 1602.969 1.375 0.252 53.515 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57570.910 38666.441 2.593 545.479 210.400 424.468 2.017

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 253.30 -0.09 253.30 0.23 0.34 280.74

 MEAN 17.74 0.00 -0.02 253.30 -0.09 253.30 0.23 0.32

 HUB 15.05 0.00 -0.02 253.30 -0.09 253.30 0.23 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.80 46.36 1.44 279.22 377.05 9.71 507.95 501.55 48.12

 MEAN 44.26 43.40 0.86 246.78 353.70 9.71 507.95 501.55 48.12

 HUB 39.59 38.84 0.75 209.38 328.69 9.71 507.95 501.55 48.12

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 288.07 79.63 276.84 1098.58 0.26 2.26 1.98 8.75

 MEAN 17.51 294.32 100.03 276.79 1098.68 0.27 2.34 2.07 6.78

 HUB 14.85 317.52 155.32 276.93 1098.79 0.29 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 275.60 339.18 195.96 0.31 1579.32 0.92 0.88

 MEAN 243.55 311.79 143.52 0.28 1752.81 0.92 0.88 0.88 1.21

 HUB 206.59 281.64 51.27 0.26 2307.85 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.30 1.02 9.82 516.49 1.01 509.92 503.77 45.61

 MEAN 10.32 1.02 9.83 516.87 1.01 510.02 504.05 45.47

 HUB 10.40 1.03 9.83 518.09 1.01 510.12 505.01 45.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.05 35.29 31.50 3.79 0.93 0.18 1.40

 MEAN 19.87 27.41 23.50 3.91 0.91 0.21 1.62

 HUB 29.29 10.49 6.50 3.99 0.91 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.962 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 327.2227 100.6913 311.3454 1097.2194 0.2982 -0.1973 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3347 9.7268 508.6671 504.7848 47.4026 17.9216 31.5000 13.5784

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 312.8594 68.2482 305.3247 1097.9915 0.2849 -0.1149 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3249 9.7669 509.3824 504.5102 451.3937 0.0291 0.1377

 

NASA/TM—2013-218094 L–93
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 318.3843 0.0000 318.3843 1097.6531 0.2901 -0.0126 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7191 509.0706 504.6125 0.0000 0.0600 0.0911 -0.2079

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7367 10.2930 1.0216 517.0913 4.1210 325.4004 2.5225

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 26043.799 0.343 72.674 453904.594 0.522861E-02

 

Melt Ratio at Stator LE, Throat, TE

0.83019E+00 0.87322E+00 0.99345E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.229 EfDer = 0.910 SH = 0.548320E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.379 1594.205 10.293 517.082 1.000 1.000 0.980

 W Kg/sec = 22.445 Wdry = 49.108 WH2O = 0.271 lbm/sec H2O = 4.578g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.411 1596.683 1.374 0.253 53.526 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56959.262 38661.133 2.482 513.330 206.813 395.845 1.914

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 266.30 -0.09 266.30 0.24 0.34 268.35

 MEAN 16.97 0.00 -0.02 266.30 -0.09 266.30 0.24 0.32

 HUB 14.32 0.00 -0.02 266.30 -0.09 266.30 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 45.19 46.36 -1.17 267.95 377.84 9.89 511.48 504.30 45.84

 MEAN 41.57 43.80 -2.23 236.10 355.95 9.89 511.48 504.30 45.84

 HUB 36.81 37.84 -1.03 199.22 332.63 9.89 511.48 504.30 45.84

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 295.40 56.13 290.02 1101.32 0.27 2.16 1.89 8.34

 MEAN 16.57 300.40 79.41 289.72 1101.67 0.27 2.24 1.97 6.35

 HUB 13.89 321.35 139.09 289.69 1102.02 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 262.66 356.04 206.53 0.32 1061.55 0.92 0.83

 MEAN 230.58 326.78 151.16 0.30 1317.76 0.92 0.83 0.83 1.16

 HUB 193.24 294.70 54.15 0.27 1933.25 0.92 0.83

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.44 1.01 9.94 519.42 1.00 512.52 506.22 45.83

 MEAN 10.47 1.02 9.95 519.98 1.01 512.85 506.55 45.35

 HUB 10.55 1.03 9.96 521.33 1.01 513.17 507.51 44.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.95 35.46 31.50 3.96 0.93 0.11 1.40

 MEAN 15.33 27.55 23.50 4.05 0.89 0.15 1.62

 HUB 25.65 10.59 6.50 4.09 0.89 0.22 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.910 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 328.1433 79.8611 318.2769 1100.4451 0.2982 -0.1622 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4815 9.8653 511.7358 507.2787 47.1926 14.0857 32.4000 18.3143

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 325.7966 73.0667 317.4975 1100.5717 0.2960 -0.1676 2.2705

 

NASA/TM—2013-218094 L–94
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4659 9.8593 511.8582 507.2966 432.2457 0.0390 0.1003

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 324.0378 0.0000 324.0378 1100.6637 0.2944 -0.0677 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8237 511.9493 507.4561 0.0000 0.0600 0.1219 -0.2339

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5520 10.4213 1.0125 520.2436 3.1613 394.4397 3.0577

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 20007.506 0.290 55.830 473185.938 0.587221E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.086 EfDer = 0.848 SH = 0.633826E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.379 1594.205 10.421 520.242 1.000 1.000 0.980

 W Kg/sec = 22.445 Wdry = 49.066 WH2O = 0.313 lbm/sec H2O = 5.323g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.756 1591.839 1.373 0.253 53.554 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56625.770 38647.910 2.486 509.668 204.994 384.739 1.877

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 266.64 -0.09 266.64 0.24 0.33 254.48

 MEAN 15.91 0.00 -0.02 266.64 -0.09 266.64 0.24 0.31

 HUB 13.07 0.00 -0.02 266.64 -0.09 266.64 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.72 47.36 -3.64 254.87 368.92 10.01 514.64 507.42 47.78

 MEAN 39.71 44.80 -5.09 221.38 346.62 10.01 514.64 507.42 47.78

 HUB 34.31 38.84 -4.53 181.83 322.79 10.01 514.64 507.42 47.78

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 293.45 40.47 290.64 1103.90 0.27 2.05 1.78 7.43

 MEAN 15.50 297.01 62.62 290.33 1104.29 0.27 2.13 1.86 5.75

 HUB 12.59 314.27 120.32 290.33 1104.68 0.28 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 249.58 358.05 209.12 0.32 727.66 0.92 0.78

 MEAN 215.60 328.17 152.98 0.30 971.99 0.92 0.78 0.78 1.13

 HUB 175.15 295.46 54.83 0.27 1516.06 0.92 0.78

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.51 1.01 10.02 521.84 1.00 515.05 508.95 48.51

 MEAN 10.54 1.01 10.04 522.37 1.00 515.42 509.23 47.95

 HUB 10.61 1.02 10.04 523.57 1.01 515.78 510.05 47.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.93 35.73 31.50 4.23 0.93 0.07 1.40

 MEAN 12.17 27.79 23.50 4.29 0.88 0.11 1.64

 HUB 22.51 10.69 6.50 4.19 0.88 0.18 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.848 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 337.4588 63.7726 331.3781 1102.3337 0.3061 -0.2707 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5461 9.8945 513.6191 510.2328 50.8154 10.8932 33.0000 22.1068

 

NASA/TM—2013-218094 L–95
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 345.5078 78.8970 336.3791 1101.8665 0.3136 -0.3897 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.5082 9.8285 513.1874 510.4366 410.5396 0.0922 0.0713

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 336.4613 0.0000 336.4613 1102.3848 0.3052 -0.0852 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8390 513.6743 510.4241 0.0000 0.0600 0.1406 -0.3696

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3540 10.4829 1.0059 522.5940 2.3514 490.0721 3.7990

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14920.457 0.240 41.635 504413.031 0.672240E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0435 Tt4 = 522.5940 T1 = 500.8095

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 138403.27 386.2069 76.3865 1.1227 0.7362 6.8205 1.0435 37.3740

NASA/TM—2013-218094 L–96
5μm, 2g/m3

, ISA +27R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.527 EfDer = 0.954 SH = 0.893968E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.270 2448.484 4.265 467.823 1.000 1.000 0.980

 W Kg/sec = 11.941 Wdry = 26.247 WH2O = 0.023 lbm/sec H2O = 0.347g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.998 2578.165 1.380 0.249 53.377 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65126.258 20605.740 3.302 831.557 251.855 619.754 2.461

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 187.96 -0.06 187.96 0.18 0.46 464.14

 MEAN 17.06 0.00 -0.02 187.96 -0.06 187.96 0.18 0.39

 HUB 12.51 0.00 -0.02 187.96 -0.06 187.96 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.91 50.47 16.44 440.80 479.26 4.17 464.99 457.60 21.33

 MEAN 62.73 47.20 15.53 364.53 410.19 4.17 464.99 457.60 21.33

 HUB 54.89 38.62 16.27 267.30 326.83 4.17 464.99 457.60 21.33

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 394.91 304.50 251.46 1063.24 0.37 7.29 6.52 16.04

 MEAN 18.04 399.47 307.65 254.81 1060.11 0.38 7.43 6.80 12.53

 HUB 15.00 432.44 345.98 259.43 1056.27 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 440.80 286.03 136.30 0.27 6283.23 0.92 0.87

 MEAN 385.38 266.40 77.73 0.25 5549.92 0.92 0.87 0.87 1.77

 HUB 320.51 260.68 25.47 0.25 5190.52 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.92 1.15 4.48 489.37 1.05 476.85 472.91 19.78

 MEAN 4.84 1.13 4.39 486.85 1.04 474.05 471.64 21.92

 HUB 4.80 1.13 4.28 485.62 1.04 470.62 471.40 24.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.45 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.37 16.96 12.70 4.26 0.95 0.52 2.22

 HUB 53.14 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 411.0974 307.0542 273.3474 1059.6848 0.3879 -0.0357 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8491 4.3773 473.7371 472.2051 23.1020 48.3237 35.4000 -12.9237

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 271.1691 66.3362 262.9300 1068.1866 0.2539 0.5172 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8370 4.6278 481.3876 471.1437 554.9116 0.0361 0.6100

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 270.0914 0.0000 270.0914 1068.2029 0.2528 0.4864 1.3089

NASA/TM—2013-218094 L–97
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6068 481.4362 471.9162 0.0000 0.0600 0.0867 0.4723

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8137 4.8132 1.1287 487.2784 19.4569 167.5380 1.2987

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 121419.047 0.625 180.254 271081.844 0.172862E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.095 EfDer = 0.958 SH = 0.267395E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.270 2448.484 4.813 487.278 1.000 1.000 0.980

 W Kg/sec = 11.941 Wdry = 26.200 WH2O = 0.070 lbm/sec H2O = 1.113g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.764 2526.195 1.378 0.250 53.435 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60808.711 20591.279 2.590 590.487 227.980 468.502 2.055

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 247.14 -0.09 247.14 0.23 0.47 453.02

 MEAN 18.08 0.00 -0.02 247.14 -0.09 247.14 0.23 0.43

 HUB 15.21 0.00 -0.02 247.14 -0.09 247.14 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.63 46.36 14.27 439.09 503.94 4.64 482.40 474.38 33.02

 MEAN 57.40 42.30 15.10 386.28 458.64 4.64 482.40 474.38 33.02

 HUB 52.76 37.84 14.92 324.99 408.35 4.64 482.40 474.38 33.02

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 363.22 253.54 260.09 1082.30 0.34 2.33 2.04 9.02

 MEAN 18.01 362.69 250.01 262.75 1079.81 0.34 2.40 2.13 7.35

 HUB 15.22 384.22 277.54 265.70 1077.36 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 436.32 317.89 182.78 0.29 5179.03 0.92 0.88 

 MEAN 384.82 295.31 134.81 0.27 4504.27 0.92 0.88 0.88 1.71

 HUB 325.27 269.96 47.73 0.25 4226.23 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.12 5.00 504.94 1.04 494.41 484.69 23.11

 MEAN 5.32 1.10 4.92 502.64 1.03 492.14 483.65 24.94

 HUB 5.28 1.10 4.85 501.69 1.03 489.91 483.56 26.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.27 35.10 31.50 3.60 0.93 0.55 1.40

 MEAN 43.58 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.25 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 387.7487 250.7154 295.7886 1078.6195 0.3595 -0.1064 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3270 4.8785 491.0978 484.3220 26.0627 40.2852 30.6000 -9.6852

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 286.0433 60.6432 279.5410 1084.5966 0.2637 0.3713 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3206 5.0733 496.5626 483.0670 491.5697 0.0257 0.4672

 

NASA/TM—2013-218094 L–98
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.5269 0.0000 296.5269 1084.0463 0.2735 0.3583 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0392 496.0768 483.5197 0.0000 0.0600 0.0666 0.2883

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8309 5.3038 1.1019 503.0863 15.8092 188.4658 1.4610

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 99139.648 0.521 147.179 246287.469 0.307941E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.113 EfDer = 0.973 SH = 0.365007E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.270 2448.484 5.304 503.086 1.000 1.000 0.980

 W Kg/sec = 11.941 Wdry = 26.174 WH2O = 0.096 lbm/sec H2O = 1.620g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.706 2486.189 1.377 0.251 53.467 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57004.727 20583.316 2.593 545.479 210.359 424.468 2.018

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.80 -0.09 250.80 0.23 0.46 435.43

 MEAN 17.74 0.00 -0.02 250.80 -0.09 250.80 0.23 0.42

 HUB 15.05 0.00 -0.02 250.80 -0.09 250.80 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.68 46.36 13.32 428.84 496.86 5.11 498.08 484.35 26.27

 MEAN 56.51 43.40 13.11 379.02 454.56 5.11 498.08 484.35 26.27

 HUB 52.06 38.84 13.22 321.57 407.88 5.11 498.08 484.35 26.27

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 354.95 237.39 263.88 1098.01 0.32 2.26 1.98 8.75

 MEAN 17.51 356.44 237.01 266.23 1095.89 0.33 2.34 2.07 6.78

 HUB 14.85 379.96 268.53 268.82 1093.80 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 423.28 322.78 185.89 0.29 4704.47 0.92 0.89 

 MEAN 374.06 299.44 137.05 0.27 4150.76 0.92 0.89 0.89 1.66

 HUB 317.30 273.21 48.77 0.25 3988.94 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.87 1.11 5.47 519.08 1.03 509.06 493.07 19.65

 MEAN 5.80 1.09 5.40 517.19 1.03 507.09 492.32 20.89

 HUB 5.78 1.09 5.33 516.64 1.03 505.16 492.48 22.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.97 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.68 27.24 23.50 3.74 0.94 0.50 1.62

 HUB 44.97 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 382.6859 238.5651 299.2243 1094.6611 0.3496 -0.1143 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8160 5.3520 505.9986 493.0124 21.8170 38.5646 31.5000 -7.0646

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 294.3151 64.2029 287.2270 1099.7843 0.2676 0.3208 2.3726

 

NASA/TM—2013-218094 L–99
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8119 5.5342 510.7542 491.8804 451.3937 0.0199 0.4421

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 299.3273 0.0000 299.3273 1099.5139 0.2722 0.3438 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5115 510.5193 492.3112 0.0000 0.0600 0.0532 0.2671

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8518 5.7979 1.0931 517.6379 14.5527 193.6946 1.5015

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91559.711 0.511 135.926 244832.781 0.419094E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.531 EfDer = 0.983 SH = 0.494463E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.270 2448.484 5.798 517.637 1.000 1.000 0.980

 W Kg/sec = 11.941 Wdry = 26.140 WH2O = 0.130 lbm/sec H2O = 2.332g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.538 2450.995 1.375 0.252 53.509 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53658.781 20572.715 2.628 513.330 195.353 395.845 2.026

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.86 -0.09 250.86 0.23 0.44 411.94

 MEAN 16.97 0.00 -0.02 250.86 -0.09 250.86 0.23 0.40

 HUB 14.32 0.00 -0.02 250.86 -0.09 250.86 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.64 46.36 12.28 411.53 482.03 5.60 512.65 493.23 22.40

 MEAN 55.33 43.80 11.53 362.61 441.00 5.60 512.65 493.23 22.40

 HUB 50.66 37.84 12.82 305.98 395.73 5.60 512.65 493.23 22.40

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 341.57 217.75 263.17 1111.99 0.31 2.16 1.89 8.34

 MEAN 16.57 343.01 217.44 265.28 1110.08 0.31 2.24 1.97 6.35

 HUB 13.89 365.07 248.32 267.60 1108.20 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 403.41 322.07 185.66 0.29 4112.76 0.92 0.90 

 MEAN 354.13 298.43 136.69 0.27 3605.32 0.92 0.90 0.90 1.62

 HUB 296.79 271.95 48.46 0.25 3450.47 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.33 1.09 5.93 531.56 1.03 522.32 500.42 17.75

 MEAN 6.26 1.08 5.87 529.84 1.02 520.52 499.79 18.70

 HUB 6.24 1.08 5.80 529.32 1.02 518.76 499.95 19.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.61 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.34 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.86 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.983 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 363.9555 218.6649 290.9455 1109.2032 0.3281 -0.0905 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2732 5.8300 519.7535 500.3719 19.3006 36.9273 32.4000 -4.5273

 

NASA/TM—2013-218094 L–100
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.0495 65.4982 284.6100 1113.1674 0.2624 0.2835 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2710 5.9828 523.4848 499.4377 432.2457 0.0153 0.4205

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.7361 0.0000 289.7361 1113.2506 0.2603 0.3304 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9764 523.5783 499.6871 0.0000 0.0600 0.0436 0.2679

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8672 6.2594 1.0796 530.2205 12.6031 208.6822 1.6177

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79621.367 0.489 118.203 250634.297 0.553035E-02

 

Melt Ratio at Stator LE, Throat, TE

0.60906E-01 0.10633E+00 0.27141E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.080 EfDer = 0.991 SH = 0.614518E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.270 2448.484 6.259 530.212 1.000 1.000 0.980

 W Kg/sec = 11.941 Wdry = 26.109 WH2O = 0.161 lbm/sec H2O = 3.061g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.377 2421.738 1.374 0.253 53.548 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50799.332 20562.848 2.781 509.668 183.273 384.739 2.099

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.20 -0.08 239.20 0.21 0.41 387.16

 MEAN 15.91 0.00 -0.02 239.20 -0.08 239.20 0.21 0.37

 HUB 13.07 0.00 -0.02 239.20 -0.08 239.20 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.58 47.36 11.22 391.44 458.81 6.07 525.70 500.14 18.94

 MEAN 54.88 44.80 10.08 340.01 415.79 6.07 525.70 500.14 18.94

 HUB 49.43 38.84 10.59 279.27 367.77 6.07 525.70 500.14 18.94

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 324.29 204.69 251.53 1124.45 0.29 2.05 1.78 7.43

 MEAN 15.50 322.82 199.75 253.60 1122.48 0.29 2.13 1.86 5.75

 HUB 12.59 339.11 222.63 255.80 1120.54 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.32 308.51 178.64 0.27 3673.63 0.92 0.91 

 MEAN 331.14 285.61 131.39 0.25 3096.98 0.92 0.91 0.91 1.61

 HUB 269.01 259.97 46.38 0.23 2804.01 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.08 6.39 542.59 1.02 534.29 506.05 15.31

 MEAN 6.68 1.07 6.31 540.64 1.02 532.42 505.34 16.11

 HUB 6.64 1.06 6.24 539.66 1.02 530.58 505.23 16.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.14 35.38 31.50 3.88 0.93 0.49 1.40

 MEAN 38.23 27.39 23.50 3.89 0.94 0.46 1.64

 HUB 41.03 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 353.0882 203.4145 288.6067 1121.0751 0.3150 -0.1697 2.0437

 

NASA/TM—2013-218094 L–101
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6856 6.2493 531.1183 505.9444 16.7542 35.1768 33.0000 -2.1768

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.8446 67.3280 287.0545 1124.1947 0.2623 0.1654 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6834 6.3760 534.0842 505.1514 410.5396 0.0258 0.3962

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.7743 0.0000 286.7743 1124.5500 0.2550 0.3196 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3887 534.4326 505.3169 0.0000 0.0600 0.0382 0.1988

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8801 6.6787 1.0670 540.9190 10.7517 228.1724 1.7688

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68151.406 0.464 101.175 262949.188 0.656970E-02

 

Melt Ratio at Stator LE, Throat, TE

0.79927E+00 0.88442E+00 0.10000E+01

 trTOT = 1.1562 Tt4 = 540.9190 T1 = 467.8228

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 459891.19 682.7354 85.9985 1.5661 0.8347 15.5266 1.1562 37.3740

NASA/TM—2013-218094 L–102
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.594 EfDer = 0.953 SH = 0.784275E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.344 2371.140 4.199 461.513 1.000 1.000 0.980

 W Kg/sec = 11.520 Wdry = 25.324 WH2O = 0.020 lbm/sec H2O = 0.304g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.686 2513.735 1.381 0.249 53.374 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62886.816 19880.031 3.393 831.557 245.064 619.754 2.529

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 181.50 -0.06 181.50 0.17 0.44 452.54

 MEAN 17.06 0.00 -0.02 181.50 -0.06 181.50 0.17 0.38

 HUB 12.51 0.00 -0.02 181.50 -0.06 181.50 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.97 50.47 16.50 426.88 463.92 4.11 458.87 453.31 24.51

 MEAN 62.79 47.20 15.59 353.01 396.99 4.11 458.87 453.31 24.51

 HUB 54.97 38.62 16.35 258.86 316.20 4.11 458.87 453.31 24.51

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 382.44 294.98 243.41 1055.60 0.36 7.29 6.52 16.04

 MEAN 18.04 386.76 298.05 246.47 1052.65 0.37 7.43 6.80 12.53

 HUB 15.00 418.44 335.03 250.71 1049.03 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.88 276.84 131.90 0.26 6086.76 0.92 0.87

 MEAN 373.20 257.67 75.15 0.24 5376.75 0.92 0.87 0.87 1.77

 HUB 310.38 251.91 24.64 0.24 5026.16 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.15 4.40 481.73 1.04 469.99 468.27 22.55

 MEAN 4.74 1.13 4.32 479.37 1.04 467.37 466.99 24.92

 HUB 4.70 1.12 4.22 478.21 1.04 464.15 466.70 28.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.47 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.41 16.96 12.70 4.26 0.95 0.52 2.22

 HUB 53.19 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.9608 297.4737 264.3524 1052.2552 0.3782 -0.0358 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7450 4.3047 467.0730 467.5161 26.1876 48.3738 35.4000 -12.9738

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.7549 64.2779 254.7715 1060.2738 0.2478 0.5175 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7340 4.5386 474.2364 466.5587 554.9116 0.0353 0.6097

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.6761 0.0000 261.6761 1060.2882 0.2468 0.4857 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5186 474.2833 467.2465 0.0000 0.0600 0.0871 0.4715

NASA/TM—2013-218094 L–103
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8132 4.7114 1.1219 479.7711 18.2589 167.2975 1.2969

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 113867.773 0.625 163.083 263989.781 0.146630E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.080 EfDer = 0.958 SH = 0.222852E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.344 2371.140 4.711 479.770 1.000 1.000 0.980

 W Kg/sec = 11.520 Wdry = 25.288 WH2O = 0.056 lbm/sec H2O = 0.923g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.051 2465.462 1.379 0.250 53.421 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58920.363 19868.721 2.649 590.487 222.898 468.502 2.102

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 239.47 -0.08 239.47 0.23 0.46 442.12

 MEAN 18.08 0.00 -0.02 239.47 -0.08 239.47 0.23 0.42

 HUB 15.21 0.00 -0.02 239.47 -0.08 239.47 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.62 46.36 14.26 425.22 488.09 4.55 475.19 469.42 36.77

 MEAN 57.38 42.30 15.08 374.08 444.23 4.55 475.19 469.42 36.77

 HUB 52.74 37.84 14.90 314.73 395.54 4.55 475.19 469.42 36.77

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 351.96 245.04 252.65 1073.62 0.33 2.33 2.04 9.02

 MEAN 18.01 351.49 241.81 255.10 1071.28 0.33 2.40 2.13 7.35

 HUB 15.22 372.37 268.68 257.82 1068.97 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 422.53 308.77 177.49 0.29 5005.41 0.92 0.88

 MEAN 372.66 286.70 130.85 0.27 4356.48 0.92 0.88 0.88 1.71

 HUB 315.00 261.95 46.31 0.25 4091.41 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.25 1.11 4.88 496.32 1.03 486.42 479.60 25.96

 MEAN 5.18 1.10 4.81 494.18 1.03 484.30 478.56 27.96

 HUB 5.15 1.09 4.74 493.30 1.03 482.22 478.44 30.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.12 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.47 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.18 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.7929 242.4889 287.0878 1070.1410 0.3512 -0.1068 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1891 4.7710 483.3212 479.1840 29.1968 40.1861 30.6000 -9.5861

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 278.0208 58.9424 271.7008 1075.7705 0.2584 0.3688 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1834 4.9516 488.4266 478.0636 491.5697 0.0249 0.4647

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 288.1395 0.0000 288.1395 1075.2465 0.2680 0.3559 0.5911

NASA/TM—2013-218094 L–104
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9198 487.9702 478.4709 0.0000 0.0600 0.0661 0.2855

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8313 5.1677 1.0969 494.5990 14.8292 188.7069 1.4628

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92851.977 0.520 132.984 240041.750 0.255595E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.014 EfDer = 0.974 SH = 0.301584E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.344 2371.140 5.168 494.599 1.000 1.000 0.980

 W Kg/sec = 11.520 Wdry = 25.268 WH2O = 0.076 lbm/sec H2O = 1.329g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.399 2428.224 1.378 0.251 53.446 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55412.246 19862.533 2.642 545.479 206.443 424.468 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.79 -0.08 243.79 0.23 0.45 425.28

 MEAN 17.74 0.00 -0.02 243.79 -0.08 243.79 0.23 0.41

 HUB 15.05 0.00 -0.02 243.79 -0.08 243.79 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.59 46.36 13.23 415.29 481.63 4.99 489.86 479.21 29.41

 MEAN 56.41 43.40 13.01 367.05 440.70 4.99 489.86 479.21 29.41

 HUB 51.95 38.84 13.11 311.42 395.56 4.99 489.86 479.21 29.41

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 344.22 228.87 257.10 1088.44 0.32 2.26 1.98 8.75

 MEAN 17.51 345.79 228.81 259.26 1086.45 0.32 2.34 2.07 6.78

 HUB 14.85 368.76 259.84 261.65 1084.49 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.91 314.44 181.04 0.29 4535.69 0.92 0.89

 MEAN 362.25 291.59 133.43 0.27 4007.21 0.92 0.89 0.89 1.66

 HUB 307.28 265.92 47.43 0.25 3859.94 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.69 1.10 5.32 509.56 1.03 500.11 487.79 22.16

 MEAN 5.63 1.09 5.25 507.82 1.03 498.29 487.05 23.52

 HUB 5.61 1.09 5.19 507.33 1.03 496.49 487.18 24.92

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.68 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.43 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.80 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.3608 230.3142 291.3146 1085.2775 0.3422 -0.1151 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6421 5.2096 497.2501 487.6970 24.5561 38.3300 31.5000 -6.8300

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.8960 62.5844 279.9866 1090.0924 0.2632 0.3156 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6385 5.3775 501.6788 486.6848 451.3937 0.0191 0.4375

 

NASA/TM—2013-218094 L–105
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.7315 0.0000 291.7315 1089.8352 0.2677 0.3397 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3565 501.4572 487.0739 0.0000 0.0600 0.0521 0.2620

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8530 5.6256 1.0886 508.2337 13.6357 194.4956 1.5077

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85610.570 0.510 122.613 238893.641 0.345288E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.352 EfDer = 0.984 SH = 0.405724E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.344 2371.140 5.626 508.233 1.000 1.000 0.980

 W Kg/sec = 11.520 Wdry = 25.241 WH2O = 0.103 lbm/sec H2O = 1.893g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.554 2395.430 1.376 0.251 53.480 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52310.883 19854.328 2.669 513.330 192.360 395.845 2.058

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.56 -0.08 244.56 0.22 0.43 402.60

 MEAN 16.97 0.00 -0.02 244.56 -0.08 244.56 0.22 0.39

 HUB 14.32 0.00 -0.02 244.56 -0.08 244.56 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.47 46.36 12.11 398.53 467.66 5.44 503.48 487.89 25.18

 MEAN 55.15 43.80 11.35 351.16 428.00 5.44 503.48 487.89 25.18

 HUB 50.47 37.84 12.63 296.31 384.26 5.44 503.48 487.89 25.18

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.54 209.36 257.08 1101.64 0.30 2.16 1.89 8.34

 MEAN 16.57 333.14 209.50 259.03 1099.85 0.30 2.24 1.97 6.35

 HUB 13.89 354.77 240.11 261.16 1098.09 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 390.67 314.58 181.31 0.29 3954.33 0.92 0.90

 MEAN 342.95 291.39 133.45 0.26 3473.61 0.92 0.90 0.90 1.61

 HUB 287.41 265.41 47.30 0.24 3336.36 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.11 1.09 5.75 521.23 1.03 512.50 494.97 20.13

 MEAN 6.05 1.08 5.69 519.65 1.02 510.84 494.35 21.17

 HUB 6.04 1.07 5.62 519.20 1.02 509.20 494.50 22.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.16 35.19 31.50 3.69 0.93 0.49 1.40

 MEAN 38.97 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.60 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 353.6414 210.6756 284.0388 1099.0132 0.3218 -0.0916 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0641 5.6510 510.1018 494.9006 21.8596 36.5649 32.4000 -4.1649

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 285.4078 64.0086 278.1375 1102.7273 0.2588 0.2763 2.2705

 

NASA/TM—2013-218094 L–106
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0623 5.7909 513.5637 494.0885 432.2457 0.0147 0.4141

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 283.1421 0.0000 283.1421 1102.8226 0.2567 0.3243 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7850 513.6672 494.4251 0.0000 0.0600 0.0425 0.2607

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8673 6.0516 1.0757 520.0286 11.7957 210.1396 1.6290

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74310.555 0.487 106.428 244795.203 0.461150E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.824 EfDer = 0.992 SH = 0.538575E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.344 2371.140 6.052 520.028 1.000 1.000 0.980

 W Kg/sec = 11.520 Wdry = 25.208 WH2O = 0.136 lbm/sec H2O = 2.647g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.642 2368.109 1.375 0.252 53.523 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49664.629 19843.820 2.815 509.668 181.028 384.739 2.125

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 233.85 -0.08 233.85 0.21 0.40 378.58

 MEAN 15.91 0.00 -0.02 233.85 -0.08 233.85 0.21 0.37

 HUB 13.07 0.00 -0.02 233.85 -0.08 233.85 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.33 47.36 10.97 379.08 445.48 5.87 515.70 495.33 22.89

 MEAN 54.62 44.80 9.82 329.27 403.93 5.87 515.70 495.33 22.89

 HUB 49.16 38.84 10.32 270.45 357.59 5.87 515.70 495.33 22.89

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.98 196.28 246.35 1113.39 0.28 2.05 1.78 7.43

 MEAN 15.50 313.88 192.06 248.26 1111.55 0.28 2.13 1.86 5.75

 HUB 12.59 330.05 215.14 250.29 1109.74 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.22 302.14 174.94 0.27 3522.74 0.92 0.91

 MEAN 320.68 279.60 128.61 0.25 2977.80 0.92 0.91 0.91 1.60

 HUB 260.51 254.37 45.37 0.23 2709.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.51 1.08 6.16 531.56 1.02 523.71 501.30 18.91

 MEAN 6.44 1.06 6.10 529.77 1.02 521.98 500.61 19.87

 HUB 6.40 1.06 6.03 528.90 1.02 520.28 500.52 20.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.55 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.73 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.68 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 343.5902 195.5852 282.4901 1110.1843 0.3095 -0.1717 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4435 6.0366 520.7388 501.2484 20.7345 34.6972 33.0000 -1.6972

 

NASA/TM—2013-218094 L–107
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 288.8376 65.9563 281.2062 1113.0863 0.2595 0.1558 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4417 6.1519 523.4720 500.5298 410.5396 0.0249 0.3882

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 280.9701 0.0000 280.9701 1113.4316 0.2523 0.3114 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1633 523.8083 500.6618 0.0000 0.0600 0.0376 0.1881

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 6.4372 1.0637 530.0475 10.0480 230.2227 1.7847

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63557.008 0.461 91.027 257097.906 0.587465E-02

 

Melt Ratio at Stator LE, Throat, TE

0.20836E+00 0.26569E+00 0.45252E+00

 trTOT = 1.1485 Tt4 = 530.0475 T1 = 461.5134

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 430197.88 616.1348 83.6861 1.5329 0.8352 15.5941 1.1485 37.3740

NASA/TM—2013-218094 L–108
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.612 EfDer = 0.953 SH = 0.712429E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.936 2340.415 4.337 459.583 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.917 WH2O = 0.018 lbm/sec H2O = 0.287g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.746 2486.369 1.381 0.249 53.371 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62025.441 20344.822 3.432 831.557 242.299 619.754 2.558

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 179.01 -0.06 179.01 0.17 0.44 447.61

 MEAN 17.06 0.00 -0.02 179.01 -0.06 179.01 0.17 0.38

 HUB 12.51 0.00 -0.02 179.01 -0.06 179.01 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.98 50.47 16.51 421.35 457.85 4.25 457.01 452.08 25.13

 MEAN 62.81 47.20 15.61 348.44 391.79 4.25 457.01 452.08 25.13

 HUB 54.99 38.62 16.37 255.50 312.03 4.25 457.01 452.08 25.13

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 377.51 291.14 240.31 1053.19 0.36 7.29 6.52 16.04

 MEAN 18.04 381.73 294.18 243.27 1050.31 0.36 7.43 6.80 12.53

 HUB 15.00 412.95 330.67 247.35 1046.78 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 421.35 273.32 130.20 0.26 6007.58 0.92 0.87

 MEAN 368.37 254.33 74.19 0.24 5306.83 0.92 0.87 0.87 1.77

 HUB 306.36 248.54 24.31 0.24 4960.84 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.54 479.28 1.04 467.84 466.89 23.14

 MEAN 4.88 1.13 4.46 476.99 1.04 465.29 465.60 25.53

 HUB 4.84 1.12 4.36 475.85 1.04 462.16 465.28 28.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.46 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.41 16.96 12.70 4.26 0.95 0.52 2.22

 HUB 53.20 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 392.7730 293.6056 260.8954 1049.9338 0.3741 -0.0358 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8879 4.4435 464.9998 466.1010 26.8085 48.3760 35.4000 -12.9760

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 259.5317 63.4894 251.6462 1057.7570 0.2454 0.5173 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8769 4.6795 471.9714 465.2184 554.9116 0.0349 0.6092

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 258.4492 0.0000 258.4492 1057.7725 0.2443 0.4852 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6591 472.0178 465.8537 0.0000 0.0600 0.0871 0.4710

NASA/TM—2013-218094 L–109
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8132 4.8539 1.1192 477.3730 17.7916 167.2555 1.2966

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 110917.617 0.625 162.567 270912.844 0.131918E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.063 EfDer = 0.958 SH = 0.199593E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.936 2340.415 4.854 477.372 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.884 WH2O = 0.052 lbm/sec H2O = 0.857g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.352 2439.619 1.379 0.250 53.413 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58195.629 20334.539 2.674 590.487 220.820 468.502 2.122

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.52 -0.08 236.52 0.22 0.46 437.49

 MEAN 18.08 0.00 -0.02 236.52 -0.08 236.52 0.22 0.41

 HUB 15.21 0.00 -0.02 236.52 -0.08 236.52 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.60 46.36 14.24 419.71 481.84 4.69 472.90 467.87 37.53

 MEAN 57.36 42.30 15.06 369.23 438.56 4.69 472.90 467.87 37.53

 HUB 52.72 37.84 14.88 310.65 390.51 4.69 472.90 467.87 37.53

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 347.53 241.60 249.81 1070.80 0.32 2.33 2.04 9.02

 MEAN 18.01 347.10 238.51 252.17 1068.51 0.32 2.40 2.13 7.35

 HUB 15.22 367.74 265.16 254.80 1066.26 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 417.06 305.27 175.45 0.29 4935.20 0.92 0.88

 MEAN 367.83 283.40 129.32 0.27 4297.11 0.92 0.88 0.88 1.71

 HUB 310.91 258.88 45.76 0.24 4037.75 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.11 5.02 493.49 1.03 483.83 478.03 26.65

 MEAN 5.32 1.10 4.95 491.41 1.03 481.77 476.98 28.66

 HUB 5.30 1.09 4.88 490.56 1.03 479.75 476.83 30.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.04 35.08 31.50 3.58 0.93 0.55 1.40

 MEAN 43.41 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.14 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.1153 239.1843 283.7559 1067.4010 0.3477 -0.1071 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3353 4.9133 480.8127 477.5764 29.9183 40.1283 30.6000 -9.5283

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.9565 58.2927 268.7062 1072.8915 0.2563 0.3675 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3297 5.0952 485.7780 476.5392 491.5697 0.0245 0.4634

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.9335 0.0000 284.9335 1072.3781 0.2657 0.3548 0.5911

NASA/TM—2013-218094 L–110
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0630 485.3326 476.9183 0.0000 0.0600 0.0657 0.2841

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8316 5.3138 1.0947 491.8197 14.4479 188.8713 1.4641

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90396.781 0.520 132.491 246422.656 0.228646E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.961 EfDer = 0.974 SH = 0.269454E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.936 2340.415 5.314 491.819 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.866 WH2O = 0.070 lbm/sec H2O = 1.228g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.865 2403.521 1.378 0.250 53.436 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54803.297 20328.926 2.663 545.479 204.836 424.468 2.072

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 241.12 -0.08 241.12 0.22 0.44 420.95

 MEAN 17.74 0.00 -0.02 241.12 -0.08 241.12 0.22 0.41

 HUB 15.05 0.00 -0.02 241.12 -0.08 241.12 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.54 46.36 13.18 409.91 475.64 5.13 487.18 477.61 30.17

 MEAN 56.36 43.40 12.96 362.29 435.26 5.13 487.18 477.61 30.17

 HUB 51.90 38.84 13.06 307.38 390.73 5.13 487.18 477.61 30.17

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.97 225.39 254.52 1085.27 0.31 2.26 1.98 8.75

 MEAN 17.51 341.61 225.49 256.61 1083.33 0.32 2.34 2.07 6.78

 HUB 14.85 364.37 256.36 258.92 1081.43 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.60 311.29 179.21 0.29 4466.57 0.92 0.89

 MEAN 357.55 288.60 132.06 0.27 3949.10 0.92 0.89 0.89 1.65

 HUB 303.30 263.14 46.93 0.24 3808.25 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.84 1.10 5.46 506.37 1.03 497.15 486.17 22.84

 MEAN 5.78 1.09 5.40 504.69 1.03 495.38 485.41 24.21

 HUB 5.76 1.08 5.33 504.23 1.03 493.64 485.53 25.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.53 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 41.31 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.72 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.9251 226.9737 288.3002 1082.1769 0.3391 -0.1156 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7910 5.3546 494.3626 486.0368 25.2729 38.2127 31.5000 -6.7127

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 284.0787 61.9698 277.2372 1086.8673 0.2614 0.3130 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7875 5.5231 498.6630 485.0975 451.3937 0.0188 0.4353

 

NASA/TM—2013-218094 L–111
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.8449 0.0000 288.8449 1086.6150 0.2658 0.3377 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5020 498.4464 485.4610 0.0000 0.0600 0.0516 0.2595

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8537 5.7745 1.0867 505.0965 13.2777 194.9160 1.5110

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83277.211 0.509 122.056 245358.891 0.308218E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.266 EfDer = 0.985 SH = 0.361733E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.936 2340.415 5.775 505.096 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.842 WH2O = 0.094 lbm/sec H2O = 1.744g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.152 2371.722 1.377 0.251 53.466 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51798.398 20321.492 2.686 513.330 191.131 395.845 2.071

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 242.17 -0.08 242.17 0.22 0.42 398.62

 MEAN 16.97 0.00 -0.02 242.17 -0.08 242.17 0.22 0.39

 HUB 14.32 0.00 -0.02 242.17 -0.08 242.17 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.39 46.36 12.03 393.37 462.00 5.58 500.43 486.22 25.93

 MEAN 55.07 43.80 11.27 346.61 422.89 5.58 500.43 486.22 25.93

 HUB 50.38 37.84 12.54 292.47 379.78 5.58 500.43 486.22 25.93

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.60 205.94 254.78 1098.16 0.30 2.16 1.89 8.34

 MEAN 16.57 329.28 206.28 256.66 1096.42 0.30 2.24 1.97 6.35

 HUB 13.89 350.78 236.88 258.72 1094.71 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 385.60 311.76 179.67 0.28 3889.70 0.92 0.90

 MEAN 338.50 288.72 132.22 0.26 3420.29 0.92 0.90 0.90 1.61

 HUB 283.69 262.92 46.81 0.24 3291.43 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.26 1.08 5.90 517.73 1.03 509.20 493.27 20.79

 MEAN 6.20 1.07 5.83 516.21 1.02 507.58 492.64 21.86

 HUB 6.19 1.07 5.77 515.79 1.02 506.00 492.78 22.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.95 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.79 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.48 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.6136 207.4409 281.4213 1095.5906 0.3191 -0.0920 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2148 5.7980 506.8619 493.1763 22.5646 36.3946 32.4000 -3.9946

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 282.9038 63.4471 275.6974 1099.2023 0.2574 0.2727 2.2705

 

NASA/TM—2013-218094 L–112
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2131 5.9379 510.2164 492.4214 432.2457 0.0144 0.4112

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.6465 0.0000 280.6465 1099.2979 0.2553 0.3215 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9320 510.3186 492.7352 0.0000 0.0600 0.0420 0.2574

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8681 6.2024 1.0741 516.5773 11.4818 210.8375 1.6344

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72231.953 0.486 105.867 251522.641 0.410729E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.709 EfDer = 0.993 SH = 0.479220E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.936 2340.415 6.202 516.577 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.812 WH2O = 0.124 lbm/sec H2O = 2.432g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.343 2345.219 1.375 0.252 53.504 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49229.426 20311.998 2.830 509.668 180.085 384.739 2.136

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.81 -0.08 231.81 0.21 0.40 374.92

 MEAN 15.91 0.00 -0.02 231.81 -0.08 231.81 0.21 0.36

 HUB 13.07 0.00 -0.02 231.81 -0.08 231.81 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.23 47.36 10.87 374.17 440.22 6.02 512.32 493.58 23.63

 MEAN 54.51 44.80 9.71 325.01 399.27 6.02 512.32 493.58 23.63

 HUB 49.04 38.84 10.20 266.94 353.60 6.02 512.32 493.58 23.63

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 311.32 192.87 244.38 1109.64 0.28 2.05 1.78 7.43

 MEAN 15.50 310.38 188.97 246.22 1107.85 0.28 2.13 1.86 5.75

 HUB 12.59 326.48 212.11 248.19 1106.09 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.41 299.72 173.53 0.27 3461.63 0.92 0.91

 MEAN 316.52 277.30 127.55 0.25 2929.87 0.92 0.91 0.91 1.59

 HUB 257.14 252.24 45.03 0.23 2671.52 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.66 1.07 6.31 527.78 1.02 520.10 499.59 19.70

 MEAN 6.59 1.06 6.25 526.06 1.02 518.43 498.89 20.69

 HUB 6.56 1.06 6.18 525.23 1.02 516.78 498.80 21.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.28 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.51 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.52 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.8774 192.4364 280.1515 1106.5020 0.3072 -0.1726 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5953 6.1846 517.2058 499.5245 21.6220 34.4852 33.0000 -1.4852

 

NASA/TM—2013-218094 L–113
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 286.5480 65.4335 278.9771 1109.3185 0.2583 0.1514 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5937 6.2997 519.8497 498.8694 410.5396 0.0246 0.3846

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.7604 0.0000 278.7604 1109.6664 0.2512 0.3077 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3110 520.1877 499.0434 0.0000 0.0600 0.0374 0.1832

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 6.5891 1.0623 526.3397 9.7792 231.1906 1.7922

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 61749.730 0.460 90.504 264250.938 0.530462E-02

 

Melt Ratio at Stator LE, Throat, TE

0.71512E-01 0.10700E+00 0.24091E+00

 trTOT = 1.1453 Tt4 = 526.3397 T1 = 459.5827

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 418573.28 613.4843 82.7456 1.5193 0.8357 15.6115 1.1453 37.3740

NASA/TM—2013-218094 L–114
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.664 EfDer = 0.953 SH = 0.716928E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.847 2268.818 4.829 461.405 1.000 1.000 0.980

 W Kg/sec = 12.658 Wdry = 27.827 WH2O = 0.020 lbm/sec H2O = 0.321g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.957 2405.546 1.381 0.249 53.372 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59993.355 21843.670 3.552 831.557 234.137 619.754 2.647

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.15 -0.06 173.15 0.17 0.43 433.06

 MEAN 17.06 0.00 -0.02 173.15 -0.06 173.15 0.17 0.36

 HUB 12.51 0.00 -0.02 173.15 -0.06 173.15 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.03 50.47 16.56 408.46 443.70 4.74 459.00 454.05 25.66

 MEAN 62.86 47.20 15.66 337.78 379.62 4.74 459.00 454.05 25.66

 HUB 55.05 38.62 16.43 247.69 302.26 4.74 459.00 454.05 25.66

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 366.04 282.21 233.11 1054.65 0.35 7.29 6.52 16.04

 MEAN 18.04 370.07 285.23 235.79 1051.96 0.35 7.43 6.80 12.53

 HUB 15.00 400.10 320.51 239.47 1048.66 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 408.46 265.10 126.25 0.25 5823.25 0.92 0.87

 MEAN 357.10 246.50 71.87 0.23 5145.38 0.92 0.87 0.87 1.77

 HUB 296.99 240.63 23.53 0.23 4808.47 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 479.92 1.04 469.16 468.09 23.76

 MEAN 5.39 1.12 4.96 477.76 1.04 466.77 466.84 26.04

 HUB 5.35 1.11 4.85 476.69 1.03 463.84 466.51 29.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.44 28.44 24.20 4.24 0.93 0.58 1.80

 MEAN 50.42 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 53.23 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 380.7316 284.6728 252.8200 1051.6017 0.3620 -0.0360 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.4007 4.9390 466.4957 467.3143 27.2691 48.3915 35.4000 -12.9915

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 252.0898 61.6689 244.4304 1058.9187 0.2381 0.5169 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3898 5.1841 473.0251 466.5126 554.9116 0.0338 0.6081

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 250.9924 0.0000 250.9924 1058.9370 0.2370 0.4838 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1624 473.0706 467.0942 0.0000 0.0600 0.0872 0.4695

NASA/TM—2013-218094 L–115
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8127 5.3653 1.1112 478.1212 16.7173 167.0791 1.2952

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 104226.031 0.625 164.014 289706.469 0.127409E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.010 EfDer = 0.958 SH = 0.189264E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.847 2268.818 5.365 478.121 1.000 1.000 0.980

 W Kg/sec = 12.658 Wdry = 27.794 WH2O = 0.053 lbm/sec H2O = 0.898g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.250 2363.137 1.379 0.250 53.410 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56530.691 21833.559 2.751 590.487 214.647 468.502 2.183

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 229.76 -0.08 229.76 0.22 0.44 423.77

 MEAN 18.08 0.00 -0.02 229.76 -0.08 229.76 0.22 0.40

 HUB 15.21 0.00 -0.02 229.76 -0.08 229.76 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.55 46.36 14.19 406.87 467.33 5.19 473.90 468.97 37.72

 MEAN 57.31 42.30 15.01 357.93 425.40 5.19 473.90 468.97 37.72

 HUB 52.67 37.84 14.83 301.15 378.85 5.19 473.90 468.97 37.72

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 337.23 233.41 243.40 1071.11 0.31 2.33 2.04 9.02

 MEAN 18.01 336.93 230.71 245.54 1068.99 0.32 2.40 2.13 7.35

 HUB 15.22 357.05 256.93 247.93 1066.89 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.30 297.40 170.89 0.28 4767.92 0.92 0.88

 MEAN 356.58 275.92 125.87 0.26 4156.57 0.92 0.88 0.88 1.70

 HUB 301.40 251.88 44.47 0.24 3912.52 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.93 1.10 5.54 493.22 1.03 484.12 478.67 27.46

 MEAN 5.85 1.09 5.47 491.28 1.03 482.21 477.66 29.38

 HUB 5.82 1.09 5.39 490.51 1.03 480.32 477.51 31.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.80 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 43.22 27.14 23.50 3.64 0.95 0.52 1.63

 HUB 46.02 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 360.2955 231.3612 276.1971 1067.9373 0.3374 -0.1077 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8627 5.4247 481.2944 478.2202 30.6041 39.9518 30.6000 -9.3518

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 268.0900 56.8370 261.9958 1073.0574 0.2498 0.3635 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8573 5.6120 485.9264 477.2898 491.5697 0.0234 0.4595

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 277.7334 0.0000 277.7334 1072.5746 0.2589 0.3513 0.5911

NASA/TM—2013-218094 L–116
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5786 485.5065 477.6367 0.0000 0.0600 0.0647 0.2799

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8325 5.8408 1.0886 491.6717 13.5517 189.3716 1.4680

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 84767.125 0.519 133.393 263867.625 0.215450E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.803 EfDer = 0.975 SH = 0.252015E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.847 2268.818 5.841 491.671 1.000 1.000 0.980

 W Kg/sec = 12.658 Wdry = 27.776 WH2O = 0.070 lbm/sec H2O = 1.265g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.234 2330.345 1.378 0.250 53.430 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53444.703 21828.148 2.727 545.479 200.036 424.468 2.122

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 235.14 -0.08 235.14 0.22 0.43 408.13

 MEAN 17.74 0.00 -0.02 235.14 -0.08 235.14 0.22 0.39

 HUB 15.05 0.00 -0.02 235.14 -0.08 235.14 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.39 46.36 13.03 397.37 461.80 5.65 487.26 478.28 30.97

 MEAN 56.20 43.40 12.80 351.21 422.72 5.65 487.26 478.28 30.97

 HUB 51.73 38.84 12.89 297.98 379.64 5.65 487.26 478.28 30.97

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 330.24 217.04 248.90 1084.64 0.30 2.26 1.98 8.75

 MEAN 17.51 332.05 217.63 250.80 1082.84 0.31 2.34 2.07 6.78

 HUB 14.85 354.35 248.20 252.90 1081.07 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 392.22 304.37 175.18 0.28 4301.18 0.92 0.89

 MEAN 346.62 282.02 128.99 0.26 3811.30 0.92 0.89 0.89 1.64

 HUB 294.02 257.01 45.81 0.24 3687.06 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.38 1.09 5.99 505.26 1.03 496.56 486.46 23.91

 MEAN 6.32 1.08 5.93 503.72 1.02 494.92 485.75 25.24

 HUB 6.30 1.08 5.86 503.32 1.02 493.30 485.86 26.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.09 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 40.95 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.46 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 356.8327 219.0532 281.6830 1081.7369 0.3299 -0.1170 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3313 5.8785 493.9444 486.3304 26.3001 37.8707 31.5000 -6.3707

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 277.9821 60.6399 271.2874 1086.0946 0.2559 0.3054 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3281 6.0505 497.9375 485.4886 451.3937 0.0177 0.4289

 

NASA/TM—2013-218094 L–117
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 282.5868 0.0000 282.5868 1085.8560 0.2602 0.3318 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0287 497.7325 485.8210 0.0000 0.0600 0.0502 0.2522

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8554 6.3148 1.0812 504.1011 12.4303 196.1340 1.5204

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 77922.211 0.507 122.621 263144.531 0.286348E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.008 EfDer = 0.986 SH = 0.333534E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.847 2268.818 6.315 504.101 1.000 1.000 0.980

 W Kg/sec = 12.658 Wdry = 27.754 WH2O = 0.093 lbm/sec H2O = 1.765g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.904 2301.437 1.377 0.251 53.456 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50696.602 21821.104 2.739 513.330 187.439 395.845 2.112

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 237.02 -0.08 237.02 0.22 0.41 386.80

 MEAN 16.97 0.00 -0.02 237.02 -0.08 237.02 0.22 0.38

 HUB 14.32 0.00 -0.02 237.02 -0.08 237.02 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.14 46.36 11.78 381.33 449.06 6.11 499.63 486.52 27.01

 MEAN 54.81 43.80 11.01 336.01 411.26 6.11 499.63 486.52 27.01

 HUB 50.11 37.84 12.27 283.52 369.61 6.11 499.63 486.52 27.01

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 318.61 197.56 249.97 1096.66 0.29 2.16 1.89 8.34

 MEAN 16.57 320.57 198.54 251.68 1095.06 0.29 2.24 1.97 6.35

 HUB 13.89 341.73 229.11 253.56 1093.48 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 373.81 305.86 176.25 0.28 3731.43 0.92 0.90

 MEAN 328.15 283.10 129.61 0.26 3291.93 0.92 0.90 0.90 1.59

 HUB 275.01 257.68 45.90 0.24 3183.49 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.81 1.08 6.43 515.86 1.02 507.78 493.25 22.00

 MEAN 6.75 1.07 6.37 514.48 1.02 506.30 492.67 23.04

 HUB 6.74 1.07 6.30 514.14 1.02 504.84 492.81 24.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.32 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.27 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.10 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 340.5732 199.6547 275.9131 1094.2600 0.3112 -0.0937 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7650 6.3324 505.5974 493.1684 23.7613 35.8900 32.4000 -3.4900

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 277.7216 62.2848 270.6472 1097.5939 0.2530 0.2617 2.2705

 

NASA/TM—2013-218094 L–118
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7636 6.4737 508.6895 492.4963 432.2457 0.0136 0.4025

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 275.4766 0.0000 275.4766 1097.6885 0.2510 0.3131 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4679 508.7892 492.7820 0.0000 0.0600 0.0408 0.2472

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8700 6.7527 1.0693 514.8248 10.7246 212.9550 1.6508

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67410.609 0.482 106.080 270136.844 0.376372E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.362 EfDer = 0.994 SH = 0.435992E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.847 2268.818 6.753 514.824 1.000 1.000 0.980

 W Kg/sec = 12.658 Wdry = 27.725 WH2O = 0.121 lbm/sec H2O = 2.419g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.392 2277.341 1.376 0.252 53.490 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48336.641 21812.223 2.875 509.668 177.251 384.739 2.171

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 227.60 -0.08 227.60 0.21 0.39 364.07

 MEAN 15.91 0.00 -0.02 227.60 -0.08 227.60 0.21 0.35

 HUB 13.07 0.00 -0.02 227.60 -0.08 227.60 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.90 47.36 10.54 362.72 428.28 6.56 510.71 493.55 24.86

 MEAN 54.16 44.80 9.36 315.06 388.74 6.56 510.71 493.55 24.86

 HUB 48.68 38.84 9.84 258.78 344.69 6.56 510.71 493.55 24.86

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 303.07 184.46 240.48 1107.39 0.27 2.05 1.78 7.43

 MEAN 15.50 302.57 181.41 242.16 1105.74 0.27 2.13 1.86 5.75

 HUB 12.59 318.69 205.06 243.95 1104.11 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.20 294.93 170.74 0.27 3310.58 0.92 0.91

 MEAN 306.84 272.71 125.43 0.25 2812.71 0.92 0.91 0.91 1.58

 HUB 249.27 247.92 44.21 0.22 2582.73 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.22 1.07 6.86 525.23 1.02 517.94 499.29 21.00

 MEAN 7.15 1.06 6.79 523.66 1.02 516.40 498.64 21.97

 HUB 7.11 1.05 6.72 522.94 1.02 514.88 498.56 22.98

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.49 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.84 27.38 23.50 3.88 0.93 0.44 1.64

 HUB 40.05 10.27 6.50 3.77 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 331.6656 184.7392 275.4514 1104.4344 0.3003 -0.1752 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1524 6.7257 515.2173 499.2310 22.9352 33.8489 33.0000 -0.8489

 

NASA/TM—2013-218094 L–119
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 282.0485 64.4060 274.5965 1107.0106 0.2548 0.1366 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1510 6.8404 517.6304 498.6548 410.5396 0.0237 0.3742

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 274.3943 0.0000 274.3943 1107.3502 0.2478 0.2967 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8523 517.9587 498.8162 0.0000 0.0600 0.0368 0.1688

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 7.1461 1.0583 523.9276 9.1179 234.2848 1.8162

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57497.500 0.456 90.480 284158.781 0.480916E-02

 

Melt Ratio at Stator LE, Throat, TE

0.64056E-01 0.95984E-01 0.21751E+00

 trTOT = 1.1355 Tt4 = 523.9276 T1 = 461.4051

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 391823.50 616.5878 79.9566 1.4800 0.8371 15.6637 1.1355 37.3740

NASA/TM—2013-218094 L–120
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.178 EfDer = 0.965 SH = 0.943266E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.857 2149.058 5.592 471.074 1.000 1.000 0.980

 W Kg/sec = 14.480 Wdry = 31.827 WH2O = 0.030 lbm/sec H2O = 0.478g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.803 2255.067 1.380 0.249 53.379 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60507.898 24987.320 3.558 831.557 233.728 619.754 2.652

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.63 -0.06 174.63 0.17 0.40 405.97

 MEAN 17.06 0.00 -0.02 174.63 -0.06 174.63 0.17 0.35

 HUB 12.51 0.00 -0.02 174.63 -0.06 174.63 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.71 50.47 15.24 386.90 424.54 5.49 468.63 462.03 25.10

 MEAN 61.38 47.20 14.18 319.95 364.56 5.49 468.63 462.03 25.10

 HUB 53.34 38.62 14.72 234.61 292.52 5.49 468.63 462.03 25.10

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 350.93 259.37 236.39 1063.68 0.33 7.29 6.52 16.04

 MEAN 18.04 357.33 265.89 238.72 1061.41 0.34 7.43 6.80 12.53

 HUB 15.00 389.69 305.42 242.03 1058.52 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.90 268.59 127.53 0.25 5352.06 0.92 0.88

 MEAN 338.25 249.44 72.36 0.24 4796.58 0.92 0.88 0.88 1.67

 HUB 281.31 243.23 24.11 0.23 4582.00 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.78 487.17 1.03 477.30 474.09 24.11

 MEAN 6.16 1.10 5.70 485.50 1.03 475.26 473.19 25.96

 HUB 6.13 1.10 5.59 484.86 1.03 472.68 473.18 28.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.65 28.35 24.20 4.15 0.93 0.54 1.80

 MEAN 48.08 16.86 12.70 4.16 0.95 0.48 2.22

 HUB 51.60 -5.69 -9.30 3.61 0.95 0.36 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.965 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.7193 265.3711 255.9924 1061.0034 0.3475 -0.0413 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1703 5.6824 474.9516 473.6670 27.1486 46.0306 35.4000 -10.6306

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.4999 62.7477 248.7065 1067.2493 0.2403 0.4764 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1622 5.9227 480.5736 472.9157 554.9116 0.0269 0.5654

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.1144 0.0000 255.1144 1067.2869 0.2390 0.4548 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9043 480.6315 473.4919 0.0000 0.0600 0.0722 0.4382

NASA/TM—2013-218094 L–121
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8308 6.1403 1.0980 485.8442 14.7714 174.2629 1.3509

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92186.977 0.616 165.961 326276.250 0.155746E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.149 EfDer = 0.973 SH = 0.221849E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.857 2149.058 6.140 485.844 1.000 1.000 0.980

 W Kg/sec = 14.480 Wdry = 31.786 WH2O = 0.071 lbm/sec H2O = 1.185g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.811 2220.535 1.379 0.250 53.420 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57456.313 24974.764 2.729 590.487 216.342 468.502 2.166

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.52 -0.08 233.52 0.22 0.42 398.20

 MEAN 18.08 0.00 -0.02 233.52 -0.08 233.52 0.22 0.39

 HUB 15.21 0.00 -0.02 233.52 -0.08 233.52 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.79 46.36 12.43 385.40 450.69 5.94 481.49 475.36 36.47

 MEAN 55.45 42.30 13.15 339.04 411.74 5.94 481.49 475.36 36.47

 HUB 50.70 37.84 12.86 285.25 368.70 5.94 481.49 475.36 36.47

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 324.68 208.67 248.75 1077.71 0.30 2.33 2.04 9.02

 MEAN 18.01 326.68 209.61 250.57 1076.00 0.30 2.40 2.13 7.35

 HUB 15.22 348.71 240.41 252.59 1074.30 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 382.96 303.74 174.29 0.28 4262.59 0.92 0.89

 MEAN 337.76 281.44 128.15 0.26 3776.44 0.92 0.89 0.89 1.61

 HUB 285.49 256.58 45.09 0.24 3660.91 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.68 1.09 6.28 498.62 1.03 490.19 483.45 28.27

 MEAN 6.62 1.08 6.21 497.16 1.02 488.63 482.73 29.82

 HUB 6.60 1.08 6.14 496.81 1.02 487.10 482.84 31.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.99 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 39.91 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.58 10.12 6.50 3.62 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 351.6508 210.1939 281.9163 1074.8823 0.3272 -0.1211 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6285 6.1617 487.6548 483.3077 31.0765 36.7078 30.6000 -6.1078

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.7548 58.2500 268.5091 1079.1078 0.2546 0.2996 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6254 6.3376 491.5012 482.4925 491.5697 0.0172 0.4056

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.4212 0.0000 284.4212 1078.6199 0.2637 0.3062 0.5911

NASA/TM—2013-218094 L–122
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3046 491.0704 482.8432 0.0000 0.0600 0.0491 0.2212

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8530 6.6120 1.0768 497.5287 11.6855 201.9146 1.5652

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73179.422 0.499 131.743 298414.688 0.248917E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.718 EfDer = 0.988 SH = 0.285430E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.857 2149.058 6.612 497.528 1.000 1.000 0.980

 W Kg/sec = 14.480 Wdry = 31.766 WH2O = 0.091 lbm/sec H2O = 1.601g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.365 2194.306 1.378 0.251 53.441 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54711.438 24968.484 2.682 545.479 203.398 424.468 2.087

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.71 -0.08 240.71 0.22 0.41 384.31

 MEAN 17.74 0.00 -0.02 240.71 -0.08 240.71 0.22 0.38

 HUB 15.05 0.00 -0.02 240.71 -0.08 240.71 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.41 46.36 11.05 376.39 446.85 6.39 492.91 483.40 31.52

 MEAN 54.12 43.40 10.72 332.67 410.69 6.39 492.91 483.40 31.52

 HUB 49.55 38.84 10.71 282.25 371.02 6.39 492.91 483.40 31.52

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 319.77 191.30 256.24 1089.08 0.29 2.26 1.98 8.75

 MEAN 17.51 323.73 195.81 257.80 1087.68 0.30 2.34 2.07 6.78

 HUB 14.85 347.78 231.50 259.54 1086.31 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.52 313.27 180.22 0.29 3791.32 0.92 0.90

 MEAN 328.32 289.86 132.51 0.27 3429.44 0.92 0.90 0.90 1.55

 HUB 278.50 263.76 47.00 0.24 3439.06 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.12 1.08 6.71 508.86 1.02 500.71 490.22 25.62

 MEAN 7.07 1.07 6.66 507.78 1.02 499.43 489.76 26.70

 HUB 7.07 1.07 6.60 507.81 1.02 498.17 490.11 27.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.74 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 37.22 27.20 23.50 3.70 0.94 0.44 1.62

 HUB 41.73 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 350.3441 197.0956 289.6451 1086.4955 0.3225 -0.1315 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0853 6.6002 498.3728 490.3721 27.8571 34.2342 31.5000 -2.7342

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.9757 62.6018 280.0644 1089.9929 0.2633 0.2295 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0837 6.7556 501.5911 489.6571 451.3937 0.0135 0.3701

 

NASA/TM—2013-218094 L–123
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.5813 0.0000 291.5813 1089.7507 0.2676 0.2771 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7346 501.3797 489.9785 0.0000 0.0600 0.0392 0.1811

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8718 7.0726 1.0697 508.1526 10.6247 211.2733 1.6378

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66678.508 0.483 120.039 298691.219 0.318902E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.686 EfDer = 0.997 SH = 0.363707E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.857 2149.058 7.073 508.152 1.000 1.000 0.980

 W Kg/sec = 14.480 Wdry = 31.741 WH2O = 0.116 lbm/sec H2O = 2.135g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.536 2171.246 1.377 0.251 53.466 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52277.766 24960.738 2.670 513.330 192.265 395.845 2.059

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.41 -0.08 244.41 0.22 0.40 364.92

 MEAN 16.97 0.00 -0.02 244.41 -0.08 244.41 0.22 0.37

 HUB 14.32 0.00 -0.02 244.41 -0.08 244.41 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.92 46.36 9.56 361.20 436.19 6.83 503.40 490.54 28.46

 MEAN 52.49 43.80 8.69 318.27 401.35 6.83 503.40 490.54 28.46

 HUB 47.70 37.84 9.86 268.56 363.19 6.83 503.40 490.54 28.46

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 310.68 171.26 259.21 1099.12 0.28 2.16 1.89 8.34

 MEAN 16.57 314.76 176.56 260.58 1097.91 0.29 2.24 1.97 6.35

 HUB 13.89 337.69 212.94 262.09 1096.73 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.08 317.19 182.81 0.29 3235.07 0.92 0.91

 MEAN 310.83 293.14 134.27 0.27 2927.65 0.92 0.91 0.91 1.49

 HUB 260.49 266.37 47.56 0.24 2958.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.53 1.06 7.13 517.80 1.02 510.13 496.13 24.20

 MEAN 7.49 1.06 7.08 516.88 1.02 509.01 495.78 25.04

 HUB 7.49 1.06 7.02 516.98 1.02 507.91 496.15 25.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.45 35.19 31.50 3.69 0.93 0.41 1.40

 MEAN 34.12 27.26 23.50 3.76 0.93 0.40 1.62

 HUB 39.09 10.28 6.50 3.78 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 336.4299 177.5493 285.7644 1097.0325 0.3067 -0.1061 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4982 7.0323 508.2255 496.3105 25.8603 31.8532 32.4000 0.5468

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.7083 64.7488 281.3539 1099.5828 0.2626 0.1775 2.2705

 

NASA/TM—2013-218094 L–124
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4974 7.1522 510.5970 495.7749 432.2457 0.0121 0.3393

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.2980 0.0000 286.2980 1099.6910 0.2603 0.2479 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1478 510.7081 496.0298 0.0000 0.0600 0.0367 0.1673

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8786 7.4869 1.0586 517.2210 9.0693 232.1106 1.7993

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57061.410 0.455 102.726 307651.938 0.403848E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.830 EfDer = 1.000 SH = 0.455890E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.857 2149.058 7.487 517.219 1.000 1.000 0.980

 W Kg/sec = 14.480 Wdry = 31.712 WH2O = 0.145 lbm/sec H2O = 2.787g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.460 2152.128 1.375 0.252 53.496 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50192.527 24951.590 2.780 509.668 183.345 384.739 2.098

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.34 -0.08 236.34 0.21 0.38 344.06

 MEAN 15.91 0.00 -0.02 236.34 -0.08 236.34 0.21 0.35

 HUB 13.07 0.00 -0.02 236.34 -0.08 236.34 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.48 47.36 8.12 343.57 417.08 7.25 512.79 496.57 26.64

 MEAN 51.63 44.80 6.83 298.43 380.75 7.25 512.79 496.57 26.64

 HUB 46.05 38.84 7.21 245.12 340.56 7.25 512.79 496.57 26.64

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 296.64 157.97 251.08 1108.12 0.27 2.05 1.78 7.43

 MEAN 15.50 298.69 159.68 252.43 1106.87 0.27 2.13 1.86 5.75

 HUB 12.59 317.02 189.84 253.89 1105.65 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 336.45 308.05 178.48 0.28 2835.41 0.92 0.91

 MEAN 290.64 284.38 130.97 0.26 2475.91 0.92 0.91 0.91 1.47

 HUB 236.11 258.07 46.27 0.23 2391.19 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.90 1.06 7.53 525.65 1.02 518.67 501.24 23.13

 MEAN 7.85 1.05 7.47 524.58 1.01 517.50 500.82 23.93

 HUB 7.84 1.05 7.41 524.33 1.01 516.36 500.97 24.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.18 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.32 27.42 23.50 3.92 0.93 0.38 1.64

 HUB 36.79 10.33 6.50 3.83 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 330.1043 162.6052 287.2775 1105.4581 0.2986 -0.1940 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8559 7.3924 516.2102 501.4317 24.9920 29.5108 33.0000 3.4892

 

NASA/TM—2013-218094 L–125
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.2436 67.4191 287.4430 1107.2977 0.2666 0.0312 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8535 7.4808 517.9339 500.9949 410.5396 0.0261 0.3082

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.1825 0.0000 287.1825 1107.6708 0.2593 0.2222 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4954 518.2902 501.0649 0.0000 0.0600 0.0408 0.0682

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8787 7.8477 1.0482 524.8257 7.6318 258.3218 2.0025

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 48150.539 0.425 86.684 324505.875 0.488293E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.25349E+00 0.30413E+00 0.46275E+00

 trTOT = 1.1141 Tt4 = 524.8257 T1 = 471.0738

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 337256.84 607.1528 79.8032 1.4033 0.8522 14.1777 1.1141 37.3740

NASA/TM—2013-218094 L–126
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.356 EfDer = 0.994 SH = 0.120018E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.134 1970.532 6.513 481.867 1.000 1.000 0.980

 W Kg/sec = 18.243 Wdry = 40.086 WH2O = 0.048 lbm/sec H2O = 0.691g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.310 2044.452 1.380 0.249 53.387 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67152.094 31476.273 3.251 831.557 255.761 619.754 2.423

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 193.81 -0.07 193.81 0.18 0.38 368.05

 MEAN 17.06 0.00 -0.02 193.81 -0.07 193.81 0.18 0.33

 HUB 12.51 0.00 -0.02 193.81 -0.07 193.81 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.36 50.47 10.89 354.76 404.30 6.37 478.86 470.56 23.65

 MEAN 56.56 47.20 9.36 293.37 351.66 6.37 478.86 470.56 23.65

 HUB 47.99 38.62 9.37 215.12 289.60 6.37 478.86 470.56 23.65

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 339.58 212.30 265.04 1071.81 0.32 7.29 6.52 16.04

 MEAN 18.04 352.09 229.66 266.88 1070.32 0.33 7.43 6.80 12.53

 HUB 15.00 392.61 285.09 269.95 1068.05 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.76 300.90 142.46 0.28 4381.06 0.92 0.91

 MEAN 310.15 278.75 80.49 0.26 4143.35 0.92 0.91 0.91 1.43

 HUB 257.94 271.31 27.15 0.25 4277.17 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.60 493.94 1.03 484.70 479.74 24.58

 MEAN 7.04 1.08 6.54 493.28 1.02 483.35 479.51 25.76

 HUB 7.05 1.08 6.43 493.65 1.02 481.30 480.18 27.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.69 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.71 16.78 12.70 4.08 0.93 0.36 2.22

 HUB 46.56 -5.74 -9.30 3.56 0.93 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 366.8771 229.2169 286.4584 1069.7042 0.3430 -0.0590 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0483 6.5049 482.8518 480.0273 27.0384 38.6659 35.4000 -3.2659

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 289.2946 70.7703 280.5048 1074.1967 0.2693 0.3410 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0458 6.7043 486.9272 479.4550 554.9116 0.0148 0.4405

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 287.2021 0.0000 287.2021 1074.2843 0.2673 0.3522 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6963 487.0251 479.9786 0.0000 0.0600 0.0403 0.3260

NASA/TM—2013-218094 L–127
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8734 7.0323 1.0798 493.6248 11.7590 199.5773 1.5471

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73463.859 0.584 166.617 405263.000 0.182870E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.525 EfDer = 0.999 SH = 0.245864E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.134 1970.532 7.032 493.624 1.000 1.000 0.980

 W Kg/sec = 18.243 Wdry = 40.035 WH2O = 0.099 lbm/sec H2O = 1.471g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.841 2019.962 1.378 0.250 53.428 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64601.434 31460.652 2.461 590.487 239.920 468.502 1.953

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.56 -0.09 262.56 0.24 0.41 362.23

 MEAN 18.08 0.00 -0.02 262.56 -0.09 262.56 0.24 0.38

 HUB 15.21 0.00 -0.02 262.56 -0.09 262.56 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.40 46.36 7.04 353.38 440.32 6.75 488.12 481.64 34.83

 MEAN 49.82 42.30 7.52 310.88 406.98 6.75 488.12 481.64 34.83

 HUB 44.90 37.84 7.06 261.55 370.67 6.75 488.12 481.64 34.83

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.46 152.88 282.78 1081.76 0.30 2.33 2.04 9.02

 MEAN 18.01 328.01 164.28 283.90 1080.90 0.30 2.40 2.13 7.35

 HUB 15.22 354.54 210.64 285.19 1080.06 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.15 345.36 198.27 0.32 3123.63 0.92 0.91

 MEAN 309.70 318.98 145.42 0.30 2960.32 0.92 0.91 0.91 1.38

 HUB 261.78 289.74 51.14 0.27 3207.92 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.45 1.06 7.01 502.20 1.02 493.95 487.11 29.88

 MEAN 7.43 1.06 6.97 501.75 1.02 493.16 486.96 30.66

 HUB 7.46 1.06 6.93 502.43 1.02 492.40 487.67 31.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.40 35.04 31.50 3.54 0.93 0.34 1.40

 MEAN 30.06 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.45 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.9755 164.7415 320.0666 1079.3601 0.3335 -0.1624 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4396 6.8963 491.7876 487.6586 32.3412 27.2353 30.6000 3.3647

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 314.2495 66.6231 307.1060 1082.0542 0.2904 0.1037 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4375 7.0208 494.2476 487.1118 491.5697 0.0145 0.2601

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 325.4207 0.0000 325.4207 1081.4207 0.3009 0.1538 0.5911

NASA/TM—2013-218094 L–128
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9798 493.6784 487.4713 0.0000 0.0600 0.0405 0.0169

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8721 7.4252 1.0559 502.1259 8.5019 249.0451 1.9306

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 53287.559 0.432 120.857 373711.438 0.270516E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.622 EfDer = 0.996 SH = 0.301512E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.134 1970.532 7.425 502.125 1.000 1.000 0.980

 W Kg/sec = 18.243 Wdry = 40.013 WH2O = 0.121 lbm/sec H2O = 1.868g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.175 2002.790 1.377 0.251 53.446 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62396.902 31453.723 2.379 545.479 229.259 424.468 1.851

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 274.53 -0.09 274.53 0.25 0.41 350.77

 MEAN 17.74 0.00 -0.02 274.53 -0.09 274.53 0.25 0.38

 HUB 15.05 0.00 -0.02 274.53 -0.09 274.53 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.51 46.36 5.15 345.13 441.07 7.11 496.12 487.70 32.57

 MEAN 48.02 43.40 4.62 305.03 410.45 7.11 496.12 487.70 32.57

 HUB 43.32 38.84 4.48 258.80 377.35 7.11 496.12 487.70 32.57

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 324.01 131.75 296.02 1089.25 0.30 2.26 1.98 8.75

 MEAN 17.51 331.50 147.82 296.71 1088.76 0.30 2.34 2.07 6.78

 HUB 14.85 359.04 200.85 297.60 1088.29 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 340.66 362.30 208.90 0.33 2611.95 0.92 0.91

 MEAN 301.05 333.94 153.22 0.31 2589.53 0.92 0.91 0.91 1.32

 HUB 255.36 302.55 54.51 0.28 2984.09 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.78 1.05 7.33 509.28 1.01 500.92 492.16 29.02

 MEAN 7.78 1.05 7.30 509.22 1.01 500.47 492.23 29.44

 HUB 7.84 1.06 7.27 510.30 1.02 500.03 493.15 29.83

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.99 35.21 31.50 3.71 0.93 0.28 1.40

 MEAN 26.48 27.31 23.50 3.81 0.92 0.30 1.62

 HUB 34.02 10.38 6.50 3.88 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.8132 148.7919 334.1860 1087.0767 0.3365 -0.1751 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7945 7.2157 498.9445 493.0005 31.1323 24.0004 31.5000 7.4996

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 333.7638 72.8083 325.7257 1089.0181 0.3065 0.0087 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7895 7.3058 500.7307 492.5793 451.3937 0.0199 0.2182

 

NASA/TM—2013-218094 L–129
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 339.5275 0.0000 339.5275 1088.6744 0.3119 0.0989 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2729 500.4226 492.8669 0.0000 0.0600 0.0552 -0.0573

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8446 7.7720 1.0467 509.6017 7.4764 269.1685 2.0866

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46944.480 0.405 106.470 376437.906 0.328984E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 2.047 EfDer = 0.977 SH = 0.363597E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.134 1970.532 7.772 509.601 1.000 1.000 0.980

 W Kg/sec = 18.243 Wdry = 39.988 WH2O = 0.146 lbm/sec H2O = 2.318g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.241 1988.045 1.377 0.251 53.466 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60621.375 31445.980 2.325 513.330 220.741 395.845 1.793

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 283.42 -0.10 283.42 0.26 0.40 334.13

 MEAN 16.97 0.00 -0.02 283.42 -0.10 283.42 0.26 0.37

 HUB 14.32 0.00 -0.02 283.42 -0.10 283.42 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.45 46.36 3.09 331.20 435.98 7.42 503.21 492.98 31.13

 MEAN 45.85 43.80 2.05 291.83 406.88 7.42 503.21 492.98 31.13

 HUB 41.00 37.84 3.16 246.25 375.52 7.42 503.21 492.98 31.13

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.58 108.44 304.87 1095.60 0.30 2.16 1.89 8.34

 MEAN 16.57 330.44 126.53 305.26 1095.36 0.30 2.24 1.97 6.35

 HUB 13.89 356.09 182.33 305.86 1095.13 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.66 373.76 216.23 0.34 2049.18 0.92 0.89

 MEAN 285.01 343.94 158.47 0.31 2098.79 0.92 0.89 0.89 1.27

 HUB 238.85 311.04 56.52 0.28 2534.00 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.05 1.04 7.59 515.21 1.01 506.88 496.45 28.77

 MEAN 8.06 1.04 7.58 515.34 1.01 506.66 496.61 28.96

 HUB 8.12 1.05 7.56 516.53 1.01 506.45 497.54 29.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.58 35.35 31.50 3.85 0.93 0.23 1.40

 MEAN 22.51 27.44 23.50 3.94 0.91 0.25 1.62

 HUB 30.80 10.47 6.50 3.97 0.91 0.30 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.8514 127.2442 335.5342 1094.0339 0.3280 -0.1430 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0747 7.5040 505.4571 497.2836 30.2663 20.7682 32.4000 11.6318

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 341.8393 76.6646 333.1316 1095.0566 0.3122 -0.0539 2.2705

 

NASA/TM—2013-218094 L–130
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0659 7.5473 506.4053 497.0674 432.2457 0.0275 0.1816

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 339.5653 0.0000 339.5653 1095.1842 0.3101 0.0455 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5299 506.5293 497.2161 0.0000 0.0600 0.0784 -0.0882

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7796 8.0402 1.0345 515.6925 6.0913 308.9255 2.3948

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38322.410 0.364 86.916 390083.500 0.393754E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.340 EfDer = 0.945 SH = 0.432573E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.134 1970.532 8.040 515.692 1.000 1.000 0.980

 W Kg/sec = 18.243 Wdry = 39.960 WH2O = 0.174 lbm/sec H2O = 2.823g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.165 1976.270 1.376 0.252 53.489 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59239.266 31437.361 2.373 509.668 214.740 384.739 1.792

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 278.95 -0.10 278.95 0.25 0.38 315.94

 MEAN 15.91 0.00 -0.02 278.95 -0.10 278.95 0.25 0.36

 HUB 13.07 0.00 -0.02 278.95 -0.10 278.95 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.49 47.36 1.13 315.03 420.85 7.69 509.52 497.25 30.25

 MEAN 44.46 44.80 -0.34 273.64 390.82 7.69 509.52 497.25 30.25

 HUB 38.87 38.84 0.03 224.75 358.28 7.69 509.52 497.25 30.25

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.83 93.12 300.74 1101.42 0.29 2.05 1.78 7.43

 MEAN 15.50 320.16 108.79 301.11 1101.17 0.29 2.13 1.86 5.75

 HUB 12.59 341.67 160.32 301.72 1100.93 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 308.50 369.91 215.38 0.34 1672.38 0.92 0.86

 MEAN 266.50 339.91 157.71 0.31 1687.57 0.92 0.86 0.86 1.24

 HUB 216.50 306.90 56.18 0.28 2019.72 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.27 1.03 7.82 520.25 1.01 512.39 500.04 28.51

 MEAN 8.27 1.03 7.81 520.29 1.01 512.16 500.14 28.71

 HUB 8.32 1.03 7.79 521.20 1.01 511.94 500.86 28.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 17.20 35.61 31.50 4.11 0.93 0.20 1.40

 MEAN 19.87 27.64 23.50 4.14 0.90 0.21 1.64

 HUB 27.98 10.55 6.50 4.05 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.945 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.3436 110.7889 343.9404 1099.0638 0.3288 -0.2470 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2746 7.6874 510.2247 500.9914 30.5644 17.8546 33.0000 15.1454

 

NASA/TM—2013-218094 L–131
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 357.1410 81.5535 347.7049 1099.3193 0.3249 -0.2636 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2498 7.6774 510.4634 500.9259 410.5396 0.0716 0.1494

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 347.4427 0.0000 347.4427 1099.8933 0.3159 0.0113 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6941 511.0008 500.9147 0.0000 0.0600 0.1016 -0.2289

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6939 8.2354 1.0243 520.5743 4.8914 359.4349 2.7863

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30837.957 0.324 69.941 413430.375 0.460042E-02

 

Melt Ratio at Stator LE, Throat, TE

0.12660E+00 0.14421E+00 0.20672E+00

 trTOT = 1.0803 Tt4 = 520.5743 T1 = 481.8665

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 242856.27 550.8001 87.3096 1.2645 0.8262 9.3556 1.0803 37.3740

NASA/TM—2013-218094 L–132
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.755 EfDer = 0.999 SH = 0.169853E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.544 1803.324 7.939 496.981 1.000 1.000 0.980

 W Kg/sec = 22.520 Wdry = 49.460 WH2O = 0.084 lbm/sec H2O = 1.154g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 89.793 1842.304 1.379 0.250 53.403 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70228.852 38848.563 3.160 831.557 263.127 619.754 2.355

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.69 -0.07 202.69 0.19 0.35 331.66

 MEAN 17.06 0.00 -0.02 202.69 -0.07 202.69 0.19 0.31

 HUB 12.51 0.00 -0.02 202.69 -0.07 202.69 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.03 50.47 7.56 324.65 382.79 7.75 493.70 482.11 22.04

 MEAN 52.96 47.20 5.76 268.47 336.45 7.75 493.70 482.11 22.04

 HUB 44.18 38.62 5.56 196.87 282.61 7.75 493.70 482.11 22.04

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.64 173.93 280.02 1085.54 0.30 7.29 6.52 16.04

 MEAN 18.04 344.37 198.77 281.21 1084.67 0.32 7.43 6.80 12.53

 HUB 15.00 387.81 264.34 283.76 1082.93 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.65 318.00 150.72 0.29 3589.69 0.92 0.91

 MEAN 283.83 293.79 85.06 0.27 3586.20 0.92 0.91 0.91 1.28

 HUB 236.05 285.17 28.28 0.26 3965.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.91 506.02 1.02 497.33 489.19 24.23

 MEAN 8.43 1.06 7.87 506.01 1.02 496.52 489.35 24.86

 HUB 8.48 1.07 7.77 506.97 1.02 494.94 490.38 26.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.85 28.29 24.20 4.09 0.93 0.30 1.80

 MEAN 35.25 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.97 -5.69 -9.30 3.61 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.3418 198.3833 302.0132 1083.9147 0.3334 -0.0731 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4412 7.8250 495.9005 489.9069 26.1308 33.2997 35.4000 2.1003

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.0393 75.1112 297.7103 1087.0670 0.2824 0.2332 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4391 7.9909 498.8011 489.4860 554.9116 0.0136 0.3529

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 304.7411 0.0000 304.7411 1087.1741 0.2803 0.2574 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9836 498.9149 490.0158 0.0000 0.0600 0.0381 0.2211

NASA/TM—2013-218094 L–133
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8726 8.4245 1.0611 506.3303 9.3494 221.5003 1.7171

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58525.770 0.555 163.858 489423.188 0.244646E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.326 EfDer = 0.988 SH = 0.317409E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.544 1803.324 8.425 506.330 1.000 1.000 0.980

 W Kg/sec = 22.520 Wdry = 49.387 WH2O = 0.157 lbm/sec H2O = 2.211g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.412 1825.219 1.377 0.251 53.451 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68509.297 38825.906 2.357 590.487 250.504 468.502 1.870

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.44 -0.10 278.44 0.26 0.39 327.31

 MEAN 18.08 0.00 -0.02 278.44 -0.10 278.44 0.26 0.37

 HUB 15.21 0.00 -0.02 278.44 -0.10 278.44 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.28 46.36 2.92 323.39 426.82 8.06 500.16 491.70 33.18

 MEAN 45.63 42.30 3.33 284.50 398.15 8.06 500.16 491.70 33.18

 HUB 40.70 37.84 2.86 239.36 367.24 8.06 500.16 491.70 33.18

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.03 107.92 303.40 1092.11 0.29 2.33 2.04 9.02

 MEAN 18.01 329.27 127.22 303.70 1091.94 0.30 2.40 2.13 7.35

 HUB 15.22 355.71 184.35 304.21 1091.78 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.35 370.95 213.43 0.34 2205.75 0.92 0.90 

 MEAN 283.42 341.52 156.21 0.31 2292.90 0.92 0.90 0.90 1.25

 HUB 239.56 309.18 55.21 0.28 2807.82 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.23 511.86 1.01 503.60 495.30 30.89

 MEAN 8.74 1.04 8.22 512.08 1.01 503.44 495.50 31.03

 HUB 8.82 1.05 8.20 513.37 1.01 503.29 496.51 31.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.58 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.73 27.22 23.50 3.72 0.92 0.24 1.63

 HUB 31.22 10.29 6.50 3.79 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.8259 127.5736 342.8608 1090.1106 0.3356 -0.1929 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7592 8.1123 501.7816 496.3091 32.9303 20.4095 30.6000 10.1905

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 338.5861 71.7827 330.8894 1091.7673 0.3101 -0.0385 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7510 8.1951 503.3093 495.9384 491.5697 0.0250 0.1650

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 351.2381 0.0000 351.2381 1091.0072 0.3219 0.0292 0.5911

NASA/TM—2013-218094 L–134
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1311 502.6158 496.3303 0.0000 0.0600 0.0696 -0.1551

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8035 8.7265 1.0358 512.4332 6.1035 300.3931 2.3286

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38347.086 0.371 107.363 454118.906 0.344813E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.040 EfDer = 0.949 SH = 0.378004E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.544 1803.324 8.727 512.433 1.000 1.000 0.980

 W Kg/sec = 22.520 Wdry = 49.357 WH2O = 0.187 lbm/sec H2O = 2.684g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.952 1814.317 1.376 0.251 53.471 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67212.094 38816.574 2.241 545.479 243.387 424.468 1.744

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 295.71 -0.10 295.71 0.27 0.40 317.76

 MEAN 17.74 0.00 -0.02 295.71 -0.10 295.71 0.27 0.37

 HUB 15.05 0.00 -0.02 295.71 -0.10 295.71 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.89 46.36 0.53 315.84 432.74 8.30 505.48 496.36 33.20

 MEAN 43.36 43.40 -0.04 279.15 406.73 8.30 505.48 496.36 33.20

 HUB 38.70 38.84 -0.14 236.84 378.93 8.30 505.48 496.36 33.20

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.51 82.79 323.07 1096.44 0.30 2.26 1.98 8.75

 MEAN 17.51 340.36 107.82 322.83 1096.71 0.31 2.34 2.07 6.78

 HUB 14.85 366.63 173.61 322.92 1096.98 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 311.75 395.98 228.96 0.36 1642.02 0.92 0.87 

 MEAN 275.50 363.78 167.68 0.33 1889.39 0.92 0.87 0.87 1.19

 HUB 233.69 328.46 60.08 0.30 2579.66 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.95 1.03 8.40 516.54 1.01 507.70 499.13 32.00

 MEAN 8.98 1.03 8.41 517.16 1.01 507.95 499.51 31.74

 HUB 9.08 1.04 8.42 518.89 1.01 508.20 500.72 31.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.37 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.47 27.45 23.50 3.95 0.90 0.19 1.62

 HUB 28.26 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.949 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.1600 108.5289 364.3392 1094.6271 0.3473 -0.2072 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9995 8.2904 506.0463 500.4437 33.8491 16.5877 31.5000 14.9123

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 366.1744 79.8785 357.3558 1095.5232 0.3342 -0.1439 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9833 8.3252 506.8761 500.2269 451.3937 0.0372 0.1204

 

NASA/TM—2013-218094 L–135
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 373.4313 0.0000 373.4313 1095.0568 0.3410 -0.0356 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2652 506.4501 500.5120 0.0000 0.0600 0.1000 -0.2449

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6851 8.9460 1.0251 517.5267 5.0952 340.2122 2.6373

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 32072.021 0.330 89.794 459914.469 0.405663E-02

 

Melt Ratio at Stator LE, Throat, TE

0.16151E-01 0.17292E-01 0.26269E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.111 EfDer = 0.892 SH = 0.435799E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.544 1803.324 8.946 517.525 1.000 1.000 0.980

 W Kg/sec = 22.520 Wdry = 49.328 WH2O = 0.216 lbm/sec H2O = 3.129g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.318 1805.367 1.376 0.252 53.490 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66464.922 38807.652 2.151 513.330 238.680 395.845 1.658

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 310.74 -0.11 310.74 0.28 0.40 303.43

 MEAN 16.97 0.00 -0.02 310.74 -0.11 310.74 0.28 0.37

 HUB 14.32 0.00 -0.02 310.74 -0.11 310.74 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.30 46.36 -2.06 303.09 434.15 8.47 509.86 500.18 33.13

 MEAN 40.69 43.80 -3.11 267.07 409.81 8.47 509.86 500.18 33.13

 HUB 35.96 37.84 -1.88 225.35 383.92 8.47 509.86 500.18 33.13

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 343.37 55.62 338.83 1099.68 0.31 2.16 1.89 8.34

 MEAN 16.57 348.50 84.14 338.19 1100.30 0.32 2.24 1.97 6.35

 HUB 13.89 371.94 155.16 338.03 1100.90 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 297.11 416.09 241.49 0.38 1052.17 0.92 0.82 

 MEAN 260.82 381.56 176.69 0.35 1396.28 0.92 0.82 0.82 1.14

 HUB 218.59 343.93 63.42 0.31 2156.77 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.08 1.02 8.50 520.15 1.01 510.79 502.08 32.85

 MEAN 9.13 1.02 8.52 521.01 1.01 511.37 502.53 32.25

 HUB 9.23 1.03 8.54 522.91 1.01 511.93 503.75 31.64

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.32 35.48 31.50 3.98 0.93 0.09 1.40

 MEAN 13.97 27.58 23.50 4.08 0.89 0.13 1.62

 HUB 24.66 10.63 6.50 4.13 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.892 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.0425 84.6097 372.5556 1098.5599 0.3478 -0.1702 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1392 8.4176 509.7738 503.3492 33.9480 12.7952 32.4000 19.6048

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 382.0393 85.6803 372.3076 1098.5577 0.3478 -0.1992 2.2705

 

NASA/TM—2013-218094 L–136
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1153 8.3953 509.7721 503.3513 432.2457 0.0482 0.0841

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 380.4358 0.0000 380.4358 1098.6517 0.3463 -0.0871 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3547 509.8616 503.3715 0.0000 0.0600 0.1293 -0.2641

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4886 9.0646 1.0133 521.3394 3.8286 418.6752 3.2455

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 24139.064 0.273 67.584 479193.344 0.456085E-02

 

Melt Ratio at Stator LE, Throat, TE

0.25610E+00 0.28268E+00 0.36453E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.963 EfDer = 0.829 SH = 0.478536E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.544 1803.324 9.065 521.334 1.000 1.000 0.980

 W Kg/sec = 22.520 Wdry = 49.307 WH2O = 0.237 lbm/sec H2O = 3.455g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.549 1798.753 1.375 0.252 53.504 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66083.703 38801.051 2.155 509.668 236.486 384.739 1.627

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 311.18 -0.11 311.18 0.28 0.38 287.56

 MEAN 15.91 0.00 -0.02 311.18 -0.11 311.18 0.28 0.36

 HUB 13.07 0.00 -0.02 311.18 -0.11 311.18 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.83 47.36 -4.53 288.30 424.28 8.59 513.66 502.65 32.05

 MEAN 38.84 44.80 -5.96 250.42 399.50 8.59 513.66 502.65 32.05

 HUB 33.48 38.84 -5.36 205.68 373.07 8.59 513.66 502.65 32.05

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 341.95 37.59 339.87 1102.78 0.31 2.05 1.78 7.43

 MEAN 15.50 345.39 64.99 339.22 1103.47 0.31 2.13 1.86 5.75

 HUB 12.59 364.58 133.87 339.11 1104.12 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.32 418.82 244.73 0.38 676.38 0.92 0.76 

 MEAN 243.89 383.50 178.90 0.35 1008.89 0.92 0.76 0.76 1.11

 HUB 198.13 345.14 64.26 0.31 1686.85 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.15 1.01 8.57 523.01 1.00 513.75 504.02 32.37

 MEAN 9.19 1.01 8.59 523.84 1.00 514.39 504.42 31.72

 HUB 9.27 1.02 8.61 525.53 1.01 515.00 505.45 31.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.31 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.85 27.81 23.50 4.31 0.87 0.09 1.64

 HUB 21.54 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.829 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 394.5000 66.1812 388.9091 1100.6702 0.3584 -0.2824 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1883 8.4204 511.7955 505.5193 34.2999 9.6576 33.0000 23.3424

 

NASA/TM—2013-218094 L–137
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 407.3193 93.0117 396.5575 1099.7925 0.3704 -0.4383 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1327 8.3202 510.9776 505.7370 410.5396 0.1108 0.0567

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 396.0731 0.0000 396.0731 1100.5503 0.3599 -0.0984 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3448 511.6821 505.5550 0.0000 0.0600 0.1442 -0.3981

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2692 9.1123 1.0053 524.1083 2.7950 528.1127 4.0939

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17643.760 0.221 49.398 510167.125 0.494053E-02

 

Melt Ratio at Stator LE, Throat, TE

0.67036E+00 0.70109E+00 0.78808E+00

 trTOT = 1.0546 Tt4 = 524.1083 T1 = 496.9814

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 170727.72 477.9974 89.7930 1.1478 0.7034 5.7554 1.0546 37.3740

NASA/TM—2013-218094 L–138
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 7.073 EfDer = 1.000 SH = 0.245223E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.846 1587.053 9.337 510.164 1.000 1.000 0.980

 W Kg/sec = 21.748 Wdry = 47.729 WH2O = 0.117 lbm/sec H2O = 1.919g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.704 1600.275 1.378 0.250 53.428 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58898.695 37506.266 3.797 831.557 219.020 619.754 2.830

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 169.99 -0.06 169.99 0.15 0.30 288.09

 MEAN 17.06 0.00 -0.02 169.99 -0.06 169.99 0.15 0.27

 HUB 12.51 0.00 -0.02 169.99 -0.06 169.99 0.15 0.22

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.25 50.47 8.78 285.72 332.51 9.18 507.86 492.10 21.78

 MEAN 54.27 47.20 7.07 236.28 291.12 9.18 507.86 492.10 21.78

 HUB 45.56 38.62 6.94 173.26 242.77 9.18 507.86 492.10 21.78

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 284.14 159.31 235.28 1100.18 0.26 7.29 6.52 16.04

 MEAN 18.04 296.04 178.58 236.11 1099.43 0.27 7.43 6.80 12.53

 HUB 15.00 331.86 231.57 237.71 1098.10 0.30 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 285.72 267.09 126.41 0.24 3287.70 0.92 0.91

 MEAN 249.79 246.61 71.21 0.22 3221.89 0.92 0.91 0.91 1.33

 HUB 207.74 238.90 23.82 0.22 3474.26 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.35 517.43 1.01 510.99 498.12 24.62

 MEAN 9.78 1.05 9.31 517.28 1.01 510.29 498.17 25.14

 HUB 9.81 1.05 9.22 517.84 1.02 509.06 498.87 26.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.10 28.25 24.20 4.05 0.93 0.33 1.80

 MEAN 37.10 16.78 12.70 4.08 0.93 0.29 2.22

 HUB 44.25 -5.72 -9.30 3.58 0.93 0.19 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 309.6745 178.2341 253.2408 1098.8798 0.2818 -0.0679 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7888 9.2716 509.8752 498.6780 26.2407 35.1384 35.4000 0.2616

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 258.2882 63.1852 250.4405 1101.3585 0.2345 0.2655 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7882 9.4255 512.1942 498.3391 554.9116 0.0111 0.3783

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 256.2574 0.0000 256.2574 1101.3970 0.2327 0.2861 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4196 512.2477 498.8725 0.0000 0.0600 0.0366 0.2535

NASA/TM—2013-218094 L–139
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8815 9.7754 1.0469 517.4745 7.3530 213.2685 1.6532

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46170.113 0.566 124.836 461131.063 0.348744E-02

 

Melt Ratio at Stator LE, Throat, TE

0.13401E+00 0.21349E+00 0.51755E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.569 EfDer = 0.995 SH = 0.420435E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.846 1587.053 9.775 517.456 1.000 1.000 0.980

 W Kg/sec = 21.748 Wdry = 47.645 WH2O = 0.201 lbm/sec H2O = 3.356g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.865 1588.931 1.376 0.252 53.485 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57730.176 37480.219 2.800 590.487 210.908 468.502 2.221

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 234.63 -0.08 234.63 0.21 0.33 284.94

 MEAN 18.08 0.00 -0.02 234.63 -0.08 234.63 0.21 0.31

 HUB 15.21 0.00 -0.02 234.63 -0.08 234.63 0.21 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.51 46.36 4.15 284.61 368.92 9.48 513.09 500.30 31.74

 MEAN 46.87 42.30 4.57 250.38 343.19 9.48 513.09 500.30 31.74

 HUB 41.93 37.84 4.09 210.65 315.37 9.48 513.09 500.30 31.74

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 276.12 102.93 256.22 1105.28 0.25 2.33 2.04 9.02

 MEAN 18.01 282.28 117.78 256.53 1105.04 0.26 2.40 2.13 7.35

 HUB 15.22 305.10 164.51 256.96 1104.80 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.81 313.05 179.88 0.28 2103.52 0.92 0.91

 MEAN 249.43 288.33 131.65 0.26 2122.76 0.92 0.91 0.91 1.28

 HUB 210.83 261.10 46.33 0.24 2505.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.07 1.03 9.65 522.07 1.01 516.02 503.13 29.71

 MEAN 10.07 1.03 9.63 522.11 1.01 515.79 503.22 29.91

 HUB 10.13 1.04 9.61 522.95 1.01 515.56 503.91 30.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 21.89 35.07 31.50 3.57 0.93 0.25 1.40

 MEAN 24.66 27.17 23.50 3.67 0.92 0.27 1.63

 HUB 32.63 10.22 6.50 3.72 0.92 0.30 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 311.9026 118.1153 288.6729 1103.7985 0.2826 -0.1811 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0843 9.5493 514.6487 503.7908 31.0624 22.2527 30.6000 8.3473

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 285.3728 60.5011 278.8857 1105.1425 0.2582 0.0001 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0807 9.6309 515.9049 503.5178 491.5697 0.0180 0.1888

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 295.3691 0.0000 295.3691 1104.6409 0.2674 0.0612 0.5911

NASA/TM—2013-218094 L–140
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5820 515.4451 503.9475 0.0000 0.0600 0.0594 -0.1066

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8336 10.0617 1.0293 522.3655 4.9195 284.6049 2.2062

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31006.822 0.388 83.837 427455.594 0.451050E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 1.117 EfDer = 0.966 SH = 0.504098E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.846 1587.053 10.062 522.365 1.000 1.000 0.980

 W Kg/sec = 21.748 Wdry = 47.605 WH2O = 0.241 lbm/sec H2O = 4.089g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.149 1581.475 1.375 0.252 53.512 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56808.297 37467.727 2.648 545.479 205.984 424.468 2.061

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.93 -0.09 249.93 0.23 0.34 276.98

 MEAN 17.74 0.00 -0.02 249.93 -0.09 249.93 0.23 0.32

 HUB 15.05 0.00 -0.02 249.93 -0.09 249.93 0.23 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.05 46.36 1.69 277.96 373.87 9.72 517.42 504.51 33.34

 MEAN 44.52 43.40 1.12 245.67 350.52 9.72 517.42 504.51 33.34

 HUB 39.84 38.84 1.00 208.44 325.50 9.72 517.42 504.51 33.34

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 284.88 81.09 273.10 1108.83 0.26 2.26 1.98 8.75

 MEAN 17.51 291.13 100.92 273.08 1108.90 0.26 2.34 2.07 6.78

 HUB 14.85 314.22 155.15 273.24 1108.98 0.28 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 274.36 334.57 193.27 0.30 1608.20 0.92 0.88

 MEAN 242.46 307.58 141.54 0.28 1768.28 0.92 0.88 0.88 1.22

 HUB 205.67 277.87 50.52 0.25 2305.27 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.28 1.02 9.83 525.89 1.01 519.47 506.98 32.68

 MEAN 10.31 1.02 9.83 526.24 1.01 519.53 507.22 32.61

 HUB 10.38 1.03 9.83 527.42 1.01 519.60 508.08 32.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.54 35.29 31.50 3.79 0.93 0.18 1.40

 MEAN 20.28 27.40 23.50 3.90 0.91 0.21 1.62

 HUB 29.59 10.47 6.50 3.97 0.91 0.27 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.966 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 323.4599 101.5817 307.0952 1107.4856 0.2921 -0.1954 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3186 9.7356 518.2404 507.9443 34.1216 18.3033 31.5000 13.1967

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 308.5057 67.2984 301.0759 1108.2802 0.2784 -0.1034 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3098 9.7790 518.9890 507.7847 451.3937 0.0277 0.1423

 

NASA/TM—2013-218094 L–141
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 313.9640 0.0000 313.9640 1107.9855 0.2834 -0.0062 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7320 518.7213 508.1333 0.0000 0.0600 0.0885 -0.1986

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7367 10.2798 1.0217 526.5173 4.1526 319.8939 2.4798

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 26249.061 0.349 70.973 433412.281 0.549576E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-1.984 EfDer = 0.915 SH = 0.604830E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.846 1587.053 10.280 526.516 1.000 1.000 0.980

 W Kg/sec = 21.748 Wdry = 47.557 WH2O = 0.289 lbm/sec H2O = 4.958g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.933 1575.227 1.373 0.253 53.544 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56218.652 37452.648 2.534 513.330 202.538 395.845 1.954

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 262.83 -0.09 262.83 0.24 0.34 264.75

 MEAN 16.97 0.00 -0.02 262.83 -0.09 262.83 0.24 0.32

 HUB 14.32 0.00 -0.02 262.83 -0.09 262.83 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 45.43 46.36 -0.93 266.74 374.54 9.89 521.06 508.48 35.76

 MEAN 41.82 43.80 -1.98 235.04 352.65 9.89 521.06 508.48 35.76

 HUB 37.05 37.84 -0.79 198.33 329.32 9.89 521.06 508.48 35.76

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 291.92 57.76 286.15 1111.56 0.26 2.16 1.89 8.34

 MEAN 16.57 296.98 80.39 285.89 1111.87 0.27 2.24 1.97 6.35

 HUB 13.89 317.83 138.88 285.88 1112.18 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 261.48 351.26 203.73 0.32 1092.17 0.92 0.84

 MEAN 229.54 322.46 149.15 0.29 1333.99 0.92 0.84 0.84 1.16

 HUB 192.37 290.84 53.49 0.26 1930.35 0.92 0.84

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.42 1.01 9.94 528.90 1.00 522.18 510.35 35.84

 MEAN 10.46 1.02 9.96 529.43 1.01 522.47 510.65 35.52

 HUB 10.54 1.02 9.97 530.74 1.01 522.76 511.53 35.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 11.41 35.45 31.50 3.95 0.93 0.12 1.40

 MEAN 15.71 27.55 23.50 4.05 0.89 0.16 1.62

 HUB 25.91 10.60 6.50 4.10 0.89 0.22 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.915 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 324.2214 80.8469 313.9798 1110.6949 0.2919 -0.1608 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4668 9.8766 521.4001 511.3280 36.8827 14.4395 32.4000 17.9605

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 321.3166 72.0619 313.1317 1110.8480 0.2893 -0.1610 2.2705

 

NASA/TM—2013-218094 L–142
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4527 9.8735 521.5491 511.3484 432.2457 0.0375 0.1044

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 319.5206 0.0000 319.5206 1110.9382 0.2876 -0.0624 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8397 521.6409 511.5417 0.0000 0.0600 0.1198 -0.2266

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5689 10.4102 1.0127 529.6908 3.1744 388.3673 3.0106

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 20126.895 0.294 54.420 451947.313 0.652204E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-4.839 EfDer = 0.854 SH = 0.711818E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.846 1587.053 10.410 529.690 1.000 1.000 0.980

 W Kg/sec = 21.748 Wdry = 47.506 WH2O = 0.341 lbm/sec H2O = 5.870g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.274 1570.501 1.372 0.254 53.579 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55879.762 37436.582 2.539 509.668 200.733 384.739 1.917

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 263.12 -0.09 263.12 0.24 0.33 251.07

 MEAN 15.91 0.00 -0.02 263.12 -0.09 263.12 0.24 0.31

 HUB 13.07 0.00 -0.02 263.12 -0.09 263.12 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.97 47.36 -3.39 253.73 365.59 10.02 524.24 511.73 38.12

 MEAN 39.96 44.80 -4.84 220.39 343.29 10.02 524.24 511.73 38.12

 HUB 34.54 38.84 -4.30 181.01 319.43 10.02 524.24 511.73 38.12

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 289.80 42.23 286.70 1114.11 0.26 2.05 1.78 7.43

 MEAN 15.50 293.45 63.80 286.43 1114.47 0.26 2.13 1.86 5.75

 HUB 12.59 310.68 120.30 286.45 1114.82 0.28 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 248.46 353.17 206.23 0.32 759.25 0.92 0.78

 MEAN 214.64 323.72 150.83 0.29 990.22 0.92 0.78 0.78 1.13

 HUB 174.37 291.50 54.07 0.26 1515.72 0.92 0.78

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.50 1.01 10.03 531.34 1.00 524.74 513.27 38.79

 MEAN 10.53 1.01 10.05 531.85 1.00 525.07 513.52 38.40

 HUB 10.60 1.02 10.05 532.99 1.01 525.40 514.27 37.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.38 35.73 31.50 4.23 0.93 0.07 1.40

 MEAN 12.56 27.77 23.50 4.27 0.88 0.11 1.64

 HUB 22.78 10.69 6.50 4.19 0.88 0.18 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.854 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 333.1611 64.9721 326.7644 1112.5869 0.2994 -0.2689 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5351 9.9116 523.3356 514.4630 40.5587 11.2457 33.0000 21.7543

 

NASA/TM—2013-218094 L–143
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 340.5151 77.7569 331.5183 1112.1692 0.3062 -0.3811 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.5003 9.8519 522.9477 514.6550 410.5396 0.0894 0.0751

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 331.6349 0.0000 331.6349 1112.6626 0.2981 -0.0814 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8609 523.4179 514.7097 0.0000 0.0600 0.1393 -0.3631

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3769 10.4752 1.0062 532.0616 2.3716 480.6592 3.7260

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 15085.707 0.244 40.789 481864.000 0.762031E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0429 Tt4 = 532.0616 T1 = 510.1643

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 138638.59 374.8555 74.7042 1.1219 0.7411 7.0734 1.0429 37.3740

NASA/TM—2013-218094 L–144
 5μm, 4g/m3

, ISA +27R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.682 EfDer = 0.953 SH = 0.148360E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.148 2453.875 4.265 467.813 1.000 1.000 0.980

 W Kg/sec = 11.886 Wdry = 26.109 WH2O = 0.039 lbm/sec H2O = 0.576g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.599 2583.841 1.380 0.249 53.396 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64836.375 20505.209 3.316 831.557 250.770 619.754 2.471

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 187.13 -0.06 187.13 0.18 0.46 465.16

 MEAN 17.06 0.00 -0.02 187.13 -0.06 187.13 0.18 0.39

 HUB 12.51 0.00 -0.02 187.13 -0.06 187.13 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.05 50.47 16.58 441.77 479.83 4.17 465.01 459.55 35.37

 MEAN 62.88 47.20 15.68 365.33 410.52 4.17 465.01 459.55 35.37

 HUB 55.07 38.62 16.45 267.89 326.83 4.17 465.01 459.55 35.37

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 395.36 306.05 250.28 1063.28 0.37 7.29 6.52 16.04

 MEAN 18.04 399.63 308.82 253.63 1060.13 0.38 7.43 6.80 12.53

 HUB 15.00 432.18 346.55 258.24 1056.27 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 441.77 284.71 135.72 0.27 6315.20 0.92 0.87

 MEAN 386.23 265.18 77.40 0.25 5571.07 0.92 0.87 0.87 1.78

 HUB 321.21 259.48 25.33 0.25 5198.99 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.92 1.15 4.48 489.48 1.05 476.96 475.94 32.23

 MEAN 4.84 1.14 4.40 486.92 1.04 474.13 474.75 35.75

 HUB 4.80 1.13 4.29 485.65 1.04 470.69 474.75 40.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.72 28.47 24.20 4.27 0.93 0.58 1.80

 MEAN 50.60 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.31 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 411.1591 308.2248 272.1199 1059.6775 0.3880 -0.0352 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8517 4.3797 473.8361 475.4472 37.4606 48.5599 35.4000 -13.1599

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 269.8859 66.0223 261.6858 1068.2133 0.2527 0.5209 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8391 4.6320 481.5273 473.8109 554.9116 0.0367 0.6141

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 268.8453 0.0000 268.8453 1068.2122 0.2517 0.4890 1.3089

NASA/TM—2013-218094 L–145
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6105 481.5745 475.0002 0.0000 0.0600 0.0883 0.4751

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8108 4.8150 1.1291 487.3473 19.5370 166.7141 1.2924

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 122214.727 0.626 180.592 269875.188 0.280082E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.262 EfDer = 0.956 SH = 0.415892E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.148 2453.875 4.815 487.345 1.000 1.000 0.980

 W Kg/sec = 11.886 Wdry = 26.039 WH2O = 0.109 lbm/sec H2O = 1.730g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.379 2531.578 1.376 0.251 53.483 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 60553.738 20483.504 2.601 590.487 227.056 468.502 2.063

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 246.09 -0.08 246.09 0.23 0.47 453.98

 MEAN 18.08 0.00 -0.02 246.09 -0.08 246.09 0.23 0.43

 HUB 15.21 0.00 -0.02 246.09 -0.08 246.09 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.79 46.36 14.43 440.06 504.27 4.64 482.53 478.28 51.12

 MEAN 57.56 42.30 15.26 387.13 458.80 4.64 482.53 478.28 51.12

 HUB 52.93 37.84 15.09 325.71 408.29 4.64 482.53 478.28 51.12

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 363.61 255.28 258.94 1082.25 0.34 2.33 2.04 9.02

 MEAN 18.01 362.83 251.41 261.61 1079.75 0.34 2.40 2.13 7.35

 HUB 15.22 384.10 278.44 264.57 1077.29 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 437.28 316.50 182.00 0.29 5214.53 0.92 0.87

 MEAN 385.67 294.04 134.25 0.27 4529.48 0.92 0.87 0.87 1.72

 HUB 325.99 268.81 47.54 0.25 4240.05 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.12 5.00 505.09 1.04 494.58 488.77 35.58

 MEAN 5.32 1.10 4.93 502.75 1.03 492.30 487.79 38.41

 HUB 5.29 1.10 4.85 501.77 1.03 490.05 487.86 41.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.59 35.10 31.50 3.60 0.93 0.55 1.40

 MEAN 43.86 27.17 23.50 3.67 0.95 0.53 1.63

 HUB 46.46 10.19 6.50 3.69 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 387.6767 252.1191 294.4982 1078.5642 0.3594 -0.1052 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3317 4.8835 491.2748 488.6242 40.0864 40.5667 30.6000 -9.9667

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 284.7268 60.3641 278.2544 1084.5680 0.2625 0.3765 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3250 5.0800 496.7690 486.8398 491.5697 0.0263 0.4718

 

NASA/TM—2013-218094 L–146
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 295.1822 0.0000 295.1822 1084.0194 0.2723 0.3618 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0457 496.2895 487.4977 0.0000 0.0600 0.0682 0.2929

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8284 5.3078 1.1024 503.2021 15.8580 187.3870 1.4526

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 99913.039 0.523 147.637 245278.422 0.476442E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.283 EfDer = 0.972 SH = 0.561307E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.148 2453.875 5.308 503.201 1.000 1.000 0.980

 W Kg/sec = 11.886 Wdry = 26.001 WH2O = 0.147 lbm/sec H2O = 2.490g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.327 2491.376 1.374 0.253 53.530 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 56765.191 20471.631 2.604 545.479 209.496 424.468 2.026

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.74 -0.09 249.74 0.23 0.46 436.34

 MEAN 17.74 0.00 -0.02 249.74 -0.09 249.74 0.23 0.42

 HUB 15.05 0.00 -0.02 249.74 -0.09 249.74 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.84 46.36 13.48 429.78 497.15 5.12 498.27 488.62 40.14

 MEAN 56.68 43.40 13.28 379.85 454.67 5.12 498.27 488.62 40.14

 HUB 52.23 38.84 13.39 322.28 407.79 5.12 498.27 488.62 40.14

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 355.25 239.14 262.70 1097.93 0.32 2.26 1.98 8.75

 MEAN 17.51 356.51 238.42 265.06 1095.79 0.33 2.34 2.07 6.78

 HUB 14.85 379.79 269.44 267.67 1093.69 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 424.21 321.34 185.07 0.29 4739.18 0.92 0.89

 MEAN 374.89 298.13 136.47 0.27 4175.42 0.92 0.89 0.89 1.67

 HUB 318.00 272.04 48.56 0.25 4002.46 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.88 1.11 5.48 519.25 1.03 509.27 497.55 30.01

 MEAN 5.81 1.09 5.41 517.34 1.03 507.29 496.86 31.90

 HUB 5.79 1.09 5.33 516.76 1.03 505.35 497.16 33.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 42.31 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.97 27.24 23.50 3.74 0.94 0.51 1.62

 HUB 45.19 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 382.5519 239.9835 297.9159 1094.5707 0.3495 -0.1132 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8233 5.3596 506.2228 497.7233 33.2898 38.8529 31.5000 -7.3529

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 292.9572 63.9066 285.9018 1099.7161 0.2664 0.3266 2.3726

 

NASA/TM—2013-218094 L–147
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8189 5.5438 511.0037 496.1510 451.3937 0.0204 0.4467

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 297.9671 0.0000 297.9671 1099.4454 0.2710 0.3477 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5208 510.7719 496.7731 0.0000 0.0600 0.0545 0.2721

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8495 5.8045 1.0936 517.7809 14.5810 192.5233 1.4924

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92313.570 0.513 136.408 243885.156 0.644717E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.703 EfDer = 0.982 SH = 0.745601E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.148 2453.875 5.805 517.776 1.000 1.000 0.980

 W Kg/sec = 11.886 Wdry = 25.953 WH2O = 0.195 lbm/sec H2O = 3.514g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.162 2456.052 1.372 0.254 53.590 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53432.551 20456.510 2.639 513.330 194.544 395.845 2.035 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 249.80 -0.09 249.80 0.23 0.44 412.79

 MEAN 16.97 0.00 -0.02 249.80 -0.09 249.80 0.23 0.40

 HUB 14.32 0.00 -0.02 249.80 -0.09 249.80 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.80 46.36 12.44 412.44 482.26 5.60 512.87 497.80 33.56

 MEAN 55.50 43.80 11.70 363.41 441.06 5.60 512.87 497.80 33.56

 HUB 50.84 37.84 13.00 306.65 395.58 5.60 512.87 497.80 33.56

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 341.76 219.44 262.00 1111.83 0.31 2.16 1.89 8.34

 MEAN 16.57 342.99 218.82 264.13 1109.90 0.31 2.24 1.97 6.35

 HUB 13.89 364.83 249.20 266.46 1108.01 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.30 320.64 184.85 0.29 4144.78 0.92 0.90

 MEAN 354.91 297.13 136.10 0.27 3628.10 0.92 0.90 0.90 1.63

 HUB 297.44 270.79 48.24 0.24 3462.64 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.34 1.09 5.95 531.72 1.03 522.53 504.87 25.98

 MEAN 6.27 1.08 5.88 529.98 1.02 520.73 504.29 27.37

 HUB 6.25 1.08 5.81 529.42 1.02 518.96 504.56 28.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.95 35.21 31.50 3.71 0.93 0.50 1.40

 MEAN 39.64 27.26 23.50 3.76 0.94 0.48 1.62

 HUB 43.08 10.26 6.50 3.76 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.982 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 363.7563 220.0472 289.6513 1109.0475 0.3280 -0.0896 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2825 5.8399 519.9660 504.9283 28.1198 37.2238 32.4000 -4.8238

 

NASA/TM—2013-218094 L–148
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 290.7170 65.1993 283.3115 1113.0216 0.2612 0.2870 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2802 5.9937 523.7067 503.6030 432.2457 0.0156 0.4254

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 288.3533 0.0000 288.3533 1113.0695 0.2591 0.3348 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9881 523.7619 503.7028 0.0000 0.0600 0.0445 0.2733

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8703 6.2683 1.0799 530.2932 12.5988 207.6050 1.6093

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 80181.359 0.491 118.481 249740.516 0.790864E-02

 

Melt Ratio at Stator LE, Throat, TE

0.34584E+00 0.42431E+00 0.65225E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.271 EfDer = 0.990 SH = 0.825800E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.148 2453.875 6.268 530.269 1.000 1.000 0.980

 W Kg/sec = 11.886 Wdry = 25.932 WH2O = 0.216 lbm/sec H2O = 4.114g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.002 2426.904 1.371 0.255 53.616 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50549.941 20449.904 2.794 509.668 182.408 384.739 2.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 238.03 -0.08 238.03 0.21 0.41 387.98

 MEAN 15.91 0.00 -0.02 238.03 -0.08 238.03 0.21 0.37

 HUB 13.07 0.00 -0.02 238.03 -0.08 238.03 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.76 47.36 11.40 392.31 458.94 6.08 525.82 503.51 25.38

 MEAN 55.07 44.80 10.27 340.76 415.73 6.08 525.82 503.51 25.38

 HUB 49.63 38.84 10.79 279.88 367.48 6.08 525.82 503.51 25.38

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 324.40 206.44 250.24 1124.28 0.29 2.05 1.78 7.43

 MEAN 15.50 322.68 201.15 252.32 1122.30 0.29 2.13 1.86 5.75

 HUB 12.59 338.72 223.48 254.53 1120.34 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.17 306.93 177.73 0.27 3705.03 0.92 0.91

 MEAN 331.87 284.17 130.72 0.25 3118.66 0.92 0.91 0.91 1.62

 HUB 269.60 258.68 46.13 0.23 2814.65 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.77 1.08 6.40 542.69 1.02 534.43 509.43 20.38

 MEAN 6.69 1.07 6.33 540.72 1.02 532.55 508.74 21.45

 HUB 6.65 1.06 6.25 539.70 1.02 530.70 508.68 22.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.52 35.38 31.50 3.88 0.93 0.49 1.40

 MEAN 38.56 27.39 23.50 3.89 0.94 0.46 1.64

 HUB 41.28 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 352.7129 204.8390 287.1366 1120.9252 0.3147 -0.1683 2.0437

 

NASA/TM—2013-218094 L–149
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6976 6.2620 531.2809 509.5573 22.4689 35.5035 33.0000 -2.5035

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 293.2480 66.9634 285.5001 1124.0817 0.2609 0.1754 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6953 6.3920 534.2937 508.7135 410.5396 0.0261 0.4012

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 285.3049 0.0000 285.3049 1124.4359 0.2537 0.3246 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4034 534.6557 509.2434 0.0000 0.0600 0.0388 0.2055

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8748 6.6905 1.0673 541.0322 10.7657 226.8244 1.7583

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68669.039 0.465 101.469 261977.047 0.915785E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1565 Tt4 = 541.0322 T1 = 467.8131

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 463291.72 684.5869 85.5988 1.5688 0.8325 15.6817 1.1565 37.3740

NASA/TM—2013-218094 L–150
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.722 EfDer = 0.952 SH = 0.127711E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.247 2375.534 4.199 461.505 1.000 1.000 0.980

 W Kg/sec = 11.476 Wdry = 25.215 WH2O = 0.032 lbm/sec H2O = 0.496g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.367 2518.393 1.380 0.249 53.390 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62657.910 19800.420 3.405 831.557 244.197 619.754 2.538

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 180.84 -0.06 180.84 0.17 0.45 453.37

 MEAN 17.06 0.00 -0.02 180.84 -0.06 180.84 0.17 0.38

 HUB 12.51 0.00 -0.02 180.84 -0.06 180.84 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.08 50.47 16.61 427.67 464.39 4.11 458.88 455.06 39.90

 MEAN 62.92 47.20 15.72 353.66 397.27 4.11 458.88 455.06 39.90

 HUB 55.12 38.62 16.50 259.34 316.21 4.11 458.88 455.06 39.90

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 382.83 296.25 242.47 1055.64 0.36 7.29 6.52 16.04

 MEAN 18.04 386.88 298.97 245.54 1052.67 0.37 7.43 6.80 12.53

 HUB 15.00 418.22 335.44 249.77 1049.04 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 427.67 275.80 131.42 0.26 6112.87 0.92 0.87

 MEAN 373.89 256.72 74.92 0.24 5393.32 0.92 0.87 0.87 1.78

 HUB 310.96 250.97 24.49 0.24 5032.44 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.15 4.40 481.82 1.04 470.07 470.95 36.04

 MEAN 4.74 1.13 4.32 479.43 1.04 467.43 469.74 39.86

 HUB 4.70 1.12 4.22 478.23 1.04 464.21 469.66 45.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.70 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.60 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.33 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.952 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 398.0026 298.3906 263.3801 1052.2568 0.3782 -0.0353 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7469 4.3066 467.1489 470.3736 41.6441 48.5662 35.4000 -13.1662

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 261.7397 64.0295 253.7871 1060.3005 0.2469 0.5205 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7357 4.5418 474.3433 468.9131 554.9116 0.0358 0.6131

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 260.6887 0.0000 260.6887 1060.2970 0.2459 0.4878 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5214 474.3892 469.9637 0.0000 0.0600 0.0883 0.4738

NASA/TM—2013-218094 L–151
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8109 4.7127 1.1223 479.8239 18.3219 166.6308 1.2917

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 114479.914 0.626 163.335 263028.906 0.232948E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.219 EfDer = 0.957 SH = 0.339451E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.247 2375.534 4.713 479.822 1.000 1.000 0.980

 W Kg/sec = 11.476 Wdry = 25.162 WH2O = 0.086 lbm/sec H2O = 1.406g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.743 2469.895 1.377 0.251 53.458 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58716.637 19783.859 2.658 590.487 222.152 468.502 2.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.63 -0.08 238.63 0.22 0.46 442.92

 MEAN 18.08 0.00 -0.02 238.63 -0.08 238.63 0.22 0.42

 HUB 15.21 0.00 -0.02 238.63 -0.08 238.63 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.75 46.36 14.39 426.01 488.37 4.55 475.29 472.80 55.79

 MEAN 57.52 42.30 15.22 374.77 444.37 4.55 475.29 472.80 55.79

 HUB 52.89 37.84 15.05 315.31 395.50 4.55 475.29 472.80 55.79

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 352.28 246.44 251.73 1073.59 0.33 2.33 2.04 9.02

 MEAN 18.01 351.63 242.96 254.19 1071.24 0.33 2.40 2.13 7.35

 HUB 15.22 372.28 269.42 256.92 1068.92 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 423.32 307.66 176.88 0.29 5034.00 0.92 0.88

 MEAN 373.35 285.68 130.39 0.27 4377.25 0.92 0.88 0.88 1.71

 HUB 315.58 261.03 46.16 0.24 4102.61 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.26 1.12 4.88 496.44 1.03 486.56 483.16 39.19

 MEAN 5.18 1.10 4.82 494.27 1.03 484.43 482.16 42.22

 HUB 5.15 1.09 4.74 493.37 1.03 482.33 482.18 45.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.39 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.71 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.36 10.19 6.50 3.69 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.7550 243.6459 286.0568 1070.1019 0.3511 -0.1059 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1928 4.7748 483.4592 482.9341 44.0283 40.4223 30.6000 -9.8223

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 276.9678 58.7191 270.6718 1075.7545 0.2575 0.3732 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1869 4.9569 488.5900 481.3515 491.5697 0.0254 0.4686

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 287.0639 0.0000 287.0639 1075.2301 0.2670 0.3590 0.5911

NASA/TM—2013-218094 L–152
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9248 488.1382 481.9441 0.0000 0.0600 0.0674 0.2894

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8293 5.1708 1.0972 494.6930 14.8720 187.8057 1.4559

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93460.539 0.522 133.345 239231.281 0.387499E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.155 EfDer = 0.973 SH = 0.454845E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.247 2375.534 5.171 494.692 1.000 1.000 0.980

 W Kg/sec = 11.476 Wdry = 25.133 WH2O = 0.115 lbm/sec H2O = 2.003g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.095 2432.493 1.376 0.252 53.496 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55219.727 19774.789 2.651 545.479 205.742 424.468 2.063

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 242.94 -0.08 242.94 0.23 0.45 426.02

 MEAN 17.74 0.00 -0.02 242.94 -0.08 242.94 0.23 0.41

 HUB 15.05 0.00 -0.02 242.94 -0.08 242.94 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.72 46.36 13.36 416.06 481.87 4.99 490.01 482.94 44.13

 MEAN 56.55 43.40 13.15 367.73 440.80 4.99 490.01 482.94 44.13

 HUB 52.10 38.84 13.26 311.99 395.49 4.99 490.01 482.94 44.13

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 344.45 230.29 256.15 1088.39 0.32 2.26 1.98 8.75

 MEAN 17.51 345.85 229.95 258.33 1086.38 0.32 2.34 2.07 6.78

 HUB 14.85 368.62 260.58 260.73 1084.41 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.67 313.29 180.38 0.29 4563.72 0.92 0.89

 MEAN 362.92 290.54 132.97 0.27 4027.12 0.92 0.89 0.89 1.66

 HUB 307.85 264.98 47.26 0.24 3870.92 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.70 1.10 5.32 509.70 1.03 500.29 491.72 33.24

 MEAN 5.64 1.09 5.26 507.94 1.03 498.45 491.03 35.29

 HUB 5.62 1.09 5.19 507.42 1.03 496.64 491.29 37.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.96 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.67 27.24 23.50 3.74 0.94 0.50 1.62

 HUB 44.98 10.27 6.50 3.77 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.2485 231.4592 290.2621 1085.2119 0.3421 -0.1141 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6478 5.2156 497.4305 491.8335 36.8124 38.5694 31.5000 -7.0694

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 285.8046 62.3463 278.9215 1090.0453 0.2622 0.3204 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6440 5.3850 501.8805 490.4344 451.3937 0.0195 0.4414

 

NASA/TM—2013-218094 L–153
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 290.6372 0.0000 290.6372 1089.7864 0.2667 0.3430 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3638 501.6612 491.0019 0.0000 0.0600 0.0532 0.2663

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8512 5.6308 1.0890 508.3532 13.6625 193.5172 1.5001

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86200.102 0.511 122.986 238125.766 0.521743E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.494 EfDer = 0.983 SH = 0.612747E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.247 2375.534 5.631 508.352 1.000 1.000 0.980

 W Kg/sec = 11.476 Wdry = 25.093 WH2O = 0.155 lbm/sec H2O = 2.858g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.251 2399.587 1.374 0.253 53.547 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52132.102 19762.322 2.678 513.330 191.710 395.845 2.065

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 243.72 -0.08 243.72 0.22 0.43 403.30

 MEAN 16.97 0.00 -0.02 243.72 -0.08 243.72 0.22 0.39

 HUB 14.32 0.00 -0.02 243.72 -0.08 243.72 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.60 46.36 12.24 399.27 467.85 5.44 503.66 492.13 37.81

 MEAN 55.29 43.80 11.49 351.81 428.05 5.44 503.66 492.13 37.81

 HUB 50.62 37.84 12.78 296.86 384.15 5.44 503.66 492.13 37.81

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.68 210.72 256.14 1101.52 0.30 2.16 1.89 8.34

 MEAN 16.57 333.12 210.60 258.10 1099.72 0.30 2.24 1.97 6.35

 HUB 13.89 354.58 240.82 260.25 1097.95 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 391.39 313.45 180.67 0.28 3979.98 0.92 0.90

 MEAN 343.58 290.35 132.98 0.26 3491.94 0.92 0.90 0.90 1.62

 HUB 287.95 264.48 47.12 0.24 3346.23 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.12 1.09 5.76 521.38 1.03 512.69 499.40 30.22

 MEAN 6.06 1.08 5.69 519.78 1.02 511.02 498.83 31.80

 HUB 6.04 1.07 5.63 519.30 1.02 509.38 499.10 33.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.44 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.21 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.78 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.983 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 353.5004 211.7880 283.0342 1098.8789 0.3217 -0.0909 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0718 5.6591 510.2997 499.5114 32.8148 36.8067 32.4000 -4.4067

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 284.3522 63.7719 277.1088 1102.6042 0.2579 0.2808 2.2705

 

NASA/TM—2013-218094 L–154
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0699 5.8004 513.7763 498.3818 432.2457 0.0149 0.4180

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 282.0923 0.0000 282.0923 1102.6802 0.2558 0.3279 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7944 513.8638 498.7295 0.0000 0.0600 0.0432 0.2651

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8672 6.0591 1.0761 520.1359 11.8028 209.0408 1.6205

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74844.656 0.489 106.785 244079.906 0.688811E-02

 

Melt Ratio at Stator LE, Throat, TE

0.81464E-02 0.27967E-01 0.12475E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.972 EfDer = 0.992 SH = 0.762140E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.247 2375.534 6.059 520.125 1.000 1.000 0.980

 W Kg/sec = 11.476 Wdry = 25.055 WH2O = 0.192 lbm/sec H2O = 3.745g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.338 2372.253 1.372 0.254 53.596 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49483.102 19750.475 2.826 509.668 180.381 384.739 2.133

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 233.00 -0.08 233.00 0.21 0.40 379.25

 MEAN 15.91 0.00 -0.02 233.00 -0.08 233.00 0.21 0.37

 HUB 13.07 0.00 -0.02 233.00 -0.08 233.00 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.48 47.36 11.12 379.78 445.63 5.88 515.86 499.26 32.26

 MEAN 54.77 44.80 9.97 329.88 403.94 5.88 515.86 499.26 32.26

 HUB 49.31 38.84 10.47 270.95 357.41 5.88 515.86 499.26 32.26

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 315.10 197.65 245.41 1113.20 0.28 2.05 1.78 7.43

 MEAN 15.50 313.83 193.18 247.33 1111.36 0.28 2.13 1.86 5.75

 HUB 12.59 329.79 215.81 249.37 1109.54 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.90 300.98 174.26 0.27 3547.28 0.92 0.91

 MEAN 321.27 278.53 128.10 0.25 2995.03 0.92 0.91 0.91 1.61

 HUB 261.00 253.43 45.18 0.23 2718.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.52 1.08 6.18 531.66 1.02 523.86 505.09 26.08

 MEAN 6.45 1.06 6.11 529.86 1.02 522.12 504.42 27.42

 HUB 6.41 1.06 6.04 528.96 1.02 520.42 504.41 28.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.85 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.99 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.87 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 343.3413 196.7172 281.3993 1110.0125 0.3093 -0.1706 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4529 6.0465 520.8899 505.1354 28.4879 34.9562 33.0000 -1.9562

 

NASA/TM—2013-218094 L–155
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 287.7029 65.6972 280.1015 1112.9237 0.2585 0.1589 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4511 6.1625 523.6314 504.1566 410.5396 0.0251 0.3923

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 279.8035 0.0000 279.8035 1113.2314 0.2513 0.3156 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1748 523.9288 504.1417 0.0000 0.0600 0.0379 0.1936

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8848 6.4465 1.0639 530.0771 10.0388 229.2761 1.7773

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63909.262 0.462 91.183 256383.125 0.795038E-02

 

Melt Ratio at Stator LE, Throat, TE

0.55194E+00 0.62258E+00 0.83135E+00

 trTOT = 1.1486 Tt4 = 530.0771 T1 = 461.5047

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 432894.47 617.6337 83.3671 1.5351 0.8343 15.7219 1.1486 37.3740

NASA/TM—2013-218094 L–156
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.744 EfDer = 0.952 SH = 0.115699E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.835 2344.952 4.337 459.574 1.000 1.000 0.980

 W Kg/sec = 11.743 Wdry = 25.805 WH2O = 0.030 lbm/sec H2O = 0.466g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.424 2491.189 1.380 0.249 53.386 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61792.938 20262.127 3.444 831.557 241.416 619.754 2.567

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 178.34 -0.06 178.34 0.17 0.44 448.48

 MEAN 17.06 0.00 -0.02 178.34 -0.06 178.34 0.17 0.38

 HUB 12.51 0.00 -0.02 178.34 -0.06 178.34 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.10 50.47 16.63 422.16 458.35 4.25 457.02 453.71 40.79

 MEAN 62.94 47.20 15.74 349.11 392.08 4.25 457.02 453.71 40.79

 HUB 55.14 38.62 16.52 256.00 312.05 4.25 457.02 453.71 40.79

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 377.90 292.42 239.37 1053.24 0.36 7.29 6.52 16.04

 MEAN 18.04 381.89 295.15 242.33 1050.35 0.36 7.43 6.80 12.53

 HUB 15.00 412.73 331.11 246.40 1046.80 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 422.16 272.27 129.74 0.26 6033.89 0.92 0.87

 MEAN 369.08 253.35 73.93 0.24 5324.39 0.92 0.87 0.87 1.78

 HUB 306.95 247.58 24.15 0.24 4967.36 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.96 1.14 4.54 479.38 1.04 467.92 469.40 36.88

 MEAN 4.88 1.13 4.46 477.05 1.04 465.35 468.17 40.72

 HUB 4.84 1.12 4.36 475.88 1.04 462.22 468.03 45.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.70 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.61 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.34 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.952 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 392.8443 294.5771 259.9056 1049.9492 0.3742 -0.0354 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8899 4.4454 465.0758 468.7715 42.5135 48.5780 35.4000 -13.1780

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 258.4956 63.2359 250.6416 1057.8020 0.2444 0.5205 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8787 4.6829 472.0825 467.4207 554.9116 0.0354 0.6128

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.4409 0.0000 257.4409 1057.7998 0.2434 0.4874 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6621 472.1278 468.3948 0.0000 0.0600 0.0884 0.4734

NASA/TM—2013-218094 L–157
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8108 4.8554 1.1195 477.4312 17.8595 166.5765 1.2913

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 111529.672 0.626 162.828 269897.406 0.209060E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.208 EfDer = 0.957 SH = 0.303301E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.835 2344.952 4.855 477.430 1.000 1.000 0.980

 W Kg/sec = 11.743 Wdry = 25.757 WH2O = 0.078 lbm/sec H2O = 1.302g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.041 2444.200 1.378 0.251 53.447 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57985.035 20247.125 2.683 590.487 220.044 468.502 2.129

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 235.66 -0.08 235.66 0.22 0.46 438.31

 MEAN 18.08 0.00 -0.02 235.66 -0.08 235.66 0.22 0.41

 HUB 15.21 0.00 -0.02 235.66 -0.08 235.66 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.74 46.36 14.38 420.53 482.13 4.69 473.00 471.03 56.81

 MEAN 57.51 42.30 15.21 369.95 438.70 4.69 473.00 471.03 56.81

 HUB 52.88 37.84 15.04 311.25 390.47 4.69 473.00 471.03 56.81

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 347.85 243.05 248.86 1070.81 0.32 2.33 2.04 9.02

 MEAN 18.01 347.22 239.68 251.23 1068.51 0.32 2.40 2.13 7.35

 HUB 15.22 367.64 265.92 253.87 1066.25 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 417.87 304.13 174.82 0.28 4964.68 0.92 0.88

 MEAN 368.55 282.35 128.87 0.26 4318.03 0.92 0.88 0.88 1.71

 HUB 311.52 257.93 45.60 0.24 4049.34 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.11 5.03 493.63 1.03 483.98 481.37 40.11

 MEAN 5.33 1.10 4.96 491.52 1.03 481.91 480.36 43.16

 HUB 5.30 1.09 4.89 490.64 1.03 479.87 480.34 46.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.32 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.65 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.33 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.0534 240.3493 282.6886 1067.3960 0.3476 -0.1060 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3392 4.9174 480.9602 481.0994 44.9884 40.3721 30.6000 -9.7721

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 273.8688 58.0621 267.6433 1072.9126 0.2553 0.3721 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3334 5.1007 485.9531 479.6275 491.5697 0.0250 0.4674

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 283.8217 0.0000 283.8217 1072.3979 0.2647 0.3579 0.5911

NASA/TM—2013-218094 L–158
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0684 485.5122 480.1827 0.0000 0.0600 0.0671 0.2882

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8295 5.3172 1.0951 491.9273 14.4990 187.9374 1.4569

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91010.484 0.521 132.871 245548.859 0.345859E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.109 EfDer = 0.973 SH = 0.405559E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.835 2344.952 5.317 491.926 1.000 1.000 0.980

 W Kg/sec = 11.743 Wdry = 25.730 WH2O = 0.105 lbm/sec H2O = 1.848g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.556 2407.917 1.376 0.251 53.480 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54602.617 20238.908 2.673 545.479 204.101 424.468 2.080

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.23 -0.08 240.23 0.22 0.44 421.72

 MEAN 17.74 0.00 -0.02 240.23 -0.08 240.23 0.22 0.41

 HUB 15.05 0.00 -0.02 240.23 -0.08 240.23 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.68 46.36 13.32 410.70 475.87 5.14 487.34 481.12 45.15

 MEAN 56.51 43.40 13.11 362.99 435.36 5.14 487.34 481.12 45.15

 HUB 52.05 38.84 13.21 307.98 390.65 5.14 487.34 481.12 45.15

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 340.21 226.85 253.53 1085.26 0.31 2.26 1.98 8.75

 MEAN 17.51 341.67 226.70 255.63 1083.31 0.32 2.34 2.07 6.78

 HUB 14.85 364.22 257.13 257.95 1081.39 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 405.38 310.08 178.53 0.29 4495.62 0.92 0.89

 MEAN 358.25 287.49 131.55 0.27 3970.21 0.92 0.89 0.89 1.66

 HUB 303.88 262.16 46.75 0.24 3819.62 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.85 1.10 5.47 506.54 1.03 497.35 489.88 34.15

 MEAN 5.79 1.09 5.41 504.84 1.03 495.56 489.17 36.22

 HUB 5.77 1.08 5.34 504.35 1.03 493.81 489.41 38.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.82 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.57 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.91 10.27 6.50 3.77 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.8175 228.1876 287.2029 1082.1594 0.3390 -0.1146 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7971 5.3610 494.5604 489.9443 37.7860 38.4677 31.5000 -6.9677

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 282.9402 61.7215 276.1260 1086.8732 0.2603 0.3181 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7935 5.5312 498.8869 488.6380 451.3937 0.0192 0.4394

 

NASA/TM—2013-218094 L–159
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 287.7026 0.0000 287.7026 1086.6199 0.2648 0.3412 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5098 498.6725 489.1730 0.0000 0.0600 0.0527 0.2640

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8518 5.7802 1.0871 505.2407 13.3155 193.8853 1.5030

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83878.781 0.510 122.459 244518.453 0.464940E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.416 EfDer = 0.984 SH = 0.545625E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.835 2344.952 5.780 505.240 1.000 1.000 0.980

 W Kg/sec = 11.743 Wdry = 25.694 WH2O = 0.141 lbm/sec H2O = 2.631g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.845 2375.980 1.374 0.253 53.525 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51609.598 20227.615 2.695 513.330 190.440 395.845 2.079

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.28 -0.08 241.28 0.22 0.42 399.33

 MEAN 16.97 0.00 -0.02 241.28 -0.08 241.28 0.22 0.39

 HUB 14.32 0.00 -0.02 241.28 -0.08 241.28 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.53 46.36 12.17 394.13 462.19 5.59 500.63 490.24 38.85

 MEAN 55.22 43.80 11.42 347.28 422.94 5.59 500.63 490.24 38.85

 HUB 50.54 37.84 12.70 293.04 379.65 5.59 500.63 490.24 38.85

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.74 207.38 253.79 1098.10 0.30 2.16 1.89 8.34

 MEAN 16.57 329.25 207.43 255.69 1096.35 0.30 2.24 1.97 6.35

 HUB 13.89 350.53 237.55 257.76 1094.63 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.35 310.54 178.97 0.28 3916.96 0.92 0.90

 MEAN 339.16 287.62 131.73 0.26 3439.37 0.92 0.90 0.90 1.61

 HUB 284.24 261.95 46.68 0.24 3300.83 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.27 1.09 5.90 517.92 1.03 509.42 497.49 31.18

 MEAN 6.21 1.07 5.84 516.37 1.02 507.80 496.91 32.78

 HUB 6.19 1.07 5.78 515.93 1.02 506.21 497.15 34.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.25 35.19 31.50 3.69 0.93 0.49 1.40

 MEAN 39.05 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.66 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.4502 208.5989 280.3604 1095.5255 0.3190 -0.0913 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2232 5.8068 507.0900 497.5631 33.8238 36.6507 32.4000 -4.2507

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 281.7843 63.1960 274.6064 1099.1544 0.2564 0.2778 2.2705

 

NASA/TM—2013-218094 L–160
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2214 5.9483 510.4660 496.5248 432.2457 0.0146 0.4153

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 279.5488 0.0000 279.5488 1099.2426 0.2543 0.3253 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9422 510.5646 496.9612 0.0000 0.0600 0.0428 0.2620

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8666 6.2105 1.0745 516.7372 11.5005 209.6776 1.6254

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72775.008 0.488 106.248 250720.859 0.620032E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.15663E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.861 EfDer = 0.992 SH = 0.703882E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.835 2344.952 6.211 516.731 1.000 1.000 0.980

 W Kg/sec = 11.743 Wdry = 25.653 WH2O = 0.182 lbm/sec H2O = 3.571g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.034 2349.401 1.373 0.254 53.577 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49047.840 20214.797 2.841 509.668 179.424 384.739 2.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 230.95 -0.08 230.95 0.21 0.40 375.59

 MEAN 15.91 0.00 -0.02 230.95 -0.08 230.95 0.21 0.36

 HUB 13.07 0.00 -0.02 230.95 -0.08 230.95 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.37 47.36 11.01 374.89 440.39 6.03 512.53 497.79 34.49

 MEAN 54.66 44.80 9.86 325.64 399.29 6.03 512.53 497.79 34.49

 HUB 49.20 38.84 10.36 267.46 353.43 6.03 512.53 497.79 34.49

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 311.45 194.27 243.43 1109.51 0.28 2.05 1.78 7.43

 MEAN 15.50 310.33 190.10 245.29 1107.72 0.28 2.13 1.86 5.75

 HUB 12.59 326.23 212.80 247.27 1105.95 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 367.12 298.56 172.85 0.27 3486.62 0.92 0.91

 MEAN 317.14 276.23 127.03 0.25 2947.42 0.92 0.91 0.91 1.60

 HUB 257.64 251.30 44.83 0.23 2680.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.07 6.32 527.95 1.02 520.31 503.68 28.15

 MEAN 6.60 1.06 6.26 526.21 1.02 518.63 503.02 29.56

 HUB 6.56 1.06 6.19 525.35 1.02 516.97 503.00 31.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.59 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.78 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.72 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.6358 193.5897 279.0619 1106.3871 0.3070 -0.1716 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6056 6.1954 517.4189 503.7392 30.7550 34.7497 33.0000 -1.7497

 

NASA/TM—2013-218094 L–161
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 285.4108 65.1738 277.8699 1109.2144 0.2573 0.1549 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6039 6.3113 520.0729 502.8109 410.5396 0.0248 0.3889

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 277.5981 0.0000 277.5981 1109.5278 0.2502 0.3120 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3234 520.3749 502.8428 0.0000 0.0600 0.0377 0.1889

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8837 6.5993 1.0626 526.4362 9.7747 230.1541 1.7841

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 62127.969 0.461 90.704 263474.906 0.743671E-02

 

Melt Ratio at Stator LE, Throat, TE

0.36385E+00 0.42808E+00 0.62166E+00

 trTOT = 1.1455 Tt4 = 526.4362 T1 = 459.5743

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 421321.91 615.1105 82.4237 1.5216 0.8344 15.7438 1.1455 37.3740

NASA/TM—2013-218094 L–162
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.782 EfDer = 0.952 SH = 0.115948E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.752 2273.080 4.829 461.398 1.000 1.000 0.980

 W Kg/sec = 12.615 Wdry = 27.720 WH2O = 0.032 lbm/sec H2O = 0.518g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.686 2410.064 1.380 0.249 53.386 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59800.316 21765.988 3.563 831.557 233.403 619.754 2.655

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.59 -0.06 172.59 0.17 0.43 433.87

 MEAN 17.06 0.00 -0.02 172.59 -0.06 172.59 0.17 0.36

 HUB 12.51 0.00 -0.02 172.59 -0.06 172.59 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.14 50.47 16.67 409.22 444.19 4.74 459.01 455.67 41.48

 MEAN 62.98 47.20 15.78 338.41 379.93 4.74 459.01 455.67 41.48

 HUB 55.19 38.62 16.57 248.15 302.32 4.74 459.01 455.67 41.48

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 366.42 283.35 232.32 1054.68 0.35 7.29 6.52 16.04

 MEAN 18.04 370.25 286.11 235.00 1051.98 0.35 7.43 6.80 12.53

 HUB 15.00 399.99 320.98 238.68 1048.66 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.22 264.23 125.87 0.25 5846.80 0.92 0.87

 MEAN 357.77 245.68 71.66 0.23 5161.34 0.92 0.87 0.87 1.78

 HUB 297.55 239.83 23.43 0.23 4815.39 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 480.00 1.04 469.23 470.52 37.76

 MEAN 5.39 1.12 4.96 477.81 1.04 466.82 469.33 41.39

 HUB 5.35 1.11 4.85 476.71 1.03 463.89 469.17 46.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.65 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.60 16.96 12.70 4.26 0.95 0.53 2.22

 HUB 53.36 -5.61 -9.30 3.69 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.952 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 380.8472 285.5565 251.9962 1051.6023 0.3622 -0.0356 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.4027 4.9409 466.5606 469.8948 43.1248 48.5724 35.4000 -13.1724

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 251.2235 61.4569 243.5904 1058.9452 0.2372 0.5198 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3916 5.1873 473.1205 468.6674 554.9116 0.0343 0.6112

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 250.1499 0.0000 250.1499 1058.9491 0.2362 0.4858 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1653 473.1651 469.5557 0.0000 0.0600 0.0884 0.4717

NASA/TM—2013-218094 L–163
 

 STAGE EXIT CONDITIONS, STAGE 1 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8106 5.3668 1.1115 478.1725 16.7773 166.4670 1.2904

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 104774.430 0.626 164.319 288774.406 0.201166E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.140 EfDer = 0.957 SH = 0.287067E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.752 2273.080 5.367 478.171 1.000 1.000 0.980

 W Kg/sec = 12.615 Wdry = 27.673 WH2O = 0.080 lbm/sec H2O = 1.362g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.985 2367.449 1.378 0.250 53.441 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56355.047 21751.289 2.759 590.487 213.998 468.502 2.189

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 229.04 -0.08 229.04 0.22 0.44 424.55

 MEAN 18.08 0.00 -0.02 229.04 -0.08 229.04 0.22 0.40

 HUB 15.21 0.00 -0.02 229.04 -0.08 229.04 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.67 46.36 14.31 407.64 467.64 5.20 473.99 472.01 57.02

 MEAN 57.44 42.30 15.14 358.61 425.58 5.20 473.99 472.01 57.02

 HUB 52.80 37.84 14.96 301.71 378.86 5.20 473.99 472.01 57.02

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 337.55 234.70 242.60 1071.11 0.32 2.33 2.04 9.02

 MEAN 18.01 337.07 231.75 244.75 1068.97 0.32 2.40 2.13 7.35

 HUB 15.22 357.01 257.63 247.14 1066.86 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 405.06 296.44 170.36 0.28 4794.21 0.92 0.88

 MEAN 357.25 275.05 125.50 0.26 4175.32 0.92 0.88 0.88 1.71

 HUB 301.97 251.09 44.34 0.24 3923.14 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.93 1.11 5.54 493.34 1.03 484.25 481.88 41.28

 MEAN 5.86 1.09 5.47 491.38 1.03 482.32 480.91 44.19

 HUB 5.83 1.09 5.40 490.58 1.03 480.42 480.88 47.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.05 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.44 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.19 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 360.2830 232.4051 275.3029 1067.9193 0.3374 -0.1068 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8666 5.4287 481.4219 481.6004 45.9654 40.1704 30.6000 -9.5704

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 267.1762 56.6433 261.1028 1073.0621 0.2490 0.3676 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8610 5.6174 486.0779 480.2752 491.5697 0.0238 0.4631

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 276.7996 0.0000 276.7996 1072.5780 0.2581 0.3541 0.5911

NASA/TM—2013-218094 L–164
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5838 485.6617 480.7816 0.0000 0.0600 0.0660 0.2836

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8306 5.8442 1.0889 491.7663 13.5964 188.5319 1.4615

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85306.680 0.520 133.788 263068.844 0.325098E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.937 EfDer = 0.974 SH = 0.378154E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.752 2273.080 5.844 491.765 1.000 1.000 0.980

 W Kg/sec = 12.615 Wdry = 27.647 WH2O = 0.105 lbm/sec H2O = 1.897g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.970 2334.498 1.377 0.251 53.471 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53275.930 21743.436 2.735 545.479 199.415 424.468 2.129

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 234.39 -0.08 234.39 0.22 0.43 408.86

 MEAN 17.74 0.00 -0.02 234.39 -0.08 234.39 0.22 0.39

 HUB 15.05 0.00 -0.02 234.39 -0.08 234.39 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.52 46.36 13.16 398.12 462.06 5.66 487.40 481.64 46.25

 MEAN 56.34 43.40 12.94 351.87 422.86 5.66 487.40 481.64 46.25

 HUB 51.87 38.84 13.03 298.54 379.62 5.66 487.40 481.64 46.25

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 330.49 218.38 248.06 1084.62 0.30 2.26 1.98 8.75

 MEAN 17.51 332.12 218.68 249.97 1082.81 0.31 2.34 2.07 6.78

 HUB 14.85 354.26 248.91 252.08 1081.03 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 392.96 303.34 174.58 0.28 4327.63 0.92 0.89 

 MEAN 347.27 281.10 128.59 0.26 3829.75 0.92 0.89 0.89 1.65

 HUB 294.57 256.18 45.66 0.24 3697.50 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.39 1.09 6.00 505.42 1.03 496.73 490.01 35.66

 MEAN 6.33 1.08 5.93 503.85 1.02 495.07 489.34 37.66

 HUB 6.31 1.08 5.86 503.43 1.02 493.45 489.57 39.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.36 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 41.18 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.64 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 356.7537 220.1141 280.7543 1081.7094 0.3298 -0.1160 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3374 5.8848 494.1178 490.0659 39.2174 38.0968 31.5000 -6.5968

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 277.0177 60.4295 270.3463 1086.0874 0.2551 0.3099 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3341 6.0584 498.1328 488.8917 451.3937 0.0181 0.4325

 

NASA/TM—2013-218094 L–165
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 281.6188 0.0000 281.6188 1085.8478 0.2594 0.3350 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0364 497.9297 489.3791 0.0000 0.0600 0.0511 0.2563

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8538 6.3205 1.0815 504.2287 12.4644 195.1978 1.5132

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 78451.195 0.508 123.036 262375.188 0.430210E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.144 EfDer = 0.986 SH = 0.500677E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.752 2273.080 6.321 504.228 1.000 1.000 0.980

 W Kg/sec = 12.615 Wdry = 27.613 WH2O = 0.139 lbm/sec H2O = 2.648g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.639 2305.468 1.375 0.252 53.511 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50536.223 21732.834 2.747 513.330 186.849 395.845 2.119

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 236.26 -0.08 236.26 0.22 0.41 387.48

 MEAN 16.97 0.00 -0.02 236.26 -0.08 236.26 0.22 0.38

 HUB 14.32 0.00 -0.02 236.26 -0.08 236.26 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.27 46.36 11.91 382.05 449.27 6.12 499.81 490.35 40.31

 MEAN 54.94 43.80 11.14 336.64 411.34 6.12 499.81 490.35 40.31

 HUB 50.26 37.84 12.42 284.06 369.53 6.12 499.81 490.35 40.31

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 318.77 198.88 249.13 1096.61 0.29 2.16 1.89 8.34

 MEAN 16.57 320.55 199.57 250.85 1094.99 0.29 2.24 1.97 6.35

 HUB 13.89 341.58 229.79 252.74 1093.40 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 374.51 304.81 175.63 0.28 3756.42 0.92 0.90

 MEAN 328.77 282.16 129.19 0.26 3309.07 0.92 0.90 0.90 1.60

 HUB 275.53 256.84 45.74 0.23 3192.88 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.82 1.08 6.44 516.03 1.02 507.98 497.27 32.84

 MEAN 6.76 1.07 6.38 514.63 1.02 506.49 496.72 34.40

 HUB 6.75 1.07 6.31 514.26 1.02 505.02 496.97 35.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.60 35.18 31.50 3.68 0.93 0.48 1.40

 MEAN 38.51 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.28 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 340.4505 200.6946 275.0059 1094.1946 0.3111 -0.0929 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7734 6.3412 505.7999 497.3428 35.4629 36.1213 32.4000 -3.7213

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 276.7628 62.0698 269.7127 1097.5449 0.2522 0.2665 2.2705

 

NASA/TM—2013-218094 L–166
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7719 6.4840 508.9110 496.4155 432.2457 0.0138 0.4062

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 274.5355 0.0000 274.5355 1097.6326 0.2501 0.3166 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4780 509.0078 496.8144 0.0000 0.0600 0.0413 0.2515

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8688 6.7609 1.0697 514.9697 10.7446 211.8723 1.6424

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67896.039 0.484 106.482 269401.000 0.565253E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.12626E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.501 EfDer = 0.994 SH = 0.638895E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.752 2273.080 6.761 514.964 1.000 1.000 0.980

 W Kg/sec = 12.615 Wdry = 27.575 WH2O = 0.177 lbm/sec H2O = 3.544g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.124 2281.298 1.373 0.253 53.556 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48180.926 21720.826 2.885 509.668 176.681 384.739 2.178 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 226.87 -0.08 226.87 0.21 0.39 364.71

 MEAN 15.91 0.00 -0.02 226.87 -0.08 226.87 0.21 0.35

 HUB 13.07 0.00 -0.02 226.87 -0.08 226.87 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.03 47.36 10.67 363.40 428.47 6.57 510.90 497.58 36.23

 MEAN 54.30 44.80 9.50 315.66 388.79 6.57 510.90 497.58 36.23

 HUB 48.82 38.84 9.98 259.26 344.57 6.57 510.90 497.58 36.23

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 303.19 185.71 239.66 1107.27 0.27 2.05 1.78 7.43

 MEAN 15.50 302.53 182.40 241.35 1105.61 0.27 2.13 1.86 5.75

 HUB 12.59 318.49 205.69 243.16 1103.98 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.86 293.92 170.15 0.27 3333.06 0.92 0.91

 MEAN 307.42 271.81 125.01 0.25 2828.04 0.92 0.91 0.91 1.58

 HUB 249.74 247.11 44.05 0.22 2590.67 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.23 1.07 6.87 525.38 1.02 518.13 503.23 29.99

 MEAN 7.16 1.06 6.80 523.80 1.02 516.58 502.61 31.40

 HUB 7.12 1.05 6.73 523.06 1.02 515.06 502.60 32.83

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.77 35.37 31.50 3.87 0.93 0.47 1.40

 MEAN 37.08 27.38 23.50 3.88 0.94 0.44 1.64

 HUB 40.23 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 331.4517 185.7468 274.5147 1104.3260 0.3001 -0.1741 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1626 6.7365 515.4092 503.2902 32.6339 34.0837 33.0000 -1.0837

 

NASA/TM—2013-218094 L–167
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 281.0726 64.1832 273.6463 1106.9103 0.2539 0.1396 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1612 6.8518 517.8300 502.4684 410.5396 0.0238 0.3779

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 273.3932 0.0000 273.3932 1107.2169 0.2469 0.3006 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8646 518.1254 502.5046 0.0000 0.0600 0.0370 0.1741

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8850 7.1563 1.0585 524.0159 9.1155 233.3453 1.8089

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57826.457 0.457 90.690 283444.344 0.675103E-02

 

Melt Ratio at Stator LE, Throat, TE

0.33659E+00 0.39685E+00 0.57870E+00

 trTOT = 1.1357 Tt4 = 524.0159 T1 = 461.3977

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 394254.81 618.3150 79.6861 1.4821 0.8360 15.7821 1.1357 37.3740

NASA/TM—2013-218094 L–168
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.279 EfDer = 0.964 SH = 0.151938E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.772 2152.985 5.592 471.068 1.000 1.000 0.980

 W Kg/sec = 14.442 Wdry = 31.724 WH2O = 0.048 lbm/sec H2O = 0.770g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.592 2259.188 1.380 0.249 53.398 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60363.965 24915.389 3.566 831.557 233.187 619.754 2.658

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.22 -0.06 174.22 0.17 0.40 406.71

 MEAN 17.06 0.00 -0.02 174.22 -0.06 174.22 0.17 0.35

 HUB 12.51 0.00 -0.02 174.22 -0.06 174.22 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.80 50.47 15.33 387.60 425.01 5.49 468.64 463.98 40.41

 MEAN 61.48 47.20 14.28 320.53 364.87 5.49 468.64 463.98 40.41

 HUB 53.46 38.62 14.84 235.04 292.62 5.49 468.64 463.98 40.41

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 351.27 260.39 235.78 1063.66 0.33 7.29 6.52 16.04

 MEAN 18.04 357.51 266.67 238.12 1061.38 0.34 7.43 6.80 12.53

 HUB 15.00 389.63 305.81 241.43 1058.48 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 387.60 267.91 127.22 0.25 5373.01 0.92 0.88

 MEAN 338.87 248.82 72.19 0.23 4810.74 0.92 0.88 0.88 1.68

 HUB 281.83 242.62 23.99 0.23 4587.93 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.79 487.23 1.03 477.35 476.82 38.24

 MEAN 6.16 1.10 5.70 485.54 1.03 475.31 475.99 41.20

 HUB 6.14 1.10 5.59 484.87 1.03 472.72 476.15 45.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.84 28.35 24.20 4.15 0.93 0.54 1.80

 MEAN 48.24 16.87 12.70 4.17 0.95 0.49 2.22

 HUB 51.71 -5.67 -9.30 3.63 0.95 0.36 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.964 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.8559 266.1548 255.3749 1060.9534 0.3477 -0.0410 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1724 5.6842 475.0045 476.5662 42.8902 46.1841 35.4000 -10.7841

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 255.8424 62.5869 248.0690 1067.2180 0.2397 0.4789 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1641 5.9258 480.6488 475.4209 554.9116 0.0272 0.5681

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 254.4767 0.0000 254.4767 1067.2439 0.2384 0.4566 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9071 480.7059 476.2749 0.0000 0.0600 0.0731 0.4402

NASA/TM—2013-218094 L–169
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8290 6.1419 1.0983 485.8803 14.8144 173.7089 1.3466

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92657.633 0.617 166.366 325500.219 0.245036E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.258 EfDer = 0.972 SH = 0.336636E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.772 2152.985 6.142 485.879 1.000 1.000 0.980

 W Kg/sec = 14.442 Wdry = 31.666 WH2O = 0.107 lbm/sec H2O = 1.797g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.599 2224.510 1.377 0.251 53.457 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 57327.094 24897.201 2.735 590.487 215.869 468.502 2.170

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 232.99 -0.08 232.99 0.22 0.42 398.92

 MEAN 18.08 0.00 -0.02 232.99 -0.08 232.99 0.22 0.39

 HUB 15.21 0.00 -0.02 232.99 -0.08 232.99 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.90 46.36 12.54 386.10 451.02 5.94 481.56 478.70 55.21

 MEAN 55.56 42.30 13.26 339.66 411.96 5.94 481.56 478.70 55.21

 HUB 50.82 37.84 12.98 285.77 368.77 5.94 481.56 478.70 55.21

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 324.93 209.77 248.15 1077.64 0.30 2.33 2.04 9.02

 MEAN 18.01 326.80 210.50 249.97 1075.91 0.30 2.40 2.13 7.35

 HUB 15.22 348.72 241.03 252.01 1074.21 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.66 303.01 173.89 0.28 4285.08 0.92 0.89

 MEAN 338.38 280.78 127.88 0.26 3792.56 0.92 0.89 0.89 1.61

 HUB 286.01 255.99 44.98 0.24 3670.45 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.68 1.09 6.28 498.70 1.03 490.29 486.93 42.57

 MEAN 6.62 1.08 6.22 497.22 1.02 488.72 486.26 44.91

 HUB 6.60 1.08 6.15 496.86 1.02 487.18 486.48 47.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.21 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 40.10 27.09 23.50 3.59 0.94 0.48 1.63

 HUB 43.72 10.12 6.50 3.62 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 351.6497 211.0917 281.2434 1074.8002 0.3272 -0.1203 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6324 6.1658 487.7545 486.9660 46.7485 36.8906 30.6000 -6.2906

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.0596 58.1026 267.8297 1079.0419 0.2540 0.3032 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6293 6.3430 491.6172 485.8077 491.5697 0.0175 0.4085

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 283.7090 0.0000 283.7090 1078.5541 0.2630 0.3088 0.5911

NASA/TM—2013-218094 L–170
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3099 491.1900 486.3009 0.0000 0.0600 0.0498 0.2246

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8517 6.6156 1.0771 497.5924 11.7144 201.1380 1.5592

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73624.445 0.500 132.192 297779.000 0.375139E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.831 EfDer = 0.987 SH = 0.426794E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.772 2152.985 6.616 497.591 1.000 1.000 0.980

 W Kg/sec = 14.442 Wdry = 31.637 WH2O = 0.136 lbm/sec H2O = 2.393g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.147 2198.175 1.376 0.252 53.487 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54584.070 24888.287 2.688 545.479 202.935 424.468 2.092 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.15 -0.08 240.15 0.22 0.41 384.99

 MEAN 17.74 0.00 -0.02 240.15 -0.08 240.15 0.22 0.38

 HUB 15.05 0.00 -0.02 240.15 -0.08 240.15 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.51 46.36 11.15 377.08 447.13 6.40 493.01 487.00 46.97

 MEAN 54.23 43.40 10.83 333.28 410.85 6.40 493.01 487.00 46.97

 HUB 49.67 38.84 10.83 282.76 371.05 6.40 493.01 487.00 46.97

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 319.94 192.45 255.59 1088.99 0.29 2.26 1.98 8.75

 MEAN 17.51 323.78 196.72 257.16 1087.58 0.30 2.34 2.07 6.78

 HUB 14.85 347.74 232.13 258.91 1086.20 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 372.20 312.46 179.74 0.29 3814.17 0.92 0.90

 MEAN 328.92 289.15 132.20 0.27 3445.41 0.92 0.90 0.90 1.55

 HUB 279.01 263.12 46.87 0.24 3448.43 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.13 1.08 6.72 508.97 1.02 500.84 493.98 38.11

 MEAN 7.08 1.07 6.66 507.87 1.02 499.55 493.57 39.73

 HUB 7.08 1.07 6.60 507.88 1.02 498.28 494.02 41.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.98 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 37.42 27.21 23.50 3.71 0.94 0.44 1.62

 HUB 41.88 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 350.2697 198.0137 288.9281 1086.4006 0.3224 -0.1306 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0915 6.6067 498.5056 494.3221 41.4086 34.4244 31.5000 -2.9244

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.2234 62.4377 279.3303 1089.9119 0.2626 0.2335 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0899 6.7635 501.7396 493.3299 451.3937 0.0137 0.3731

 

NASA/TM—2013-218094 L–171
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 290.8223 0.0000 290.8223 1089.6686 0.2669 0.2800 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7425 501.5302 493.7805 0.0000 0.0600 0.0395 0.1850

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8709 7.0787 1.0700 508.2373 10.6466 210.3809 1.6309

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67114.469 0.484 120.504 298089.844 0.475961E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.803 EfDer = 0.996 SH = 0.540735E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.772 2152.985 7.079 508.236 1.000 1.000 0.980

 W Kg/sec = 14.442 Wdry = 31.601 WH2O = 0.172 lbm/sec H2O = 3.173g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.312 2175.033 1.374 0.253 53.524 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52153.141 24876.984 2.676 513.330 191.812 395.845 2.064

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 243.82 -0.08 243.82 0.22 0.40 365.56

 MEAN 16.97 0.00 -0.02 243.82 -0.08 243.82 0.22 0.37

 HUB 14.32 0.00 -0.02 243.82 -0.08 243.82 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.03 46.36 9.67 361.86 436.41 6.84 503.53 494.52 42.15

 MEAN 52.60 43.80 8.80 318.85 401.46 6.84 503.53 494.52 42.15

 HUB 47.82 37.84 9.98 269.05 363.16 6.84 503.53 494.52 42.15

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 310.73 172.38 258.53 1098.99 0.28 2.16 1.89 8.34

 MEAN 16.57 314.72 177.45 259.92 1097.78 0.29 2.24 1.97 6.35

 HUB 13.89 337.57 213.55 261.44 1096.58 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.72 316.37 182.34 0.29 3256.22 0.92 0.91

 MEAN 311.40 292.40 133.94 0.27 2942.54 0.92 0.91 0.91 1.50

 HUB 260.97 265.71 47.42 0.24 2967.42 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.54 1.07 7.14 517.91 1.02 510.27 500.21 35.64

 MEAN 7.49 1.06 7.09 516.98 1.02 509.15 499.89 36.89

 HUB 7.50 1.06 7.03 517.06 1.02 508.04 500.36 38.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.69 35.19 31.50 3.69 0.93 0.41 1.40

 MEAN 34.32 27.26 23.50 3.76 0.93 0.41 1.62

 HUB 39.24 10.28 6.50 3.78 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 336.2926 178.4528 285.0392 1096.9000 0.3066 -0.1055 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.5068 7.0413 508.3733 500.5258 38.0383 32.0492 32.4000 0.3508

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 287.9493 64.5786 280.6144 1099.4586 0.2619 0.1806 2.2705

 

NASA/TM—2013-218094 L–172
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.5060 7.1622 510.7544 499.7578 432.2457 0.0120 0.3423

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 285.5165 0.0000 285.5165 1099.5459 0.2597 0.2512 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1583 510.8465 499.9602 0.0000 0.0600 0.0366 0.1714

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8810 7.4955 1.0589 517.2882 9.0799 231.0998 1.7915

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57442.270 0.457 103.137 307088.094 0.587633E-02

 

Melt Ratio at Stator LE, Throat, TE

0.63589E-01 0.96630E-01 0.21029E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.958 EfDer = 1.000 SH = 0.630604E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.772 2152.985 7.496 517.277 1.000 1.000 0.980

 W Kg/sec = 14.442 Wdry = 31.572 WH2O = 0.200 lbm/sec H2O = 3.855g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.227 2155.921 1.373 0.253 53.553 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50054.371 24868.045 2.787 509.668 182.855 384.739 2.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 235.70 -0.08 235.70 0.21 0.38 344.66

 MEAN 15.91 0.00 -0.02 235.70 -0.08 235.70 0.21 0.35

 HUB 13.07 0.00 -0.02 235.70 -0.08 235.70 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.60 47.36 8.24 344.20 417.23 7.26 512.89 500.07 36.76

 MEAN 51.76 44.80 6.96 298.98 380.77 7.26 512.89 500.07 36.76

 HUB 46.18 38.84 7.34 245.56 340.43 7.26 512.89 500.07 36.76

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 296.63 159.11 250.34 1107.96 0.27 2.05 1.78 7.43

 MEAN 15.50 298.57 160.58 251.71 1106.71 0.27 2.13 1.86 5.75

 HUB 12.59 316.80 190.43 253.18 1105.47 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.06 307.15 177.96 0.28 2855.87 0.92 0.91

 MEAN 291.17 283.57 130.60 0.26 2489.86 0.92 0.91 0.91 1.48

 HUB 236.55 257.35 46.12 0.23 2398.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.92 1.06 7.54 525.72 1.02 518.78 504.62 31.36

 MEAN 7.86 1.05 7.48 524.64 1.01 517.61 504.22 32.46

 HUB 7.85 1.05 7.42 524.37 1.01 516.45 504.44 33.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.44 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.54 27.42 23.50 3.92 0.93 0.38 1.64

 HUB 36.95 10.32 6.50 3.82 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 329.8200 163.5220 286.4294 1105.3082 0.2984 -0.1930 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8666 7.4038 516.3187 504.9152 33.7744 29.7220 33.0000 3.2780

 

NASA/TM—2013-218094 L–173
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.3572 67.2167 286.5800 1107.1569 0.2659 0.0338 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8644 7.4927 518.0502 504.3112 410.5396 0.0258 0.3114

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.2619 0.0000 286.2619 1107.4985 0.2585 0.2260 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5084 518.3757 504.2630 0.0000 0.0600 0.0403 0.0735

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8851 7.8586 1.0484 524.8370 7.6335 257.4180 1.9955

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 48405.250 0.426 86.911 323915.125 0.651831E-02

 

Melt Ratio at Stator LE, Throat, TE

0.59726E+00 0.65563E+00 0.82656E+00

 trTOT = 1.1141 Tt4 = 524.8370 T1 = 471.0680

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 339244.06 609.1102 79.5915 1.4053 0.8525 14.2790 1.1141 37.3740

NASA/TM—2013-218094 L–174
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.451 EfDer = 0.994 SH = 0.192363E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.047 1974.130 6.513 481.862 1.000 1.000 0.980

 W Kg/sec = 18.203 Wdry = 39.969 WH2O = 0.077 lbm/sec H2O = 1.107g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.119 2048.185 1.379 0.250 53.411 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 67030.797 31398.697 3.257 831.557 255.316 619.754 2.427

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 193.46 -0.07 193.46 0.18 0.38 368.73

 MEAN 17.06 0.00 -0.02 193.46 -0.07 193.46 0.18 0.33

 HUB 12.51 0.00 -0.02 193.46 -0.07 193.46 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.44 50.47 10.97 355.40 404.71 6.37 478.87 472.84 37.88

 MEAN 56.65 47.20 9.45 293.90 351.92 6.37 478.87 472.84 37.88

 HUB 48.10 38.62 9.48 215.52 289.66 6.37 478.87 472.84 37.88

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 339.75 213.24 264.50 1071.76 0.32 7.29 6.52 16.04

 MEAN 18.04 352.17 230.39 266.35 1070.25 0.33 7.43 6.80 12.53

 HUB 15.00 392.57 285.51 269.43 1067.98 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.40 300.29 142.17 0.28 4400.48 0.92 0.91

 MEAN 310.72 278.20 80.32 0.26 4156.51 0.92 0.91 0.91 1.43

 HUB 258.41 270.79 27.10 0.25 4283.56 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.60 493.98 1.03 484.75 482.79 38.95

 MEAN 7.04 1.08 6.54 493.31 1.02 483.40 482.62 40.82

 HUB 7.06 1.08 6.44 493.66 1.02 481.34 483.51 43.82

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.88 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.86 16.78 12.70 4.08 0.94 0.36 2.22

 HUB 46.66 -5.74 -9.30 3.56 0.94 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 366.9145 229.9455 285.9219 1069.6212 0.3430 -0.0586 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0506 6.5072 482.9061 483.2718 42.6985 38.8071 35.4000 -3.4071

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 288.7137 70.6282 279.9415 1074.1272 0.2688 0.3437 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0480 6.7079 486.9994 482.3972 554.9116 0.0149 0.4429

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 286.6344 0.0000 286.6344 1074.2074 0.2668 0.3545 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6998 487.0965 483.1444 0.0000 0.0600 0.0406 0.3284

NASA/TM—2013-218094 L–175
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8723 7.0344 1.0801 493.6512 11.7905 198.9560 1.5423

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73860.477 0.585 167.151 404530.969 0.287244E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.626 EfDer = 0.999 SH = 0.374473E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.047 1974.130 7.034 493.650 1.000 1.000 0.980

 W Kg/sec = 18.203 Wdry = 39.897 WH2O = 0.150 lbm/sec H2O = 2.240g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.641 2023.596 1.377 0.251 53.470 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64489.066 31376.070 2.465 590.487 239.519 468.502 1.956

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.10 -0.09 262.10 0.24 0.41 362.89

 MEAN 18.08 0.00 -0.02 262.10 -0.09 262.10 0.24 0.38

 HUB 15.21 0.00 -0.02 262.10 -0.09 262.10 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.49 46.36 7.13 354.03 440.56 6.75 488.19 485.27 52.93

 MEAN 49.93 42.30 7.63 311.44 407.12 6.75 488.19 485.27 52.93

 HUB 45.00 37.84 7.16 262.03 370.68 6.75 488.19 485.27 52.93

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.47 153.93 282.22 1081.66 0.30 2.33 2.04 9.02

 MEAN 18.01 327.97 165.14 283.36 1080.78 0.30 2.40 2.13 7.35

 HUB 15.22 354.47 211.23 284.66 1079.93 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.79 344.67 197.85 0.32 3145.14 0.92 0.91

 MEAN 310.27 318.36 145.12 0.29 2975.88 0.92 0.91 0.91 1.39

 HUB 262.25 289.20 51.03 0.27 3216.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.45 1.06 7.02 502.27 1.02 494.05 490.85 45.17

 MEAN 7.43 1.06 6.98 501.80 1.02 493.25 490.75 46.37

 HUB 7.46 1.06 6.93 502.46 1.02 492.47 491.57 47.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.61 35.03 31.50 3.53 0.93 0.34 1.40

 MEAN 30.23 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.58 10.16 6.50 3.66 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.8239 165.6081 319.4483 1079.2552 0.3334 -0.1617 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4443 6.9015 491.8878 491.6295 48.8411 27.4031 30.6000 3.1969

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 313.6006 66.4856 306.4719 1081.9622 0.2898 0.1072 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4422 7.0273 494.3616 490.8492 491.5697 0.0143 0.2626

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 324.7405 0.0000 324.7405 1081.3324 0.3003 0.1568 0.5911

NASA/TM—2013-218094 L–176
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9866 493.7977 491.3361 0.0000 0.0600 0.0401 0.0210

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8725 7.4300 1.0562 502.1758 8.5263 247.9996 1.9225

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 53654.996 0.434 121.425 373131.375 0.408623E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.729 EfDer = 0.996 SH = 0.450858E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.047 1974.130 7.430 502.175 1.000 1.000 0.980

 W Kg/sec = 18.203 Wdry = 39.866 WH2O = 0.181 lbm/sec H2O = 2.792g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.958 2006.347 1.376 0.252 53.495 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62275.813 31366.539 2.384 545.479 228.831 424.468 1.855

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 273.99 -0.09 273.99 0.25 0.41 351.39

 MEAN 17.74 0.00 -0.02 273.99 -0.09 273.99 0.25 0.38

 HUB 15.05 0.00 -0.02 273.99 -0.09 273.99 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.61 46.36 5.25 345.76 441.23 7.11 496.22 491.56 48.56

 MEAN 48.13 43.40 4.73 305.59 410.51 7.11 496.22 491.56 48.56

 HUB 43.43 38.84 4.59 259.27 377.29 7.11 496.22 491.56 48.56

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 323.86 132.86 295.36 1089.16 0.30 2.26 1.98 8.75

 MEAN 17.51 331.31 148.69 296.07 1088.65 0.30 2.34 2.07 6.78

 HUB 14.85 358.82 201.38 296.98 1088.16 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 341.28 361.48 208.41 0.33 2633.92 0.92 0.91

 MEAN 301.59 333.23 152.90 0.31 2604.73 0.92 0.91 0.91 1.33

 HUB 255.83 301.93 54.44 0.28 2991.97 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.79 1.05 7.34 509.37 1.01 501.05 496.14 43.11

 MEAN 7.79 1.05 7.31 509.29 1.01 500.59 496.25 43.75

 HUB 7.84 1.06 7.28 510.35 1.02 500.14 497.27 44.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 24.22 35.21 31.50 3.71 0.93 0.29 1.40

 MEAN 26.67 27.31 23.50 3.81 0.92 0.30 1.62

 HUB 34.14 10.39 6.50 3.89 0.92 0.34 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.5093 149.6660 333.4624 1086.9764 0.3363 -0.1743 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8021 7.2243 499.0821 497.2089 46.2178 24.1717 31.5000 7.3283

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 332.9951 72.6406 324.9755 1088.9326 0.3058 0.0123 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7973 7.3158 500.8831 496.6234 451.3937 0.0196 0.2205

 

NASA/TM—2013-218094 L–177
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 338.7316 0.0000 338.7316 1088.5917 0.3112 0.1021 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2833 500.5788 497.0091 0.0000 0.0600 0.0544 -0.0530

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8463 7.7800 1.0471 509.6720 7.4973 267.8968 2.0767

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47295.367 0.406 107.032 375883.313 0.489448E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 2.162 EfDer = 0.978 SH = 0.536871E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.047 1974.130 7.780 509.671 1.000 1.000 0.980

 W Kg/sec = 18.203 Wdry = 39.832 WH2O = 0.215 lbm/sec H2O = 3.423g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.005 1991.538 1.374 0.253 53.522 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60489.992 31355.785 2.330 513.330 220.278 395.845 1.797

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 282.80 -0.10 282.80 0.26 0.40 334.72

 MEAN 16.97 0.00 -0.02 282.80 -0.10 282.80 0.26 0.37

 HUB 14.32 0.00 -0.02 282.80 -0.10 282.80 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.57 46.36 3.21 331.80 436.04 7.43 503.34 497.08 45.79

 MEAN 45.96 43.80 2.16 292.36 406.83 7.43 503.34 497.08 45.79

 HUB 41.11 37.84 3.27 246.70 375.35 7.43 503.34 497.08 45.79

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.26 109.59 304.12 1095.50 0.30 2.16 1.89 8.34

 MEAN 16.57 330.12 127.46 304.53 1095.25 0.30 2.24 1.97 6.35

 HUB 13.89 355.78 182.92 305.15 1095.00 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 325.26 372.83 215.67 0.34 2070.90 0.92 0.89

 MEAN 285.53 343.11 158.07 0.31 2114.11 0.92 0.89 0.89 1.27

 HUB 239.29 310.31 56.37 0.28 2542.21 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.07 1.04 7.60 515.31 1.01 507.05 500.62 41.99

 MEAN 8.07 1.04 7.59 515.43 1.01 506.81 500.80 42.29

 HUB 8.13 1.05 7.57 516.60 1.01 506.58 501.82 42.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.82 35.34 31.50 3.84 0.93 0.23 1.40

 MEAN 22.71 27.43 23.50 3.93 0.91 0.25 1.62

 HUB 30.94 10.47 6.50 3.97 0.91 0.30 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.978 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.4243 128.1736 334.7230 1093.9291 0.3276 -0.1424 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0857 7.5162 505.6196 501.6103 44.0901 20.9531 32.4000 11.4469

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 340.9760 76.4709 332.2903 1094.9659 0.3114 -0.0510 2.2705

 

NASA/TM—2013-218094 L–178
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0771 7.5606 506.5820 501.2886 432.2457 0.0271 0.1841

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 338.6637 0.0000 338.6637 1095.0823 0.3093 0.0489 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5441 506.6959 501.3982 0.0000 0.0600 0.0772 -0.0837

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7857 8.0518 1.0349 515.7623 6.1091 307.2551 2.3818

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38638.281 0.365 87.441 389545.188 0.570404E-02

 

Melt Ratio at Stator LE, Throat, TE

0.79800E-01 0.10063E+00 0.16880E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.212 EfDer = 0.947 SH = 0.602277E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.047 1974.130 8.052 515.754 1.000 1.000 0.980

 W Kg/sec = 18.203 Wdry = 39.805 WH2O = 0.241 lbm/sec H2O = 3.932g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.905 1979.745 1.374 0.253 53.544 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59083.375 31347.584 2.379 509.668 214.200 384.739 1.796

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 278.21 -0.10 278.21 0.25 0.38 316.50

 MEAN 15.91 0.00 -0.02 278.21 -0.10 278.21 0.25 0.36

 HUB 13.07 0.00 -0.02 278.21 -0.10 278.21 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.61 47.36 1.25 315.61 420.80 7.71 509.64 500.95 42.00

 MEAN 44.59 44.80 -0.21 274.14 390.65 7.71 509.64 500.95 42.00

 HUB 39.00 38.84 0.16 225.16 357.97 7.71 509.64 500.95 42.00

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.37 94.37 299.87 1101.32 0.29 2.05 1.78 7.43

 MEAN 15.50 319.69 109.75 300.26 1101.06 0.29 2.13 1.86 5.75

 HUB 12.59 341.20 160.90 300.88 1100.80 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 309.06 368.80 214.69 0.33 1694.75 0.92 0.87

 MEAN 266.99 338.94 157.23 0.31 1702.43 0.92 0.87 0.87 1.25

 HUB 216.89 306.05 56.00 0.28 2026.95 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.28 1.03 7.84 520.35 1.01 512.55 503.66 38.93

 MEAN 8.28 1.03 7.82 520.37 1.01 512.30 503.77 39.21

 HUB 8.33 1.03 7.80 521.26 1.01 512.06 504.55 39.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 17.47 35.60 31.50 4.10 0.93 0.20 1.40

 MEAN 20.08 27.64 23.50 4.14 0.90 0.22 1.64

 HUB 28.14 10.54 6.50 4.04 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.947 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 360.6823 111.7651 342.9289 1098.9733 0.3282 -0.2460 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2888 7.7034 510.3825 504.7577 41.5887 18.0515 33.0000 14.9485

 

NASA/TM—2013-218094 L–179
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 356.0479 81.3038 346.6407 1099.2467 0.3239 -0.2604 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2646 7.6945 510.6373 504.6336 410.5396 0.0705 0.1519

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 346.3244 0.0000 346.3244 1099.7977 0.3149 0.0147 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7120 511.1516 504.4967 0.0000 0.0600 0.1002 -0.2239

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7047 8.2503 1.0247 520.6173 4.9050 357.5424 2.7716

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31076.934 0.325 70.329 412843.719 0.620459E-02

 

Melt Ratio at Stator LE, Throat, TE

0.46202E+00 0.49682E+00 0.60378E+00

 trTOT = 1.0804 Tt4 = 520.6173 T1 = 481.8623

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 244526.06 553.3781 87.1193 1.2668 0.8287 9.4513 1.0804 37.3740

NASA/TM—2013-218094 L–180
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.837 EfDer = 0.999 SH = 0.268347E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1806.825 7.939 496.979 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.333 WH2O = 0.133 lbm/sec H2O = 1.822g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 89.651 1845.881 1.378 0.250 53.435 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70157.461 38772.156 3.163 831.557 262.871 619.754 2.358

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.49 -0.07 202.49 0.19 0.35 332.31

 MEAN 17.06 0.00 -0.02 202.49 -0.07 202.49 0.19 0.31

 HUB 12.51 0.00 -0.02 202.49 -0.07 202.49 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.10 50.47 7.63 325.28 383.22 7.75 493.71 484.83 34.80

 MEAN 53.04 47.20 5.84 269.00 336.74 7.75 493.71 484.83 34.80

 HUB 44.26 38.62 5.64 197.25 282.73 7.75 493.71 484.83 34.80

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.78 174.75 279.67 1085.43 0.30 7.29 6.52 16.04

 MEAN 18.04 344.47 199.43 280.88 1084.55 0.32 7.43 6.80 12.53

 HUB 15.00 387.86 264.77 283.44 1082.81 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 325.28 317.61 150.53 0.29 3606.63 0.92 0.91

 MEAN 284.38 293.44 84.96 0.27 3598.07 0.92 0.91 0.91 1.28

 HUB 236.51 284.84 28.26 0.26 3972.40 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.92 506.05 1.02 497.38 492.71 38.05

 MEAN 8.43 1.06 7.87 506.03 1.02 496.56 492.94 39.05

 HUB 8.48 1.07 7.77 506.97 1.02 494.97 494.19 41.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.00 28.29 24.20 4.09 0.93 0.30 1.80

 MEAN 35.38 16.83 12.70 4.13 0.92 0.27 2.22

 HUB 43.05 -5.69 -9.30 3.61 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.4378 199.0403 301.6956 1083.7706 0.3335 -0.0729 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4437 7.8274 495.9501 493.6543 40.9327 33.4144 35.4000 1.9856

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 306.6828 75.0240 297.3646 1086.9313 0.2822 0.2355 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4415 7.9945 498.8634 493.0194 554.9116 0.0136 0.3547

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 304.3904 0.0000 304.3904 1087.0327 0.2800 0.2596 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9874 498.9769 493.7507 0.0000 0.0600 0.0380 0.2234

NASA/TM—2013-218094 L–181
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8723 8.4270 1.0615 506.3469 9.3690 220.8637 1.7121

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58863.012 0.556 164.542 488925.938 0.381195E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.408 EfDer = 0.989 SH = 0.481615E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1806.825 8.427 506.346 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.227 WH2O = 0.238 lbm/sec H2O = 3.352g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.254 1828.732 1.375 0.252 53.505 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68447.930 38739.328 2.359 590.487 250.287 468.502 1.872

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.18 -0.10 278.18 0.26 0.39 327.94

 MEAN 18.08 0.00 -0.02 278.18 -0.10 278.18 0.26 0.37

 HUB 15.21 0.00 -0.02 278.18 -0.10 278.18 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.36 46.36 3.00 324.02 427.13 8.06 500.21 495.87 50.26

 MEAN 45.71 42.30 3.41 285.05 398.36 8.06 500.21 495.87 50.26

 HUB 40.78 37.84 2.94 239.82 367.35 8.06 500.21 495.87 50.26

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.01 108.83 303.06 1091.94 0.29 2.33 2.04 9.02

 MEAN 18.01 329.25 127.94 303.37 1091.76 0.30 2.40 2.13 7.35

 HUB 15.22 355.75 184.96 303.89 1091.58 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.97 370.51 213.14 0.34 2224.28 0.92 0.90

 MEAN 283.97 341.14 156.03 0.31 2306.01 0.92 0.90 0.90 1.26

 HUB 240.03 308.84 55.07 0.28 2817.07 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.74 1.04 8.23 511.90 1.01 503.69 499.58 46.50

 MEAN 8.75 1.04 8.22 512.11 1.01 503.52 499.81 46.73

 HUB 8.82 1.05 8.21 513.38 1.01 503.36 500.92 46.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.75 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.87 27.22 23.50 3.72 0.92 0.24 1.63

 HUB 31.33 10.27 6.50 3.77 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.7334 128.3040 342.4894 1089.9368 0.3356 -0.1922 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7642 8.1180 501.8705 500.8277 49.4956 20.5370 30.6000 10.0630

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 338.1901 71.6987 330.5024 1091.5999 0.3098 -0.0361 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7562 8.2017 503.4055 500.2984 491.5697 0.0247 0.1666

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 350.8033 0.0000 350.8033 1090.8401 0.3216 0.0315 0.5911

NASA/TM—2013-218094 L–182
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1383 502.7134 500.7732 0.0000 0.0600 0.0688 -0.1518

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8067 8.7320 1.0362 512.4567 6.1186 299.1448 2.3190

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38636.926 0.373 108.004 453813.656 0.515886E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.19685E-01 0.27586E-01 0.61783E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.050 EfDer = 0.951 SH = 0.548420E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1806.825 8.732 512.452 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.194 WH2O = 0.271 lbm/sec H2O = 3.892g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.771 1817.798 1.374 0.253 53.526 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67130.945 38729.004 2.244 545.479 243.110 424.468 1.746

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 295.36 -0.10 295.36 0.27 0.40 318.37

 MEAN 17.74 0.00 -0.02 295.36 -0.10 295.36 0.27 0.37

 HUB 15.05 0.00 -0.02 295.36 -0.10 295.36 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.98 46.36 0.62 316.45 432.95 8.31 505.55 500.43 48.07

 MEAN 43.45 43.40 0.05 279.69 406.84 8.31 505.55 500.43 48.07

 HUB 38.79 38.84 -0.05 237.30 378.94 8.31 505.55 500.43 48.07

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.30 83.72 322.61 1096.27 0.30 2.26 1.98 8.75

 MEAN 17.51 340.19 108.60 322.39 1096.53 0.31 2.34 2.07 6.78

 HUB 14.85 366.51 174.16 322.49 1096.78 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 312.35 395.41 228.63 0.36 1660.61 0.92 0.87

 MEAN 276.03 363.27 167.44 0.33 1902.99 0.92 0.87 0.87 1.20

 HUB 234.15 328.02 59.99 0.30 2587.81 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.96 1.03 8.41 516.58 1.01 507.80 503.15 45.50

 MEAN 8.99 1.03 8.42 517.19 1.01 508.04 503.54 45.15

 HUB 9.09 1.04 8.42 518.89 1.01 508.27 504.83 44.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.55 35.32 31.50 3.82 0.93 0.16 1.40

 MEAN 18.62 27.45 23.50 3.95 0.90 0.19 1.62

 HUB 28.37 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.951 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 379.8801 109.3113 363.8130 1094.4636 0.3471 -0.2066 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0071 8.2992 506.1404 504.6379 47.9495 16.7234 31.5000 14.7766

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 365.6349 79.7608 356.8292 1095.3652 0.3338 -0.1428 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9912 8.3343 506.9738 504.3038 451.3937 0.0369 0.1221

 

NASA/TM—2013-218094 L–183
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 372.8033 0.0000 372.8033 1094.8881 0.3405 -0.0333 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2757 506.5367 504.5299 0.0000 0.0600 0.0991 -0.2415

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6939 8.9542 1.0254 517.5217 5.1030 339.0038 2.6279

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 32282.018 0.331 90.239 459610.813 0.567429E-02

 

Melt Ratio at Stator LE, Throat, TE

0.30465E+00 0.33740E+00 0.43109E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.007 EfDer = 0.894 SH = 0.585066E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1806.825 8.954 517.512 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.176 WH2O = 0.289 lbm/sec H2O = 4.201g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.115 1808.881 1.374 0.253 53.538 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66349.148 38723.328 2.154 513.330 238.301 395.845 1.661

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 310.20 -0.11 310.20 0.28 0.40 304.02

 MEAN 16.97 0.00 -0.02 310.20 -0.11 310.20 0.28 0.37

 HUB 14.32 0.00 -0.02 310.20 -0.11 310.20 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.40 46.36 -1.96 303.68 434.18 8.48 509.91 503.58 44.45

 MEAN 40.79 43.80 -3.01 267.59 409.74 8.48 509.91 503.58 44.45

 HUB 36.06 37.84 -1.78 225.79 383.74 8.48 509.91 503.58 44.45

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 342.89 56.67 338.17 1099.53 0.31 2.16 1.89 8.34

 MEAN 16.57 348.08 84.99 337.55 1100.13 0.32 2.24 1.97 6.35

 HUB 13.89 371.60 155.72 337.40 1100.72 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 297.69 415.27 241.02 0.38 1072.07 0.92 0.82

 MEAN 261.33 380.83 176.34 0.35 1410.44 0.92 0.82 0.82 1.14

 HUB 219.01 343.28 63.29 0.31 2164.51 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.09 1.02 8.51 520.17 1.01 510.88 505.42 43.41

 MEAN 9.14 1.02 8.54 521.01 1.01 511.44 505.87 42.64

 HUB 9.24 1.03 8.55 522.89 1.01 511.98 507.14 41.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.51 35.48 31.50 3.98 0.93 0.09 1.40

 MEAN 14.13 27.58 23.50 4.08 0.89 0.13 1.62

 HUB 24.78 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.894 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 381.5075 85.4687 371.8105 1098.4139 0.3473 -0.1696 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1496 8.4298 509.8500 506.7896 44.7470 12.9458 32.4000 19.4542

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 381.2625 85.5060 371.5505 1098.4221 0.3471 -0.1983 2.2705

 

NASA/TM—2013-218094 L–184
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1260 8.4078 509.8562 506.7557 432.2457 0.0478 0.0858

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 379.5848 0.0000 379.5848 1098.5010 0.3455 -0.0850 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3686 509.9308 506.6803 0.0000 0.0600 0.1285 -0.2611

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5003 9.0756 1.0136 521.3087 3.8428 416.6091 3.2295

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 24333.619 0.275 68.021 478813.281 0.595498E-02

 

Melt Ratio at Stator LE, Throat, TE

0.71296E+00 0.74570E+00 0.84193E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.845 EfDer = 0.831 SH = 0.605555E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.466 1806.825 9.076 521.295 1.000 1.000 0.980

 W Kg/sec = 22.484 Wdry = 49.166 WH2O = 0.300 lbm/sec H2O = 4.376g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.322 1802.298 1.374 0.253 53.545 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65933.898 38720.152 2.160 509.668 236.002 384.739 1.630

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 310.48 -0.11 310.48 0.28 0.38 288.13

 MEAN 15.91 0.00 -0.02 310.48 -0.11 310.48 0.28 0.36

 HUB 13.07 0.00 -0.02 310.48 -0.11 310.48 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.95 47.36 -4.41 288.86 424.14 8.60 513.69 505.41 40.58

 MEAN 38.95 44.80 -5.85 250.91 399.26 8.60 513.69 505.41 40.58

 HUB 33.59 38.84 -5.25 206.08 372.71 8.60 513.69 505.41 40.58

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 341.24 38.80 339.03 1102.67 0.31 2.05 1.78 7.43

 MEAN 15.50 344.75 65.91 338.39 1103.33 0.31 2.13 1.86 5.75

 HUB 12.59 364.02 134.42 338.29 1103.96 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.87 417.74 244.07 0.38 698.06 0.92 0.76

 MEAN 244.36 382.56 178.45 0.35 1023.11 0.92 0.76 0.76 1.11

 HUB 198.51 344.31 64.09 0.31 1693.76 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.16 1.01 8.58 523.02 1.00 513.83 506.85 40.80

 MEAN 9.20 1.01 8.61 523.83 1.00 514.45 507.24 40.01

 HUB 9.28 1.02 8.62 525.50 1.01 515.04 508.29 39.22

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.53 35.75 31.50 4.25 0.93 0.05 1.40

 MEAN 11.02 27.80 23.50 4.30 0.87 0.09 1.64

 HUB 21.67 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.831 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 393.6943 67.1163 387.9312 1100.5654 0.3577 -0.2817 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2016 8.4363 511.8837 508.5747 43.4170 9.8156 33.0000 23.1844

 

NASA/TM—2013-218094 L–185
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 406.2094 92.7583 395.4770 1099.7153 0.3694 -0.4345 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1466 8.3383 511.0959 508.8910 410.5396 0.1102 0.0582

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 395.0504 0.0000 395.0504 1100.4709 0.3590 -0.0971 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3619 511.8028 508.8167 0.0000 0.0600 0.1438 -0.3958

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2785 9.1261 1.0056 524.1158 2.8199 523.5421 4.0585

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17868.723 0.223 49.949 509690.469 0.634116E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0546 Tt4 = 524.1158 T1 = 496.9790

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES 

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 171984.30 480.7556 89.6513 1.1495 0.7084 5.8368 1.0546 37.3740

NASA/TM—2013-218094 L–186
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 7.226 EfDer = 1.000 SH = 0.377960E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.699 1592.219 9.337 510.149 1.000 1.000 0.980

 W Kg/sec = 21.681 Wdry = 47.519 WH2O = 0.180 lbm/sec H2O = 2.955g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.474 1605.484 1.376 0.251 53.471 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58759.887 37371.137 3.805 831.557 218.521 619.754 2.836

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 169.59 -0.06 169.59 0.15 0.30 289.03

 MEAN 17.06 0.00 -0.02 169.59 -0.06 169.59 0.15 0.27

 HUB 12.51 0.00 -0.02 169.59 -0.06 169.59 0.15 0.22

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.40 50.47 8.93 286.65 333.11 9.19 507.86 495.24 33.57

 MEAN 54.43 47.20 7.23 237.05 291.51 9.19 507.86 495.24 33.57

 HUB 45.72 38.62 7.10 173.82 242.89 9.19 507.86 495.24 33.57

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 284.37 160.57 234.70 1099.98 0.26 7.29 6.52 16.04

 MEAN 18.04 296.19 179.58 235.54 1099.22 0.27 7.43 6.80 12.53

 HUB 15.00 331.90 232.21 237.14 1097.88 0.30 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 286.65 266.42 126.08 0.24 3313.74 0.92 0.91

 MEAN 250.61 246.02 71.02 0.22 3239.96 0.92 0.91 0.91 1.33

 HUB 208.42 238.33 23.78 0.22 3483.82 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.35 517.43 1.01 511.00 501.42 35.57

 MEAN 9.78 1.05 9.31 517.27 1.01 510.30 501.52 36.33

 HUB 9.81 1.05 9.22 517.81 1.02 509.06 502.34 37.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.38 28.24 24.20 4.04 0.93 0.33 1.80

 MEAN 37.32 16.78 12.70 4.08 0.93 0.30 2.22

 HUB 44.40 -5.73 -9.30 3.57 0.93 0.19 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 309.7457 179.2344 252.6211 1098.6476 0.2819 -0.0672 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7903 9.2732 509.8652 502.0207 37.5203 35.3557 35.4000 0.0443

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 257.6876 63.0382 249.8581 1101.1241 0.2340 0.2634 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7898 9.4259 512.1810 501.4330 554.9116 0.0111 0.3818

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.5613 0.0000 255.5613 1101.1445 0.2321 0.2901 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4232 512.2147 502.0565 0.0000 0.0600 0.0366 0.2579

NASA/TM—2013-218094 L–187
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8897 9.7770 1.0471 517.3922 7.3542 213.0297 1.6514

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46366.926 0.564 124.982 460044.156 0.488743E-02

 

Melt Ratio at Stator LE, Throat, TE

0.73424E+00 0.83809E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.724 EfDer = 0.996 SH = 0.638085E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.699 1592.219 9.777 517.389 1.000 1.000 0.980

 W Kg/sec = 21.681 Wdry = 47.395 WH2O = 0.304 lbm/sec H2O = 5.089g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.627 1594.230 1.373 0.253 53.555 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57607.160 37332.371 2.805 590.487 210.481 468.502 2.226

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 234.12 -0.08 234.12 0.21 0.34 285.89

 MEAN 18.08 0.00 -0.02 234.12 -0.08 234.12 0.21 0.31

 HUB 15.21 0.00 -0.02 234.12 -0.08 234.12 0.21 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.66 46.36 4.30 285.54 369.31 9.48 513.07 504.95 48.23

 MEAN 47.02 42.30 4.72 251.19 343.44 9.48 513.07 504.95 48.23

 HUB 42.08 37.84 4.24 211.34 315.45 9.48 513.07 504.95 48.23

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 276.05 104.32 255.58 1104.98 0.25 2.33 2.04 9.02

 MEAN 18.01 282.19 118.93 255.91 1104.71 0.26 2.40 2.13 7.35

 HUB 15.22 305.04 165.32 256.35 1104.46 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 283.73 312.26 179.41 0.28 2131.81 0.92 0.91

 MEAN 250.24 287.63 131.31 0.26 2143.46 0.92 0.91 0.91 1.29

 HUB 211.52 260.48 46.20 0.24 2517.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.08 1.03 9.66 522.06 1.01 516.05 508.14 45.82

 MEAN 10.08 1.03 9.64 522.09 1.01 515.81 508.26 46.14

 HUB 10.13 1.04 9.62 522.91 1.01 515.57 509.03 46.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 22.20 35.07 31.50 3.57 0.93 0.26 1.40

 MEAN 24.93 27.16 23.50 3.66 0.92 0.27 1.63

 HUB 32.82 10.22 6.50 3.72 0.92 0.31 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 311.7185 119.2681 287.9991 1103.4813 0.2825 -0.1802 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0905 9.5565 514.6945 509.0356 48.0286 22.4958 30.6000 8.1042

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 284.6541 60.3487 278.1833 1104.8370 0.2576 0.0063 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0870 9.6405 515.9668 508.6331 491.5697 0.0176 0.1920

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 294.6316 0.0000 294.6316 1104.3398 0.2668 0.0655 0.5911

NASA/TM—2013-218094 L–188
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5915 515.5125 509.1456 0.0000 0.0600 0.0581 -0.1007

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8350 10.0685 1.0298 522.3496 4.9611 281.9450 2.1856

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31487.857 0.391 84.876 426707.281 0.692505E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 1.278 EfDer = 0.968 SH = 0.755272E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.699 1592.219 10.068 522.348 1.000 1.000 0.980

 W Kg/sec = 21.681 Wdry = 47.339 WH2O = 0.360 lbm/sec H2O = 6.122g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.885 1586.647 1.372 0.254 53.593 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56673.719 37314.809 2.654 545.479 205.522 424.468 2.065

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.34 -0.09 249.34 0.23 0.34 277.88

 MEAN 17.74 0.00 -0.02 249.34 -0.09 249.34 0.23 0.32

 HUB 15.05 0.00 -0.02 249.34 -0.09 249.34 0.23 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.21 46.36 1.85 278.87 374.15 9.73 517.46 509.58 49.92

 MEAN 44.68 43.40 1.28 246.47 350.66 9.73 517.46 509.58 49.92

 HUB 40.00 38.84 1.16 209.12 325.48 9.73 517.46 509.58 49.92

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 284.60 82.57 272.36 1108.54 0.26 2.26 1.98 8.75

 MEAN 17.51 290.87 102.10 272.37 1108.59 0.26 2.34 2.07 6.78

 HUB 14.85 314.01 155.97 272.54 1108.65 0.28 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 275.25 333.63 192.69 0.30 1637.38 0.92 0.89 

 MEAN 243.25 306.77 141.15 0.28 1788.94 0.92 0.89 0.89 1.22

 HUB 206.34 277.15 50.36 0.25 2317.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.30 1.02 9.84 525.92 1.01 519.56 512.14 48.46

 MEAN 10.32 1.02 9.84 526.25 1.01 519.61 512.39 48.38

 HUB 10.39 1.03 9.84 527.41 1.01 519.66 513.32 48.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.86 35.28 31.50 3.78 0.93 0.19 1.40

 MEAN 20.55 27.39 23.50 3.89 0.91 0.21 1.62

 HUB 29.78 10.47 6.50 3.97 0.91 0.27 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.968 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 323.0648 102.7700 306.2829 1107.1943 0.2918 -0.1944 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3295 9.7482 518.3336 513.2755 50.5056 18.5486 31.5000 12.9514

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 307.6478 67.1113 300.2386 1108.0034 0.2777 -0.0987 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3210 9.7933 519.0981 513.0313 451.3937 0.0272 0.1454

 

NASA/TM—2013-218094 L–189
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 313.0692 0.0000 313.0692 1107.7137 0.2826 -0.0019 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7470 518.8351 513.4150 0.0000 0.0600 0.0869 -0.1926

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7434 10.2916 1.0222 526.5278 4.1800 317.1704 2.4587

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 26623.080 0.351 71.763 432697.625 0.808859E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-1.814 EfDer = 0.918 SH = 0.870898E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.699 1592.219 10.292 526.526 1.000 1.000 0.980

 W Kg/sec = 21.681 Wdry = 47.283 WH2O = 0.415 lbm/sec H2O = 7.136g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.643 1580.339 1.370 0.255 53.631 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56065.246 37297.418 2.541 513.330 202.011 395.845 1.960

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 262.11 -0.09 262.11 0.24 0.34 265.61

 MEAN 16.97 0.00 -0.02 262.11 -0.09 262.11 0.24 0.32

 HUB 14.32 0.00 -0.02 262.11 -0.09 262.11 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 45.60 46.36 -0.76 267.61 374.66 9.91 521.15 513.54 51.42

 MEAN 41.99 43.80 -1.81 235.80 352.63 9.91 521.15 513.54 51.42

 HUB 37.22 37.84 -0.62 198.97 329.13 9.91 521.15 513.54 51.42

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 291.37 59.28 285.28 1111.31 0.26 2.16 1.89 8.34

 MEAN 16.57 296.50 81.66 285.04 1111.60 0.27 2.24 1.97 6.35

 HUB 13.89 317.48 139.79 285.04 1111.88 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 262.33 350.16 203.05 0.32 1121.04 0.92 0.84

 MEAN 230.29 321.46 148.63 0.29 1354.92 0.92 0.84 0.84 1.17

 HUB 193.00 289.97 53.21 0.26 1942.98 0.92 0.84

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.44 1.01 9.96 528.97 1.00 522.32 515.49 51.05

 MEAN 10.47 1.02 9.98 529.47 1.01 522.59 515.79 50.64

 HUB 10.55 1.03 9.98 530.75 1.01 522.86 516.72 50.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 11.74 35.44 31.50 3.94 0.93 0.12 1.40

 MEAN 15.99 27.54 23.50 4.04 0.89 0.16 1.62

 HUB 26.12 10.57 6.50 4.07 0.89 0.23 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.918 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 323.6249 82.1174 313.0332 1110.4363 0.2914 -0.1600 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4826 9.8946 521.5363 516.5862 52.4597 14.6991 32.4000 17.7009

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 320.3038 71.8348 312.1447 1110.6090 0.2884 -0.1569 2.2705

 

NASA/TM—2013-218094 L–190
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4688 9.8933 521.7050 516.5800 432.2457 0.0369 0.1074

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 318.4912 0.0000 318.4912 1110.6991 0.2867 -0.0585 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8602 521.7966 516.7507 0.0000 0.0600 0.1182 -0.2213

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5807 10.4270 1.0132 529.7309 3.2048 384.0265 2.9769

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 20482.127 0.298 55.210 451212.281 0.923689E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-4.660 EfDer = 0.858 SH = 0.987119E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.699 1592.219 10.427 529.729 1.000 1.000 0.980

 W Kg/sec = 21.681 Wdry = 47.228 WH2O = 0.471 lbm/sec H2O = 8.141g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.957 1575.554 1.369 0.256 53.668 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 55706.098 37279.875 2.547 509.668 200.133 384.739 1.922

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 262.30 -0.09 262.30 0.24 0.33 251.88

 MEAN 15.91 0.00 -0.02 262.30 -0.09 262.30 0.24 0.31

 HUB 13.07 0.00 -0.02 262.30 -0.09 262.30 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.15 47.36 -3.21 254.55 365.58 10.04 524.36 516.66 52.75

 MEAN 40.14 44.80 -4.66 221.11 343.12 10.04 524.36 516.66 52.75

 HUB 34.71 38.84 -4.13 181.60 319.09 10.04 524.36 516.66 52.75

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 289.07 43.80 285.73 1113.90 0.26 2.05 1.78 7.43

 MEAN 15.50 292.78 65.02 285.47 1114.23 0.26 2.13 1.86 5.75

 HUB 12.59 310.11 121.06 285.50 1114.55 0.28 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 249.27 351.94 205.47 0.32 787.41 0.92 0.78

 MEAN 215.34 322.63 150.32 0.29 1009.04 0.92 0.78 0.78 1.14

 HUB 174.93 290.54 53.87 0.26 1525.35 0.92 0.78

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.53 1.01 10.05 531.44 1.00 524.92 518.25 53.18

 MEAN 10.55 1.01 10.07 531.92 1.00 525.23 518.50 52.68

 HUB 10.62 1.02 10.07 533.04 1.01 525.53 519.28 52.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.71 35.72 31.50 4.22 0.93 0.08 1.40

 MEAN 12.83 27.77 23.50 4.27 0.88 0.12 1.64

 HUB 22.98 10.69 6.50 4.19 0.88 0.18 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.858 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 332.3166 66.2090 325.6542 1112.3760 0.2987 -0.2679 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5554 9.9349 523.5191 519.5959 55.5051 11.4922 33.0000 21.5078

 

NASA/TM—2013-218094 L–191
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 339.3025 77.4800 330.3378 1111.9832 0.3051 -0.3769 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.5211 9.8771 523.1550 519.8016 410.5396 0.0885 0.0777

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 330.4529 0.0000 330.4529 1112.4689 0.2970 -0.0788 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8861 523.6181 519.7850 0.0000 0.0600 0.1383 -0.3589

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3931 10.4962 1.0066 532.1303 2.4009 474.1541 3.6756

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 15397.004 0.248 41.503 481077.063 0.103980E-01

 

Melt Ratio at Stator LE, Throat, TE

 0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0431 Tt4 = 532.1303 T1 = 510.1488

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 140356.98 378.3334 74.4742 1.1241 0.7470 7.2256 1.0431 37.3740

NASA/TM—2013-218094 L–192
 5μm, 2g/m3

, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 Ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.675 EfDer = 0.953 SH = 0.130125E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.912 2483.351 4.265 477.912 1.000 1.000 0.980

 W Kg/sec = 11.778 Wdry = 25.878 WH2O = 0.034 lbm/sec H2O = 0.495g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.734 2587.131 1.380 0.249 53.390 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65632.930 20321.205 3.311 831.557 251.148 619.754 2.468

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 189.43 -0.07 189.43 0.18 0.46 465.75

 MEAN 17.06 0.00 -0.02 189.43 -0.07 189.43 0.18 0.39

 HUB 12.51 0.00 -0.02 189.43 -0.07 189.43 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.04 50.47 16.57 447.08 485.61 4.17 475.04 464.31 19.82

 MEAN 62.88 47.20 15.68 369.72 415.48 4.17 475.04 464.31 19.82

 HUB 55.06 38.62 16.44 271.11 330.78 4.17 475.04 464.31 19.82

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 400.12 309.72 253.32 1074.72 0.37 7.29 6.52 16.04

 MEAN 18.04 404.43 312.50 256.72 1071.52 0.38 7.43 6.80 12.53

 HUB 15.00 437.42 350.72 261.41 1067.61 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 447.08 288.17 137.36 0.27 6390.87 0.92 0.87

 MEAN 390.86 268.42 78.37 0.25 5637.31 0.92 0.87 0.87 1.78

 HUB 325.07 262.66 25.65 0.25 5261.58 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.93 1.16 4.48 500.11 1.05 487.28 479.32 18.34

 MEAN 4.84 1.14 4.40 497.49 1.04 484.38 478.15 20.29

 HUB 4.80 1.13 4.29 496.19 1.04 480.85 478.02 22.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.72 28.47 24.20 4.27 0.93 0.58 1.80

 MEAN 50.60 16.98 12.70 4.28 0.95 0.53 2.22

 HUB 53.30 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 416.0938 311.8899 275.4247 1071.0731 0.3885 -0.0351 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8533 4.3800 484.0800 478.7642 21.3571 48.5528 35.4000 -13.1528

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 273.1366 66.8176 264.8377 1079.7346 0.2530 0.5210 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8408 4.6330 491.9617 477.4951 554.9116 0.0367 0.6141

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 272.0848 0.0000 272.0848 1079.7498 0.2520 0.4890 1.3089

NASA/TM—2013-218094 L–193
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6115 492.0099 478.4286 0.0000 0.0600 0.0882 0.4751

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8112 4.8166 1.1294 497.9269 20.0159 166.7671 1.2928

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 125138.016 0.626 183.239 263135.219 0.247566E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.263 EfDer = 0.956 SH = 0.382036E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.912 2483.351 4.817 497.926 1.000 1.000 0.980

 W Kg/sec = 11.778 Wdry = 25.813 WH2O = 0.099 lbm/sec H2O = 1.556g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.482 2534.624 1.377 0.251 53.472 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61280.063 20300.973 2.598 590.487 227.312 468.502 2.061

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 249.04 -0.09 249.04 0.23 0.47 454.53

 MEAN 18.08 0.00 -0.02 249.04 -0.09 249.04 0.23 0.43

 HUB 15.21 0.00 -0.02 249.04 -0.09 249.04 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.79 46.36 14.43 445.35 510.33 4.64 492.99 481.42 30.55

 MEAN 57.56 42.30 15.26 391.78 464.31 4.64 492.99 481.42 30.55

 HUB 52.93 37.84 15.09 329.62 413.19 4.64 492.99 481.42 30.55

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 367.98 258.38 262.01 1094.00 0.34 2.33 2.04 9.02

 MEAN 18.01 367.18 254.45 264.72 1091.46 0.34 2.40 2.13 7.35

 HUB 15.22 388.70 281.80 267.73 1088.96 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 442.53 320.25 184.15 0.29 5277.82 0.92 0.87

 MEAN 390.30 297.54 135.85 0.27 4584.09 0.92 0.87 0.87 1.72

 HUB 329.90 272.02 48.10 0.25 4291.16 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.12 5.00 516.11 1.04 505.35 491.34 21.59

 MEAN 5.32 1.11 4.93 513.72 1.03 503.00 490.37 23.26

 HUB 5.29 1.10 4.85 512.71 1.03 500.70 490.36 25.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.60 35.10 31.50 3.60 0.93 0.55 1.40

 MEAN 43.87 27.17 23.50 3.67 0.95 0.53 1.63

 HUB 46.47 10.19 6.50 3.69 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 392.3168 255.1592 298.0038 1090.2664 0.3598 -0.1052 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3349 4.8853 501.9557 491.0972 24.2666 40.5711 30.6000 -9.9711

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 288.0955 61.0783 281.5466 1096.3595 0.2628 0.3767 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3282 5.0825 507.5898 489.6322 491.5697 0.0263 0.4720

 

NASA/TM—2013-218094 L–194
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 298.6786 0.0000 298.6786 1095.8081 0.2726 0.3619 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0481 507.0981 490.1649 0.0000 0.0600 0.0683 0.2931

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8285 5.3109 1.1026 514.1827 16.2572 187.3820 1.4526

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 102329.727 0.523 149.841 239133.094 0.439095E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.289 EfDer = 0.972 SH = 0.519522E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.912 2483.351 5.311 514.182 1.000 1.000 0.980

 W Kg/sec = 11.778 Wdry = 25.777 WH2O = 0.135 lbm/sec H2O = 2.258g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.407 2494.236 1.375 0.252 53.517 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57433.883 20289.861 2.601 545.479 209.679 424.468 2.024

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 252.68 -0.09 252.68 0.23 0.46 436.84

 MEAN 17.74 0.00 -0.02 252.68 -0.09 252.68 0.23 0.42

 HUB 15.05 0.00 -0.02 252.68 -0.09 252.68 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.85 46.36 13.49 434.94 503.09 5.12 509.13 491.17 24.54

 MEAN 56.69 43.40 13.29 384.42 460.10 5.12 509.13 491.17 24.54

 HUB 52.24 38.84 13.40 326.15 412.65 5.12 509.13 491.17 24.54

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 359.48 242.06 265.77 1109.93 0.32 2.26 1.98 8.75

 MEAN 17.51 360.76 241.32 268.16 1107.76 0.33 2.34 2.07 6.78

 HUB 14.85 384.28 272.64 270.81 1105.63 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 429.31 325.10 187.24 0.29 4797.04 0.92 0.89

 MEAN 379.39 301.62 138.07 0.27 4226.28 0.92 0.89 0.89 1.67

 HUB 321.82 275.24 49.18 0.25 4050.02 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.89 1.11 5.48 530.64 1.03 520.41 499.63 18.51

 MEAN 5.82 1.10 5.41 528.68 1.03 518.38 498.94 19.64

 HUB 5.79 1.09 5.34 528.08 1.03 516.39 499.14 20.82

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 42.33 35.17 31.50 3.67 0.93 0.52 1.40

 MEAN 41.98 27.24 23.50 3.74 0.94 0.51 1.62

 HUB 45.19 10.29 6.50 3.79 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 387.0973 242.9065 301.3979 1106.5313 0.3498 -0.1132 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8280 5.3630 517.2838 499.6839 20.4837 38.8665 31.5000 -7.3665

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 296.3646 64.6499 289.2271 1111.7532 0.2666 0.3267 2.3726

 

NASA/TM—2013-218094 L–195
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8236 5.5478 522.1880 498.3616 451.3937 0.0204 0.4470

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 301.4240 0.0000 301.4240 1111.4700 0.2712 0.3480 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5249 521.9407 498.7748 0.0000 0.0600 0.0546 0.2724

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8503 5.8092 1.0938 529.1232 14.9531 192.5024 1.4923

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 94543.930 0.513 138.440 237763.359 0.589117E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.36768E-02 0.27261E-01 0.15483E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.720 EfDer = 0.982 SH = 0.664421E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.912 2483.351 5.809 529.116 1.000 1.000 0.980

 W Kg/sec = 11.778 Wdry = 25.740 WH2O = 0.172 lbm/sec H2O = 3.068g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.224 2458.770 1.373 0.253 53.564 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54039.625 20278.100 2.637 513.330 194.633 395.845 2.034

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 252.64 -0.09 252.64 0.23 0.44 413.25

 MEAN 16.97 0.00 -0.02 252.64 -0.09 252.64 0.23 0.40

 HUB 14.32 0.00 -0.02 252.64 -0.09 252.64 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.82 46.36 12.46 417.39 487.97 5.61 524.09 499.40 20.03

 MEAN 55.52 43.80 11.72 367.78 446.26 5.61 524.09 499.40 20.03

 HUB 50.86 37.84 13.02 310.33 400.23 5.61 524.09 499.40 20.03

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.81 222.23 264.95 1124.10 0.31 2.16 1.89 8.34

 MEAN 16.57 347.03 221.54 267.11 1122.14 0.31 2.24 1.97 6.35

 HUB 13.89 369.11 252.24 269.47 1120.22 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.15 324.25 186.92 0.29 4197.40 0.92 0.90

 MEAN 359.18 300.49 137.64 0.27 3673.27 0.92 0.90 0.90 1.63

 HUB 301.01 273.85 48.78 0.24 3504.84 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.35 1.09 5.95 543.44 1.03 534.02 506.14 15.60

 MEAN 6.28 1.08 5.88 541.65 1.02 532.16 505.54 16.41

 HUB 6.26 1.08 5.81 541.08 1.02 530.34 505.73 17.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.99 35.20 31.50 3.70 0.93 0.50 1.40

 MEAN 39.67 27.26 23.50 3.76 0.94 0.48 1.62

 HUB 43.11 10.26 6.50 3.76 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.982 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 368.0127 222.7872 292.9150 1121.2782 0.3282 -0.0895 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2892 5.8452 531.3793 506.0872 16.8445 37.2561 32.4000 -4.8561

 

NASA/TM—2013-218094 L–196
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 293.9662 65.9280 286.4780 1125.3237 0.2612 0.2883 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2868 6.0000 535.2278 505.0073 432.2457 0.0157 0.4259

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 291.5994 0.0000 291.5994 1125.3892 0.2591 0.3352 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9940 535.3026 505.1658 0.0000 0.0600 0.0446 0.2739

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8685 6.2749 1.0802 541.9985 12.9412 207.4708 1.6083

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 82155.680 0.491 120.300 243410.547 0.708750E-02

 

Melt Ratio at Stator LE, Throat, TE

0.68931E+00 0.79032E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.275 EfDer = 0.990 SH = 0.840365E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.912 2483.351 6.275 541.997 1.000 1.000 0.980

 W Kg/sec = 11.778 Wdry = 25.694 WH2O = 0.218 lbm/sec H2O = 4.100g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.051 2429.390 1.371 0.255 53.621 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51153.758 20263.750 2.792 509.668 182.558 384.739 2.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 240.86 -0.08 240.86 0.21 0.41 388.38

 MEAN 15.91 0.00 -0.02 240.86 -0.08 240.86 0.21 0.37

 HUB 13.07 0.00 -0.02 240.86 -0.08 240.86 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.76 47.36 11.40 397.02 464.44 6.08 537.45 506.44 17.45

 MEAN 55.08 44.80 10.28 344.86 420.71 6.08 537.45 506.44 17.45

 HUB 49.63 38.84 10.79 283.24 371.87 6.08 537.45 506.44 17.45

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 328.28 208.98 253.17 1136.65 0.29 2.05 1.78 7.43

 MEAN 15.50 326.53 203.59 255.28 1134.65 0.29 2.13 1.86 5.75

 HUB 12.59 342.75 226.18 257.53 1132.67 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.78 310.53 179.81 0.27 3750.55 0.92 0.91

 MEAN 335.85 287.51 132.26 0.25 3156.51 0.92 0.91 0.91 1.62

 HUB 272.84 261.72 46.66 0.23 2848.72 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.78 1.08 6.41 554.74 1.02 546.29 512.64 14.69

 MEAN 6.70 1.07 6.33 552.72 1.02 544.36 511.96 15.44

 HUB 6.66 1.06 6.26 551.68 1.02 542.47 511.89 16.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.54 35.38 31.50 3.88 0.93 0.49 1.40

 MEAN 38.57 27.39 23.50 3.89 0.94 0.46 1.64

 HUB 41.29 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 356.9638 207.3252 290.5846 1133.2120 0.3150 -0.1683 2.0437

 

NASA/TM—2013-218094 L–197
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7066 6.2697 543.0731 512.7065 16.1251 35.5070 33.0000 -2.5070

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 296.7556 67.7644 288.9150 1136.4066 0.2611 0.1756 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7043 6.4002 546.1558 511.9073 410.5396 0.0262 0.4013

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 288.7169 0.0000 288.7169 1136.7659 0.2540 0.3247 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4116 546.5265 512.3521 0.0000 0.0600 0.0388 0.2056

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 6.6995 1.0677 553.0466 11.0505 226.1682 1.7532

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 70594.094 0.467 103.370 255458.406 0.962266E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1572 Tt4 = 553.0466 T1 = 477.9123

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 474761.47 695.1902 85.7343 1.5710 0.8321 15.6754 1.1572 37.3740

NASA/TM—2013-218094 L–198
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.664 EfDer = 0.953 SH = 0.115771E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.054 2402.380 4.199 471.469 1.000 1.000 0.980

 W Kg/sec = 11.388 Wdry = 25.025 WH2O = 0.029 lbm/sec H2O = 0.440g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.618 2519.823 1.380 0.249 53.386 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 63523.379 19649.746 3.395 831.557 244.925 619.754 2.530 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 183.34 -0.06 183.34 0.17 0.45 453.63

 MEAN 17.06 0.00 -0.02 183.34 -0.06 183.34 0.17 0.38

 HUB 12.51 0.00 -0.02 183.34 -0.06 183.34 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.03 50.47 16.56 432.50 469.81 4.11 468.77 460.33 22.94

 MEAN 62.86 47.20 15.66 357.66 401.97 4.11 468.77 460.33 22.94

 HUB 55.05 38.62 16.43 262.27 320.05 4.11 468.77 460.33 22.94

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 387.28 299.27 245.81 1066.92 0.36 7.29 6.52 16.04

 MEAN 18.04 391.51 302.18 248.92 1063.92 0.37 7.43 6.80 12.53

 HUB 15.00 423.38 339.31 253.22 1060.25 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 432.50 279.59 133.23 0.26 6175.30 0.92 0.87

 MEAN 378.12 260.25 75.94 0.24 5451.23 0.92 0.87 0.87 1.77

 HUB 314.47 254.43 24.84 0.24 5090.41 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.15 4.40 492.23 1.04 480.20 474.94 21.10

 MEAN 4.74 1.13 4.32 489.79 1.04 477.50 473.76 23.26

 HUB 4.70 1.12 4.22 488.58 1.04 474.21 473.60 26.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.60 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.52 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.27 -5.60 -9.30 3.70 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 402.8041 301.5946 267.0053 1063.5055 0.3788 -0.0355 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7475 4.3060 477.2115 474.3395 24.4234 48.4811 35.4000 -13.0811

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 265.3363 64.9094 257.2744 1071.6456 0.2476 0.5192 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7363 4.5413 484.5645 473.1787 554.9116 0.0356 0.6116

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 264.2646 0.0000 264.2646 1071.6598 0.2466 0.4869 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5210 484.6119 474.0171 0.0000 0.0600 0.0878 0.4729

NASA/TM—2013-218094 L–199
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8118 4.7135 1.1225 490.1987 18.7315 166.9134 1.2939

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 117011.172 0.626 165.668 256825.938 0.212779E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.158 EfDer = 0.957 SH = 0.321873E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.054 2402.380 4.713 490.198 1.000 1.000 0.980

 W Kg/sec = 11.388 Wdry = 24.973 WH2O = 0.081 lbm/sec H2O = 1.305g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.960 2471.233 1.377 0.251 53.453 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59520.004 19633.756 2.651 590.487 222.765 468.502 2.103

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 241.90 -0.08 241.90 0.23 0.46 443.16

 MEAN 18.08 0.00 -0.02 241.90 -0.08 241.90 0.23 0.42

 HUB 15.21 0.00 -0.02 241.90 -0.08 241.90 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.69 46.36 14.33 430.82 494.16 4.55 485.54 476.67 34.21

 MEAN 57.46 42.30 15.16 379.01 449.69 4.55 485.54 476.67 34.21

 HUB 52.82 37.84 14.98 318.87 400.31 4.55 485.54 476.67 34.21

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 356.40 248.83 255.16 1085.10 0.33 2.33 2.04 9.02

 MEAN 18.01 355.82 245.40 257.65 1082.72 0.33 2.40 2.13 7.35

 HUB 15.22 376.83 272.37 260.42 1080.38 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 428.10 311.84 179.27 0.29 5082.74 0.92 0.88

 MEAN 377.57 289.57 132.17 0.27 4421.23 0.92 0.88 0.88 1.71

 HUB 319.15 264.58 46.78 0.24 4147.52 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.26 1.12 4.88 507.17 1.03 497.06 486.41 24.41

 MEAN 5.18 1.10 4.82 504.96 1.03 494.88 485.45 26.24

 HUB 5.15 1.09 4.74 504.05 1.03 492.74 485.41 28.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.28 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.61 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.29 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 380.3160 246.0934 289.9627 1081.5792 0.3516 -0.1063 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1939 4.7747 493.8824 486.1296 27.3566 40.3215 30.6000 -9.7215

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 280.7521 59.5215 274.3701 1087.2935 0.2582 0.3714 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1881 4.9567 499.1221 484.8085 491.5697 0.0252 0.4670

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 290.9843 0.0000 290.9843 1086.7678 0.2678 0.3577 0.5911

NASA/TM—2013-218094 L–200
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9247 498.6578 485.2908 0.0000 0.0600 0.0668 0.2878

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8301 5.1721 1.0973 505.3959 15.1985 188.1891 1.4588

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 95474.172 0.521 135.175 233610.016 0.368101E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.096 EfDer = 0.973 SH = 0.432838E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.054 2402.380 5.172 505.395 1.000 1.000 0.980

 W Kg/sec = 11.388 Wdry = 24.946 WH2O = 0.108 lbm/sec H2O = 1.866g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.289 2433.795 1.376 0.252 53.489 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55968.914 19625.105 2.644 545.479 206.285 424.468 2.058

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 246.24 -0.08 246.24 0.23 0.45 426.25

 MEAN 17.74 0.00 -0.02 246.24 -0.08 246.24 0.23 0.41

 HUB 15.05 0.00 -0.02 246.24 -0.08 246.24 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.67 46.36 13.31 420.76 487.59 4.99 500.58 486.18 27.60

 MEAN 56.50 43.40 13.10 371.88 446.09 4.99 500.58 486.18 27.60

 HUB 52.04 38.84 13.20 315.52 400.30 4.99 500.58 486.18 27.60

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 348.49 232.47 259.62 1100.09 0.32 2.26 1.98 8.75

 MEAN 17.51 350.00 232.27 261.82 1098.07 0.32 2.34 2.07 6.78

 HUB 14.85 373.09 263.37 264.25 1096.08 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.31 317.54 182.84 0.29 4606.95 0.92 0.89

 MEAN 367.02 294.46 134.75 0.27 4067.81 0.92 0.89 0.89 1.66

 HUB 311.33 268.57 47.95 0.25 3912.36 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.70 1.10 5.33 520.73 1.03 511.09 494.44 20.98

 MEAN 5.64 1.09 5.26 518.93 1.03 509.21 493.76 22.22

 HUB 5.62 1.09 5.19 518.42 1.03 507.37 493.96 23.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.84 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.58 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.90 10.29 6.50 3.79 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 375.7832 233.7976 294.1967 1096.8840 0.3426 -0.1147 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6494 5.2158 508.1599 494.4672 23.1615 38.4741 31.5000 -6.9741

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 289.6823 63.1922 282.7058 1101.7693 0.2629 0.3184 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6457 5.3852 512.7049 493.2865 451.3937 0.0194 0.4399

 

NASA/TM—2013-218094 L–201
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 294.5774 0.0000 294.5774 1101.5090 0.2674 0.3417 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3640 512.4797 493.7444 0.0000 0.0600 0.0528 0.2645

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8519 5.6326 1.0890 519.3594 13.9645 193.9225 1.5033

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 88045.055 0.510 124.657 232544.234 0.493780E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.437 EfDer = 0.984 SH = 0.578431E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.054 2402.380 5.633 519.359 1.000 1.000 0.980

 W Kg/sec = 11.388 Wdry = 24.909 WH2O = 0.145 lbm/sec H2O = 2.642g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.428 2400.854 1.374 0.253 53.536 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52832.625 19613.711 2.671 513.330 192.193 395.845 2.060

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 246.99 -0.09 246.99 0.22 0.43 403.51

 MEAN 16.97 0.00 -0.02 246.99 -0.09 246.99 0.22 0.39

 HUB 14.32 0.00 -0.02 246.99 -0.09 246.99 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.55 46.36 12.19 403.78 473.41 5.44 514.54 494.72 23.79

 MEAN 55.24 43.80 11.44 355.79 433.19 5.44 514.54 494.72 23.79

 HUB 50.56 37.84 12.72 300.21 388.83 5.44 514.54 494.72 23.79

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 335.60 212.72 259.58 1113.40 0.30 2.16 1.89 8.34

 MEAN 16.57 337.15 212.72 261.57 1111.58 0.30 2.24 1.97 6.35

 HUB 13.89 358.92 243.45 263.74 1109.80 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 395.81 317.66 183.10 0.29 4017.73 0.92 0.90

 MEAN 347.47 294.23 134.75 0.26 3527.04 0.92 0.90 0.90 1.61

 HUB 291.20 268.03 47.75 0.24 3382.71 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.12 1.09 5.76 532.67 1.03 523.77 501.50 19.00

 MEAN 6.06 1.08 5.69 531.04 1.02 522.06 500.93 19.96

 HUB 6.04 1.07 5.63 530.57 1.02 520.38 501.13 20.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.33 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.12 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.71 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 357.8114 213.9166 286.8251 1110.7365 0.3221 -0.0912 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0737 5.6597 521.3131 501.5062 20.5515 36.7159 32.4000 -4.3159

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.1766 64.6296 280.8358 1114.4989 0.2586 0.2783 2.2705

 

NASA/TM—2013-218094 L–202
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0719 5.8006 524.8600 500.5273 432.2457 0.0148 0.4166

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 285.8625 0.0000 285.8625 1114.5745 0.2565 0.3266 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7950 524.9449 500.7390 0.0000 0.0600 0.0429 0.2635

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8688 6.0611 1.0761 531.3946 12.0668 209.5124 1.6241

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76423.781 0.488 108.203 238353.188 0.635806E-02

 

Melt Ratio at Stator LE, Throat, TE

0.15994E+00 0.22649E+00 0.44029E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.923 EfDer = 0.992 SH = 0.692348E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.054 2402.380 6.061 531.383 1.000 1.000 0.980

 W Kg/sec = 11.388 Wdry = 24.881 WH2O = 0.173 lbm/sec H2O = 3.332g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.503 2373.511 1.373 0.254 53.573 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50134.250 19604.760 2.819 509.668 180.791 384.739 2.128

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.07 -0.08 236.07 0.21 0.40 379.45

 MEAN 15.91 0.00 -0.02 236.07 -0.08 236.07 0.21 0.37

 HUB 13.07 0.00 -0.02 236.07 -0.08 236.07 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.43 47.36 11.07 384.07 450.89 5.88 526.99 501.04 19.77

 MEAN 54.72 44.80 9.92 333.61 408.75 5.88 526.99 501.04 19.77

 HUB 49.26 38.84 10.42 274.01 361.74 5.88 526.99 501.04 19.77

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 318.81 199.55 248.63 1125.28 0.28 2.05 1.78 7.43

 MEAN 15.50 317.58 195.10 250.58 1123.41 0.28 2.13 1.86 5.75

 HUB 12.59 333.81 218.17 252.65 1121.57 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.11 304.94 176.55 0.27 3581.48 0.92 0.91

 MEAN 324.90 282.20 129.80 0.25 3024.94 0.92 0.91 0.91 1.60

 HUB 263.95 256.76 45.77 0.23 2747.84 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.52 1.08 6.18 543.19 1.02 535.19 506.59 16.09

 MEAN 6.45 1.06 6.11 541.36 1.02 533.41 505.93 16.88

 HUB 6.41 1.06 6.04 540.44 1.02 531.67 505.87 17.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.75 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.91 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.81 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 347.5023 198.6817 285.1025 1122.0459 0.3097 -0.1709 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4554 6.0477 532.1459 506.5402 17.5236 34.8718 33.0000 -1.8718

 

NASA/TM—2013-218094 L–203
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 291.4716 66.5578 283.7706 1125.0037 0.2591 0.1591 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4536 6.1641 534.9604 505.8153 410.5396 0.0251 0.3909

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 283.5381 0.0000 283.5381 1125.3649 0.2520 0.3142 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1758 535.3205 506.1914 0.0000 0.0600 0.0378 0.1918

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8782 6.4490 1.0640 541.6464 10.2793 229.6439 1.7802

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65302.621 0.462 92.457 250321.750 0.752104E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1488 Tt4 = 541.6464 T1 = 471.4685

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 442256.81 626.1604 83.6183 1.5358 0.8342 15.6643 1.1488 37.3740

NASA/TM—2013-218094 L–204
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.680 EfDer = 0.953 SH = 0.105841E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.634 2370.470 4.337 469.497 1.000 1.000 0.980

 W Kg/sec = 11.652 Wdry = 25.607 WH2O = 0.027 lbm/sec H2O = 0.417g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.661 2491.571 1.380 0.249 53.383 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62638.320 20105.498 3.435 831.557 242.106 619.754 2.560

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 180.78 -0.06 180.78 0.17 0.44 448.55

 MEAN 17.06 0.00 -0.02 180.78 -0.06 180.78 0.17 0.38

 HUB 12.51 0.00 -0.02 180.78 -0.06 180.78 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.04 50.47 16.57 426.76 463.53 4.25 466.88 459.22 23.61

 MEAN 62.88 47.20 15.68 352.91 396.58 4.25 466.88 459.22 23.61

 HUB 55.07 38.62 16.45 258.79 315.73 4.25 466.88 459.22 23.61

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 382.17 295.27 242.64 1064.49 0.36 7.29 6.52 16.04

 MEAN 18.04 386.33 298.18 245.64 1061.56 0.36 7.43 6.80 12.53

 HUB 15.00 417.70 334.79 249.78 1057.98 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.76 275.97 131.49 0.26 6092.71 0.92 0.87

 MEAN 373.10 256.81 74.92 0.24 5379.01 0.92 0.87 0.87 1.77

 HUB 310.29 250.97 24.50 0.24 5022.67 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.96 1.14 4.54 489.71 1.04 478.00 473.67 21.75

 MEAN 4.88 1.13 4.46 487.34 1.04 475.37 472.48 23.93

 HUB 4.84 1.12 4.36 486.16 1.04 472.17 472.28 26.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.59 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.52 16.96 12.70 4.26 0.95 0.53 2.22

 HUB 53.27 -5.60 -9.30 3.70 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.4601 297.5988 263.4568 1061.1597 0.3746 -0.0356 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8902 4.4447 475.0867 473.0350 25.1109 48.4823 35.4000 -13.0823

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.0305 64.1006 254.0690 1069.0980 0.2451 0.5190 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8790 4.6821 482.2401 471.9552 554.9116 0.0352 0.6111

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 260.9540 0.0000 260.9540 1069.1128 0.2441 0.4864 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6614 482.2868 472.7352 0.0000 0.0600 0.0878 0.4723

NASA/TM—2013-218094 L–205
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8118 4.8558 1.1196 487.7373 18.2420 166.8817 1.2937

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 113902.195 0.625 165.000 263499.500 0.192646E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.138 EfDer = 0.957 SH = 0.289925E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.634 2370.470 4.856 487.737 1.000 1.000 0.980

 W Kg/sec = 11.652 Wdry = 25.560 WH2O = 0.074 lbm/sec H2O = 1.218g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.251 2444.554 1.378 0.251 53.442 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58774.734 20090.896 2.676 590.487 220.644 468.502 2.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.87 -0.08 238.87 0.22 0.46 438.38

 MEAN 18.08 0.00 -0.02 238.87 -0.08 238.87 0.22 0.41

 HUB 15.21 0.00 -0.02 238.87 -0.08 238.87 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.67 46.36 14.31 425.10 487.69 4.69 483.19 475.21 35.04

 MEAN 57.44 42.30 15.14 373.97 443.82 4.69 483.19 475.21 35.04

 HUB 52.80 37.84 14.96 314.64 395.10 4.69 483.19 475.21 35.04

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 351.80 245.23 252.24 1082.24 0.33 2.33 2.04 9.02

 MEAN 18.01 351.27 241.97 254.64 1079.93 0.33 2.40 2.13 7.35

 HUB 15.22 372.04 268.70 257.31 1077.64 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 422.41 308.25 177.18 0.28 5009.38 0.92 0.88 

 MEAN 372.56 286.18 130.59 0.26 4359.29 0.92 0.88 0.88 1.71

 HUB 314.91 261.43 46.20 0.24 4091.74 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.11 5.03 504.26 1.03 494.39 484.92 25.14

 MEAN 5.33 1.10 4.96 502.12 1.03 492.28 483.95 26.99

 HUB 5.30 1.09 4.89 501.23 1.03 490.20 483.89 28.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.19 35.08 31.50 3.58 0.93 0.55 1.40

 MEAN 43.54 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.24 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.4756 242.6453 286.5400 1078.8068 0.3480 -0.1065 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3396 4.9168 491.3033 484.6023 28.1270 40.2583 30.6000 -9.6583

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 277.6086 58.8550 271.2980 1084.3767 0.2560 0.3700 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3339 5.0998 496.3966 483.3698 491.5697 0.0248 0.4656

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 287.6943 0.0000 287.6943 1083.8619 0.2654 0.3565 0.5911

NASA/TM—2013-218094 L–206
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0675 495.9436 483.8214 0.0000 0.0600 0.0665 0.2863

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8305 5.3177 1.0951 502.5370 14.8011 188.3730 1.4603

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92882.055 0.521 134.550 239759.297 0.331106E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.039 EfDer = 0.973 SH = 0.388704E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.634 2370.470 5.318 502.537 1.000 1.000 0.980

 W Kg/sec = 11.652 Wdry = 25.535 WH2O = 0.100 lbm/sec H2O = 1.734g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.749 2408.289 1.376 0.251 53.474 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55343.047 20083.025 2.665 545.479 204.646 424.468 2.074

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.49 -0.08 243.49 0.22 0.44 421.78

 MEAN 17.74 0.00 -0.02 243.49 -0.08 243.49 0.22 0.41

 HUB 15.05 0.00 -0.02 243.49 -0.08 243.49 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.61 46.36 13.25 415.17 481.38 5.14 497.82 484.65 28.39

 MEAN 56.44 43.40 13.04 366.94 440.45 5.14 497.82 484.65 28.39

 HUB 51.98 38.84 13.14 311.33 395.30 5.14 497.82 484.65 28.39

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 344.10 228.85 256.97 1096.88 0.31 2.26 1.98 8.75

 MEAN 17.51 345.67 228.81 259.10 1094.91 0.32 2.34 2.07 6.78

 HUB 14.85 368.59 259.81 261.44 1092.97 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.79 314.28 180.94 0.29 4535.28 0.92 0.89

 MEAN 362.14 291.39 133.33 0.27 4007.16 0.92 0.89 0.89 1.66

 HUB 307.19 265.70 47.38 0.24 3859.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.85 1.10 5.47 517.45 1.03 508.04 492.88 21.67

 MEAN 5.79 1.09 5.41 515.71 1.03 506.22 492.19 22.93

 HUB 5.77 1.08 5.34 515.23 1.03 504.43 492.37 24.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.69 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.45 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.82 10.27 6.50 3.77 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.1905 230.3114 291.0997 1093.7448 0.3394 -0.1150 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7975 5.3603 505.1875 492.8673 23.8980 38.3502 31.5000 -6.8502

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.7917 62.5617 279.8849 1098.5012 0.2611 0.3158 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7939 5.5301 509.5987 491.7635 451.3937 0.0190 0.4376

 

NASA/TM—2013-218094 L–207
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.6147 0.0000 291.6147 1098.2471 0.2655 0.3396 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5088 509.3785 492.1929 0.0000 0.0600 0.0522 0.2620

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8526 5.7807 1.0871 516.1302 13.5942 194.3528 1.5066

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85590.289 0.510 123.987 238775.250 0.442845E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.347 EfDer = 0.984 SH = 0.517834E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.634 2370.470 5.781 516.130 1.000 1.000 0.980

 W Kg/sec = 11.652 Wdry = 25.501 WH2O = 0.133 lbm/sec H2O = 2.444g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.024 2376.364 1.375 0.252 53.516 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52305.426 20072.703 2.688 513.330 190.936 395.845 2.073

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.53 -0.08 244.53 0.22 0.42 399.40

 MEAN 16.97 0.00 -0.02 244.53 -0.08 244.53 0.22 0.39

 HUB 14.32 0.00 -0.02 244.53 -0.08 244.53 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.47 46.36 12.11 398.42 467.55 5.59 511.40 493.10 24.54

 MEAN 55.15 43.80 11.35 351.06 427.90 5.59 511.40 493.10 24.54

 HUB 50.47 37.84 12.63 296.23 384.18 5.59 511.40 493.10 24.54

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.51 209.14 257.21 1109.87 0.30 2.16 1.89 8.34

 MEAN 16.57 333.14 209.37 259.13 1108.11 0.30 2.24 1.97 6.35

 HUB 13.89 354.76 240.02 261.23 1106.37 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 390.56 314.75 181.41 0.28 3950.28 0.92 0.90

 MEAN 342.85 291.49 133.48 0.26 3471.45 0.92 0.90 0.90 1.61

 HUB 287.33 265.48 47.31 0.24 3335.13 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.27 1.09 5.90 529.07 1.03 520.37 499.89 19.77

 MEAN 6.21 1.07 5.84 527.50 1.02 518.71 499.32 20.74

 HUB 6.20 1.07 5.78 527.05 1.02 517.09 499.51 21.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.12 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 38.94 27.25 23.50 3.75 0.94 0.47 1.62

 HUB 42.58 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 353.6455 210.5446 284.1410 1107.2719 0.3194 -0.0918 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2235 5.8060 517.9789 499.8935 21.3842 36.5379 32.4000 -4.1379

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 285.6052 64.0529 278.3299 1110.9309 0.2571 0.2749 2.2705

 

NASA/TM—2013-218094 L–208
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2217 5.9469 521.4172 498.9923 432.2457 0.0145 0.4135

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 283.3154 0.0000 283.3154 1111.0129 0.2550 0.3237 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9411 521.5079 499.2462 0.0000 0.0600 0.0424 0.2599

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8686 6.2109 1.0744 527.8546 11.7436 210.2118 1.6295

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74242.852 0.487 107.549 244834.672 0.576494E-02

 

Melt Ratio at Stator LE, Throat, TE

0.53152E-01 0.95400E-01 0.25276E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.799 EfDer = 0.992 SH = 0.637823E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.634 2370.470 6.211 527.846 1.000 1.000 0.980

 W Kg/sec = 11.652 Wdry = 25.471 WH2O = 0.164 lbm/sec H2O = 3.169g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.204 2349.825 1.373 0.253 53.555 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49695.906 20063.072 2.834 509.668 179.853 384.739 2.139

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 234.00 -0.08 234.00 0.21 0.40 375.66

 MEAN 15.91 0.00 -0.02 234.00 -0.08 234.00 0.21 0.36

 HUB 13.07 0.00 -0.02 234.00 -0.08 234.00 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.31 47.36 10.95 378.97 445.47 6.03 523.53 499.70 21.06

 MEAN 54.60 44.80 9.80 329.18 403.94 6.03 523.53 499.70 21.06

 HUB 49.13 38.84 10.29 270.37 357.63 6.03 523.53 499.70 21.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 315.03 195.97 246.65 1121.46 0.28 2.05 1.78 7.43

 MEAN 15.50 313.97 191.86 248.53 1119.65 0.28 2.13 1.86 5.75

 HUB 12.59 330.15 215.01 250.53 1117.86 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.11 302.51 175.14 0.27 3517.21 0.92 0.91 

 MEAN 320.59 279.89 128.73 0.25 2974.60 0.92 0.91 0.91 1.60

 HUB 260.44 254.62 45.43 0.23 2708.07 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.07 6.32 539.31 1.02 531.48 505.27 17.27

 MEAN 6.60 1.06 6.26 537.54 1.02 529.76 504.62 18.11

 HUB 6.56 1.06 6.19 536.67 1.02 528.07 504.55 18.97

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.47 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.67 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.64 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 343.6885 195.3747 282.7553 1118.2949 0.3073 -0.1719 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6058 6.1945 528.5186 505.2244 18.8082 34.6432 33.0000 -1.6432

 

NASA/TM—2013-218094 L–209
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 289.1965 66.0383 281.5556 1121.1503 0.2579 0.1529 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6041 6.3101 531.2265 504.4627 410.5396 0.0247 0.3872

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 281.2939 0.0000 281.2939 1121.4889 0.2508 0.3103 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3222 531.5564 504.5898 0.0000 0.0600 0.0375 0.1867

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8819 6.5996 1.0626 537.7932 9.9943 230.6775 1.7882

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63393.348 0.460 91.832 257244.875 0.677649E-02

 

Melt Ratio at Stator LE, Throat, TE

0.77380E+00 0.85744E+00 0.10000E+01

 trTOT = 1.1455 Tt4 = 537.7932 T1 = 469.4966

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 430010.72 622.9186 82.6607 1.5217 0.8352 15.6796 1.1455 37.3740

NASA/TM—2013-218094 L–210
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.741 EfDer = 0.952 SH = 0.105877E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.489 2295.269 4.829 471.207 1.000 1.000 0.980

 W Kg/sec = 12.495 Wdry = 27.460 WH2O = 0.029 lbm/sec H2O = 0.463g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.764 2408.148 1.380 0.249 53.383 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60490.344 21560.418 3.559 831.557 233.626 619.754 2.653

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.58 -0.06 174.58 0.17 0.43 433.53

 MEAN 17.06 0.00 -0.02 174.58 -0.06 174.58 0.17 0.36

 HUB 12.51 0.00 -0.02 174.58 -0.06 174.58 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.10 50.47 16.63 413.22 448.64 4.74 468.76 461.17 24.18

 MEAN 62.94 47.20 15.74 341.71 383.78 4.74 468.76 461.17 24.18

 HUB 55.14 38.62 16.52 250.58 305.45 4.74 468.76 461.17 24.18

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 370.10 285.91 235.02 1065.77 0.35 7.29 6.52 16.04

 MEAN 18.04 374.03 288.77 237.72 1063.04 0.35 7.43 6.80 12.53

 HUB 15.00 404.21 324.17 241.44 1059.70 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 413.22 267.29 127.31 0.25 5899.50 0.92 0.87

 MEAN 361.26 248.53 72.49 0.23 5209.31 0.92 0.87 0.87 1.77

 HUB 300.45 242.61 23.72 0.23 4863.34 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 490.16 1.04 479.17 474.86 22.44

 MEAN 5.39 1.12 4.96 487.94 1.04 476.72 473.72 24.53

 HUB 5.35 1.11 4.85 486.83 1.03 473.73 473.50 27.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.58 28.44 24.20 4.24 0.93 0.58 1.80

 MEAN 50.54 16.96 12.70 4.26 0.95 0.53 2.22

 HUB 53.32 -5.61 -9.30 3.69 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.952 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 384.7662 288.2104 254.9114 1062.6685 0.3621 -0.0357 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.4018 4.9402 476.4522 474.2314 25.6747 48.5084 35.4000 -13.1084

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 254.1482 62.1724 246.4262 1070.0774 0.2375 0.5189 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3908 5.1861 483.1360 473.2521 554.9116 0.0341 0.6101

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 253.0567 0.0000 253.0567 1070.0953 0.2365 0.4851 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1642 483.1818 473.9717 0.0000 0.0600 0.0880 0.4710

NASA/TM—2013-218094 L–211
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8112 5.3661 1.1113 488.3076 17.1022 166.6651 1.2920

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 106785.758 0.625 165.885 281496.281 0.185649E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.092 EfDer = 0.958 SH = 0.274638E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.489 2295.269 5.366 488.307 1.000 1.000 0.980

 W Kg/sec = 12.495 Wdry = 27.414 WH2O = 0.075 lbm/sec H2O = 1.275g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.065 2365.620 1.378 0.250 53.437 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57009.676 21546.064 2.756 590.487 214.217 468.502 2.187

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 231.70 -0.08 231.70 0.22 0.44 424.22

 MEAN 18.08 0.00 -0.02 231.70 -0.08 231.70 0.22 0.40

 HUB 15.21 0.00 -0.02 231.70 -0.08 231.70 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.63 46.36 14.27 411.62 472.42 5.20 484.02 476.29 35.49

 MEAN 57.39 42.30 15.09 362.11 429.96 5.20 484.02 476.29 35.49

 HUB 52.75 37.84 14.91 304.66 382.82 5.20 484.02 476.29 35.49

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 340.96 236.68 245.43 1082.35 0.32 2.33 2.04 9.02

 MEAN 18.01 340.54 233.79 247.60 1080.19 0.32 2.40 2.13 7.35

 HUB 15.22 360.77 260.08 250.02 1078.07 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.01 299.90 172.34 0.28 4834.56 0.92 0.88

 MEAN 360.74 278.25 126.95 0.26 4212.05 0.92 0.88 0.88 1.70

 HUB 304.92 254.01 44.83 0.24 3960.47 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.93 1.10 5.54 503.76 1.03 494.48 485.56 26.10

 MEAN 5.85 1.09 5.47 501.77 1.03 492.52 484.63 27.87

 HUB 5.82 1.09 5.40 500.96 1.03 490.58 484.56 29.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.96 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.36 27.14 23.50 3.64 0.95 0.52 1.63

 HUB 46.13 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.0579 234.4494 278.5169 1079.1394 0.3374 -0.1071 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8648 5.4271 491.5948 485.2349 28.9886 40.0899 30.6000 -9.4899

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 270.3129 57.3083 264.1682 1084.3232 0.2493 0.3661 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8594 5.6152 496.3359 484.1261 491.5697 0.0237 0.4617

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 280.0453 0.0000 280.0453 1083.8407 0.2584 0.3530 0.5911

NASA/TM—2013-218094 L–212
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5816 495.9100 484.5424 0.0000 0.0600 0.0655 0.2822

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8313 5.8426 1.0888 502.1604 13.8540 188.8329 1.4638

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86901.203 0.519 134.996 256474.984 0.311834E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.886 EfDer = 0.974 SH = 0.363594E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.489 2295.269 5.843 502.160 1.000 1.000 0.980

 W Kg/sec = 12.495 Wdry = 27.389 WH2O = 0.100 lbm/sec H2O = 1.786g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.051 2332.762 1.377 0.251 53.466 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53898.582 21538.469 2.732 545.479 199.637 424.468 2.126

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 237.13 -0.08 237.13 0.22 0.43 408.56

 MEAN 17.74 0.00 -0.02 237.13 -0.08 237.13 0.22 0.39

 HUB 15.05 0.00 -0.02 237.13 -0.08 237.13 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.47 46.36 13.11 402.00 466.80 5.65 497.69 485.32 29.39

 MEAN 56.29 43.40 12.89 355.30 427.23 5.65 497.69 485.32 29.39

 HUB 51.82 38.84 12.98 301.45 383.61 5.65 497.69 485.32 29.39

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.86 220.16 250.98 1095.99 0.30 2.26 1.98 8.75

 MEAN 17.51 335.58 220.57 252.90 1094.17 0.31 2.34 2.07 6.78

 HUB 14.85 358.01 251.26 255.03 1092.38 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 396.79 306.91 176.63 0.28 4363.00 0.92 0.89

 MEAN 350.66 284.40 130.09 0.26 3862.84 0.92 0.89 0.89 1.65

 HUB 297.45 259.18 46.18 0.24 3732.47 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.39 1.09 6.00 516.06 1.03 507.20 493.18 22.87

 MEAN 6.32 1.08 5.93 514.47 1.02 505.51 492.53 24.11

 HUB 6.31 1.08 5.86 514.05 1.02 503.86 492.70 25.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.26 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 41.09 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.57 10.26 6.50 3.76 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 360.5222 222.0157 284.0515 1093.0642 0.3298 -0.1163 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3347 5.8822 504.5296 493.1638 25.0770 38.0113 31.5000 -6.5113

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 280.2894 61.1432 273.5392 1097.4751 0.2554 0.3083 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3314 6.0551 508.6167 492.1709 451.3937 0.0179 0.4311

 

NASA/TM—2013-218094 L–213
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 284.9411 0.0000 284.9411 1097.2352 0.2597 0.3338 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0332 508.4089 492.5671 0.0000 0.0600 0.0508 0.2548

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8543 6.3180 1.0814 514.8604 12.7008 195.5413 1.5158

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79904.367 0.508 124.127 255831.719 0.411730E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.092 EfDer = 0.986 SH = 0.478089E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.489 2295.269 6.318 514.860 1.000 1.000 0.980

 W Kg/sec = 12.495 Wdry = 27.358 WH2O = 0.131 lbm/sec H2O = 2.476g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.722 2303.812 1.375 0.252 53.503 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51129.152 21528.662 2.744 513.330 187.069 395.845 2.116

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 239.03 -0.08 239.03 0.22 0.41 387.20

 MEAN 16.97 0.00 -0.02 239.03 -0.08 239.03 0.22 0.38

 HUB 14.32 0.00 -0.02 239.03 -0.08 239.03 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.22 46.36 11.86 385.78 453.90 6.12 510.33 493.41 25.79

 MEAN 54.89 43.80 11.09 339.92 415.62 6.12 510.33 493.41 25.79

 HUB 50.20 37.84 12.36 286.83 373.44 6.12 510.33 493.41 25.79

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 322.06 200.45 252.07 1108.10 0.29 2.16 1.89 8.34

 MEAN 16.57 323.92 201.26 253.81 1106.48 0.29 2.24 1.97 6.35

 HUB 13.89 345.23 231.95 255.71 1104.88 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.17 308.42 177.71 0.28 3786.17 0.92 0.90

 MEAN 331.97 285.49 130.71 0.26 3337.06 0.92 0.90 0.90 1.59

 HUB 278.22 259.86 46.27 0.24 3222.96 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.82 1.08 6.44 526.88 1.02 518.66 499.89 21.09

 MEAN 6.76 1.07 6.37 525.45 1.02 517.14 499.35 22.05

 HUB 6.74 1.07 6.31 525.09 1.02 515.65 499.54 23.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.49 35.18 31.50 3.68 0.93 0.48 1.40

 MEAN 38.41 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.21 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 344.0670 202.3920 278.2438 1105.6730 0.3112 -0.0931 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7696 6.3374 516.4313 499.8889 22.7057 36.0318 32.4000 -3.6318

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 280.0479 62.8066 272.9142 1109.0441 0.2525 0.2640 2.2705

 

NASA/TM—2013-218094 L–214
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7681 6.4793 519.5931 499.0803 432.2457 0.0137 0.4048

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 277.7711 0.0000 277.7711 1109.1241 0.2504 0.3153 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4737 519.6812 499.3092 0.0000 0.0600 0.0411 0.2499

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8708 6.7572 1.0695 525.7897 10.9490 212.2955 1.6457

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 69134.023 0.483 107.396 262697.656 0.528939E-02

 

Melt Ratio at Stator LE, Throat, TE

0.64838E-01 0.10860E+00 0.26521E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.452 EfDer = 0.994 SH = 0.582199E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.489 2295.269 6.757 525.782 1.000 1.000 0.980

 W Kg/sec = 12.495 Wdry = 27.329 WH2O = 0.160 lbm/sec H2O = 3.163g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.209 2279.742 1.374 0.253 53.537 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48738.734 21519.717 2.882 509.668 176.872 384.739 2.175

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 229.50 -0.08 229.50 0.21 0.39 364.46

 MEAN 15.91 0.00 -0.02 229.50 -0.08 229.50 0.21 0.35

 HUB 13.07 0.00 -0.02 229.50 -0.08 229.50 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.98 47.36 10.62 366.95 432.87 6.56 521.62 499.71 22.39

 MEAN 54.25 44.80 9.45 318.74 392.83 6.56 521.62 499.71 22.39

 HUB 48.77 38.84 9.93 261.79 348.20 6.56 521.62 499.71 22.39

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 306.32 187.21 242.46 1118.90 0.27 2.05 1.78 7.43

 MEAN 15.50 305.69 183.94 244.16 1117.23 0.27 2.13 1.86 5.75

 HUB 12.59 321.89 207.63 245.98 1115.59 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 359.34 297.34 172.12 0.27 3360.08 0.92 0.91

 MEAN 310.42 274.97 126.47 0.25 2851.92 0.92 0.91 0.91 1.58

 HUB 252.18 249.98 44.55 0.22 2615.04 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.22 1.07 6.86 536.40 1.02 528.99 505.04 18.61

 MEAN 7.15 1.06 6.80 534.79 1.02 527.41 504.42 19.45

 HUB 7.12 1.05 6.73 534.05 1.02 525.86 504.37 20.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.67 35.37 31.50 3.87 0.93 0.47 1.40

 MEAN 36.99 27.38 23.50 3.88 0.94 0.44 1.64

 HUB 40.17 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 334.9733 187.3151 277.7051 1115.9290 0.3002 -0.1743 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1578 6.7317 526.2108 504.9967 20.1803 34.0001 33.0000 -1.0001

 

NASA/TM—2013-218094 L–215
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 284.3516 64.9319 276.8387 1118.5348 0.2542 0.1380 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1564 6.8466 528.6760 504.3201 410.5396 0.0238 0.3766

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 276.5930 0.0000 276.5930 1118.8613 0.2472 0.2992 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8592 528.9933 504.4160 0.0000 0.0600 0.0369 0.1723

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8835 7.1516 1.0584 535.0335 9.2994 233.7747 1.8122

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58887.539 0.456 91.478 276360.844 0.616154E-02

 

Melt Ratio at Stator LE, Throat, TE

0.76815E+00 0.84830E+00 0.10000E+01

 trTOT = 1.1355 Tt4 = 535.0335 T1 = 471.2066

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 401612.91 623.8813 79.7643 1.4811 0.8367 15.7413 1.1355 37.3740

NASA/TM—2013-218094 L–216
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.287 EfDer = 0.964 SH = 0.135445E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.344 2167.876 5.592 480.735 1.000 1.000 0.980

 W Kg/sec = 14.247 Wdry = 31.302 WH2O = 0.042 lbm/sec H2O = 0.673g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.320 2251.842 1.380 0.249 53.392 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60760.598 24581.279 3.579 831.557 232.374 619.754 2.667 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 175.36 -0.06 175.36 0.16 0.40 405.39

 MEAN 17.06 0.00 -0.02 175.36 -0.06 175.36 0.16 0.35

 HUB 12.51 0.00 -0.02 175.36 -0.06 175.36 0.16 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.81 50.47 15.34 390.28 427.93 5.49 478.27 468.78 23.59

 MEAN 61.49 47.20 14.29 322.75 367.37 5.49 478.27 468.78 23.59

 HUB 53.47 38.62 14.85 236.67 294.61 5.49 478.27 468.78 23.59

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 353.70 262.21 237.39 1074.48 0.33 7.29 6.52 16.04

 MEAN 18.04 359.98 268.54 239.72 1072.18 0.34 7.43 6.80 12.53

 HUB 15.00 392.31 307.96 243.04 1069.28 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 390.28 269.73 128.08 0.25 5410.55 0.92 0.88

 MEAN 341.21 250.50 72.67 0.23 4844.46 0.92 0.88 0.88 1.68

 HUB 283.77 244.24 24.18 0.23 4620.13 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.78 497.13 1.03 487.11 480.57 22.80

 MEAN 6.16 1.10 5.70 495.42 1.03 485.04 479.75 24.49

 HUB 6.13 1.10 5.60 494.74 1.03 482.41 479.81 26.83

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.84 28.35 24.20 4.15 0.93 0.54 1.80

 MEAN 48.25 16.86 12.70 4.16 0.95 0.49 2.22

 HUB 51.72 -5.68 -9.30 3.62 0.95 0.36 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.964 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 371.3857 268.0204 257.0844 1071.7626 0.3465 -0.0410 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1686 5.6837 484.7290 480.2675 25.6031 46.1931 35.4000 -10.7931

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 257.6035 63.0177 249.7766 1078.0563 0.2390 0.4791 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1603 5.9237 490.4541 479.3762 554.9116 0.0272 0.5681

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 256.2263 0.0000 256.2263 1078.0920 0.2377 0.4566 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9051 490.5121 480.0892 0.0000 0.0600 0.0732 0.4401

NASA/TM—2013-218094 L–217
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8290 6.1383 1.0976 495.7607 15.0271 173.6784 1.3463

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93944.297 0.617 166.404 316160.031 0.222594E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.259 EfDer = 0.972 SH = 0.317227E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.344 2167.876 6.138 495.760 1.000 1.000 0.980

 W Kg/sec = 14.247 Wdry = 31.245 WH2O = 0.099 lbm/sec H2O = 1.659g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.385 2217.464 1.377 0.251 53.451 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57723.516 24563.631 2.744 590.487 215.218 468.502 2.177

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 234.60 -0.08 234.60 0.22 0.42 397.65

 MEAN 18.08 0.00 -0.02 234.60 -0.08 234.60 0.22 0.38

 HUB 15.21 0.00 -0.02 234.60 -0.08 234.60 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.90 46.36 12.54 388.77 454.14 5.94 491.38 482.40 34.65

 MEAN 55.56 42.30 13.26 342.01 414.80 5.94 491.38 482.40 34.65

 HUB 50.82 37.84 12.98 287.75 371.32 5.94 491.38 482.40 34.65

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 327.20 211.18 249.93 1088.52 0.30 2.33 2.04 9.02

 MEAN 18.01 329.09 211.95 251.75 1086.79 0.30 2.40 2.13 7.35

 HUB 15.22 351.13 242.67 253.79 1085.08 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.31 305.18 175.13 0.28 4313.95 0.92 0.89

 MEAN 340.72 282.77 128.77 0.26 3818.65 0.92 0.89 0.89 1.61

 HUB 287.99 257.80 45.33 0.24 3695.35 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.68 1.09 6.28 508.76 1.03 500.23 490.14 27.12

 MEAN 6.61 1.08 6.21 507.27 1.02 498.64 489.48 28.56

 HUB 6.60 1.07 6.14 506.90 1.02 497.08 489.65 30.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.20 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 40.09 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.72 10.13 6.50 3.63 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 354.1158 212.5438 283.2368 1085.6758 0.3262 -0.1204 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6253 6.1618 497.6593 490.1074 29.7166 36.8849 30.6000 -6.2849

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 276.0389 58.5222 269.7641 1089.9338 0.2533 0.3030 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6222 6.3378 501.5762 489.1510 491.5697 0.0174 0.4083

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 285.7518 0.0000 285.7518 1089.4481 0.2623 0.3086 0.5911

NASA/TM—2013-218094 L–218
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3048 501.1429 489.5724 0.0000 0.0600 0.0498 0.2243

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8517 6.6086 1.0766 507.6412 11.8817 201.1550 1.5593

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74637.563 0.500 132.206 289272.375 0.355671E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.822 EfDer = 0.987 SH = 0.407557E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.344 2167.876 6.609 507.641 1.000 1.000 0.980

 W Kg/sec = 14.247 Wdry = 31.217 WH2O = 0.128 lbm/sec H2O = 2.238g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.974 2191.362 1.376 0.251 53.480 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 54980.281 24554.824 2.695 545.479 202.403 424.468 2.097

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 241.89 -0.08 241.89 0.22 0.41 383.79

 MEAN 17.74 0.00 -0.02 241.89 -0.08 241.89 0.22 0.38

 HUB 15.05 0.00 -0.02 241.89 -0.08 241.89 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.51 46.36 11.15 379.69 450.27 6.39 502.99 490.26 30.29

 MEAN 54.22 43.40 10.82 335.58 413.74 6.39 502.99 490.26 30.29

 HUB 49.66 38.84 10.82 284.72 373.66 6.39 502.99 490.26 30.29

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.21 193.68 257.50 1099.92 0.29 2.26 1.98 8.75

 MEAN 17.51 326.09 198.02 259.08 1098.51 0.30 2.34 2.07 6.78

 HUB 14.85 350.24 233.75 260.82 1097.13 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 374.77 314.81 181.09 0.29 3838.45 0.92 0.90

 MEAN 331.19 291.30 133.17 0.27 3468.21 0.92 0.90 0.90 1.55

 HUB 280.94 265.06 47.19 0.24 3472.46 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.12 1.08 6.71 519.18 1.02 510.93 496.83 24.83

 MEAN 7.07 1.07 6.66 518.06 1.02 509.62 496.42 25.84

 HUB 7.07 1.07 6.59 518.08 1.02 508.33 496.81 26.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.95 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 37.39 27.20 23.50 3.70 0.94 0.44 1.62

 HUB 41.87 10.25 6.50 3.75 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 352.7761 199.3241 291.0685 1097.3291 0.3215 -0.1307 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0809 6.5995 508.5603 497.0834 26.9094 34.4034 31.5000 -2.9034

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 288.3776 62.9076 281.4325 1100.8528 0.2620 0.2331 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0794 6.7550 511.8381 496.2502 451.3937 0.0136 0.3727

 

NASA/TM—2013-218094 L–219
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 293.0071 0.0000 293.0071 1100.6106 0.2662 0.2796 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7341 511.6257 496.6373 0.0000 0.0600 0.0395 0.1845

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8709 7.0682 1.0695 518.4379 10.7975 210.4616 1.6315

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68026.625 0.484 120.496 289629.094 0.454860E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.786 EfDer = 0.996 SH = 0.512955E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.344 2167.876 7.068 518.436 1.000 1.000 0.980

 W Kg/sec = 14.247 Wdry = 31.184 WH2O = 0.161 lbm/sec H2O = 2.947g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.171 2168.424 1.375 0.252 53.515 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52545.199 24544.520 2.682 513.330 191.369 395.845 2.068 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 245.66 -0.08 245.66 0.22 0.40 364.45

 MEAN 16.97 0.00 -0.02 245.66 -0.08 245.66 0.22 0.37

 HUB 14.32 0.00 -0.02 245.66 -0.08 245.66 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.02 46.36 9.66 364.37 439.51 6.83 513.66 497.23 27.34

 MEAN 52.59 43.80 8.79 321.06 404.33 6.83 513.66 497.23 27.34

 HUB 47.81 37.84 9.97 270.91 365.77 6.83 513.66 497.23 27.34

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 312.99 173.44 260.54 1109.98 0.28 2.16 1.89 8.34

 MEAN 16.57 317.01 178.58 261.92 1108.76 0.29 2.24 1.97 6.35

 HUB 13.89 340.06 215.02 263.45 1107.56 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 357.18 318.81 183.74 0.29 3276.16 0.92 0.91

 MEAN 313.55 294.65 134.97 0.27 2961.18 0.92 0.91 0.91 1.50

 HUB 262.78 267.74 47.75 0.24 2987.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.53 1.06 7.13 528.24 1.02 520.49 502.49 23.06

 MEAN 7.48 1.06 7.08 527.30 1.02 519.34 502.17 23.84

 HUB 7.48 1.06 7.02 527.38 1.02 518.22 502.57 24.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.65 35.19 31.50 3.69 0.93 0.41 1.40

 MEAN 34.29 27.26 23.50 3.76 0.93 0.41 1.62

 HUB 39.22 10.27 6.50 3.77 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 338.7371 179.5834 287.2153 1107.8831 0.3058 -0.1055 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4928 7.0304 518.5555 502.7080 24.5250 32.0160 32.4000 0.3840

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 290.1814 65.0792 282.7896 1110.4481 0.2613 0.1793 2.2705

 

NASA/TM—2013-218094 L–220
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4919 7.1499 520.9651 502.0479 432.2457 0.0120 0.3418

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 287.7150 0.0000 287.7150 1110.5341 0.2591 0.2506 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1463 521.0546 502.1733 0.0000 0.0600 0.0366 0.1708

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8821 7.4815 1.0585 527.6031 9.2047 231.3691 1.7936

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58172.648 0.456 103.041 298403.813 0.547438E-02

 

Melt Ratio at Stator LE, Throat, TE

0.33092E+00 0.40280E+00 0.61318E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.936 EfDer = 1.000 SH = 0.581709E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.344 2167.876 7.482 527.592 1.000 1.000 0.980

 W Kg/sec = 14.247 Wdry = 31.162 WH2O = 0.182 lbm/sec H2O = 3.482g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.113 2149.508 1.374 0.253 53.537 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50438.504 24537.775 2.793 509.668 182.468 384.739 2.109

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 237.51 -0.08 237.51 0.21 0.38 343.64

 MEAN 15.91 0.00 -0.02 237.51 -0.08 237.51 0.21 0.34

 HUB 13.07 0.00 -0.02 237.51 -0.08 237.51 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.58 47.36 8.22 346.58 420.22 7.25 523.14 502.19 23.44

 MEAN 51.74 44.80 6.94 301.05 383.52 7.25 523.14 502.19 23.44

 HUB 46.16 38.84 7.32 247.26 342.91 7.25 523.14 502.19 23.44

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 298.79 160.04 252.31 1119.01 0.27 2.05 1.78 7.43

 MEAN 15.50 300.77 161.60 253.67 1117.75 0.27 2.13 1.86 5.75

 HUB 12.59 319.16 191.73 255.14 1116.51 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 339.39 309.56 179.35 0.28 2872.64 0.92 0.91

 MEAN 293.19 285.77 131.59 0.26 2505.68 0.92 0.91 0.91 1.48

 HUB 238.18 259.34 46.45 0.23 2414.99 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.90 1.06 7.52 536.16 1.02 529.11 506.55 20.19

 MEAN 7.84 1.05 7.47 535.07 1.01 527.92 506.15 20.87

 HUB 7.83 1.05 7.41 534.80 1.01 526.75 506.31 21.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.39 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.50 27.42 23.50 3.92 0.93 0.38 1.64

 HUB 36.92 10.32 6.50 3.82 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 332.2754 164.5608 288.6636 1116.3535 0.2976 -0.1932 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8498 7.3900 526.6219 506.8184 21.8258 29.6865 33.0000 3.3135

 

NASA/TM—2013-218094 L–221
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 296.6311 67.7360 288.7938 1118.2205 0.2653 0.0368 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8475 7.4796 528.3931 506.4100 410.5396 0.0257 0.3107

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 288.5698 0.0000 288.5698 1118.6017 0.2580 0.2252 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4935 528.7667 506.6783 0.0000 0.0600 0.0404 0.0724

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8761 7.8418 1.0482 535.3401 7.7498 257.5280 1.9963

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 49073.984 0.426 86.925 314762.688 0.629764E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1136 Tt4 = 535.3401 T1 = 480.7346

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 343855.13 609.0708 79.3201 1.4022 0.8515 14.2872 1.1136 37.3740

NASA/TM—2013-218094 L–222
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.489 EfDer = 0.994 SH = 0.168076E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.395 1982.604 6.513 491.410 1.000 1.000 0.980

 W Kg/sec = 17.907 Wdry = 39.329 WH2O = 0.066 lbm/sec H2O = 0.949g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.548 2036.905 1.379 0.250 53.403 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67223.016 30890.998 3.279 831.557 253.608 619.754 2.444

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 194.02 -0.07 194.02 0.18 0.38 366.69

 MEAN 17.06 0.00 -0.02 194.02 -0.07 194.02 0.18 0.33

 HUB 12.51 0.00 -0.02 194.02 -0.07 194.02 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.48 50.47 11.01 356.93 406.31 6.37 488.40 476.92 22.21

 MEAN 56.69 47.20 9.49 295.17 353.28 6.37 488.40 476.92 22.21

 HUB 48.14 38.62 9.52 216.44 290.72 6.37 488.40 476.92 22.21

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 341.08 214.34 265.32 1082.33 0.32 7.29 6.52 16.04

 MEAN 18.04 353.50 231.48 267.16 1080.83 0.33 7.43 6.80 12.53

 HUB 15.00 393.97 286.71 270.21 1078.55 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 356.93 301.21 142.59 0.28 4423.17 0.92 0.91

 MEAN 312.05 279.04 80.57 0.26 4176.20 0.92 0.91 0.91 1.43

 HUB 259.52 271.57 27.19 0.25 4301.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.08 6.60 503.66 1.02 494.35 485.98 23.23

 MEAN 7.03 1.08 6.54 502.97 1.02 492.97 485.79 24.31

 HUB 7.05 1.08 6.44 503.32 1.02 490.90 486.50 26.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.93 28.25 24.20 4.05 0.93 0.41 1.80

 MEAN 40.91 16.78 12.70 4.08 0.94 0.36 2.22

 HUB 46.70 -5.75 -9.30 3.55 0.94 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.2548 231.0347 286.7657 1080.2045 0.3409 -0.0585 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0446 6.5080 492.4814 486.3529 25.5052 38.8569 35.4000 -3.4569

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 289.6321 70.8528 280.8320 1084.7122 0.2670 0.3445 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0421 6.7066 496.6146 485.6950 554.9116 0.0149 0.4435

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 287.5458 0.0000 287.5458 1084.7971 0.2651 0.3550 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6985 496.7125 486.3457 0.0000 0.0600 0.0407 0.3290

NASA/TM—2013-218094 L–223
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8722 7.0286 1.0792 503.3145 11.9048 198.7706 1.5409

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74518.000 0.585 165.896 391971.156 0.256748E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.655 EfDer = 0.999 SH = 0.346885E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.395 1982.604 7.029 503.314 1.000 1.000 0.980

 W Kg/sec = 17.907 Wdry = 39.259 WH2O = 0.137 lbm/sec H2O = 2.034g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.163 2012.679 1.377 0.251 53.461 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64700.176 30869.160 2.480 590.487 238.075 468.502 1.968

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.95 -0.09 262.95 0.24 0.41 360.93

 MEAN 18.08 0.00 -0.02 262.95 -0.09 262.95 0.24 0.38

 HUB 15.21 0.00 -0.02 262.95 -0.09 262.95 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.52 46.36 7.16 355.55 442.29 6.75 497.81 488.41 33.31

 MEAN 49.95 42.30 7.65 312.78 408.70 6.75 497.81 488.41 33.31

 HUB 45.03 37.84 7.19 263.16 372.08 6.75 497.81 488.41 33.31

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.74 154.74 283.22 1092.24 0.30 2.33 2.04 9.02

 MEAN 18.01 329.25 165.99 284.35 1091.36 0.30 2.40 2.13 7.35

 HUB 15.22 355.83 212.17 285.65 1090.51 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 353.30 345.89 198.56 0.32 3161.57 0.92 0.91

 MEAN 311.60 319.47 145.61 0.29 2991.07 0.92 0.91 0.91 1.39

 HUB 263.38 290.20 51.21 0.27 3231.22 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.44 1.06 7.01 512.02 1.02 503.73 493.68 28.78

 MEAN 7.42 1.06 6.97 511.55 1.02 502.92 493.56 29.52

 HUB 7.45 1.06 6.93 512.21 1.02 502.14 494.28 30.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.65 35.03 31.50 3.53 0.93 0.34 1.40

 MEAN 30.27 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.60 10.16 6.50 3.66 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 361.1809 166.4536 320.5384 1089.8412 0.3314 -0.1615 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4339 6.8980 501.5515 494.3139 31.0636 27.4426 30.6000 3.1574

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 314.7113 66.7210 307.5573 1092.5479 0.2881 0.1080 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4320 7.0225 504.0499 493.6842 491.5697 0.0142 0.2631

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 325.8722 0.0000 325.8722 1091.9224 0.2984 0.1573 0.5911

NASA/TM—2013-218094 L–224
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9823 503.4825 494.1145 0.0000 0.0600 0.0400 0.0218

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8726 7.4199 1.0557 511.9257 8.6120 247.7512 1.9206

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 54152.047 0.434 120.556 361563.719 0.382118E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.747 EfDer = 0.996 SH = 0.426654E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.395 1982.604 7.420 511.925 1.000 1.000 0.980

 W Kg/sec = 17.907 Wdry = 39.227 WH2O = 0.168 lbm/sec H2O = 2.590g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.536 1995.679 1.376 0.252 53.487 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62504.668 30859.379 2.397 545.479 227.560 424.468 1.865

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 275.00 -0.09 275.00 0.25 0.40 349.52

 MEAN 17.74 0.00 -0.02 275.00 -0.09 275.00 0.25 0.38

 HUB 15.05 0.00 -0.02 275.00 -0.09 275.00 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.63 46.36 5.27 347.24 443.02 7.11 505.92 494.45 31.55

 MEAN 48.15 43.40 4.75 306.90 412.15 7.11 505.92 494.45 31.55

 HUB 43.45 38.84 4.61 260.39 378.78 7.11 505.92 494.45 31.55

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 325.19 133.53 296.51 1099.74 0.30 2.26 1.98 8.75

 MEAN 17.51 332.66 149.41 297.22 1099.23 0.30 2.34 2.07 6.78

 HUB 14.85 360.30 202.33 298.12 1098.74 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 342.74 362.89 209.21 0.33 2647.11 0.92 0.91

 MEAN 302.89 334.51 153.48 0.30 2617.26 0.92 0.91 0.91 1.33

 HUB 256.93 303.08 54.59 0.28 3006.06 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.78 1.05 7.33 519.20 1.01 510.80 498.77 28.25

 MEAN 7.77 1.05 7.30 519.11 1.01 510.33 498.86 28.65

 HUB 7.83 1.05 7.27 520.18 1.02 509.88 499.78 29.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 24.24 35.21 31.50 3.71 0.93 0.29 1.40

 MEAN 26.69 27.31 23.50 3.81 0.92 0.30 1.62

 HUB 34.16 10.38 6.50 3.88 0.92 0.34 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.9479 150.3859 334.7160 1097.5598 0.3343 -0.1741 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7878 7.2172 508.8148 499.6891 30.2160 24.1941 31.5000 7.3059

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 334.2776 72.9204 326.2271 1099.5139 0.3040 0.0128 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7831 7.3077 510.6325 499.2030 451.3937 0.0194 0.2208

 

NASA/TM—2013-218094 L–225
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 340.0169 0.0000 340.0169 1099.1719 0.3093 0.1024 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2756 510.3236 499.5248 0.0000 0.0600 0.0543 -0.0524

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8470 7.7660 1.0466 519.4925 7.5714 267.7031 2.0752

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47728.590 0.406 106.256 364297.156 0.464487E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10230E-01 0.17690E-01 0.60035E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 2.172 EfDer = 0.978 SH = 0.505059E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.395 1982.604 7.766 519.489 1.000 1.000 0.980

 W Kg/sec = 17.907 Wdry = 39.196 WH2O = 0.199 lbm/sec H2O = 3.156g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.627 1981.091 1.375 0.252 53.512 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60727.289 30849.740 2.343 513.330 219.126 395.845 1.806

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 283.91 -0.10 283.91 0.26 0.40 332.96

 MEAN 16.97 0.00 -0.02 283.91 -0.10 283.91 0.26 0.37

 HUB 14.32 0.00 -0.02 283.91 -0.10 283.91 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.58 46.36 3.22 333.23 437.85 7.42 513.11 499.53 29.84

 MEAN 45.97 43.80 2.17 293.62 408.50 7.42 513.11 499.53 29.84

 HUB 41.12 37.84 3.28 247.76 376.88 7.42 513.11 499.53 29.84

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 324.62 110.13 305.37 1106.08 0.29 2.16 1.89 8.34

 MEAN 16.57 331.51 128.08 305.77 1105.82 0.30 2.24 1.97 6.35

 HUB 13.89 357.28 183.78 306.40 1105.58 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 326.65 374.34 216.53 0.34 2081.08 0.92 0.89

 MEAN 286.75 344.49 158.68 0.31 2124.38 0.92 0.89 0.89 1.27

 HUB 240.32 311.57 56.54 0.28 2554.08 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.05 1.04 7.59 525.18 1.01 516.84 502.78 27.32

 MEAN 8.06 1.04 7.58 525.30 1.01 516.60 502.94 27.51

 HUB 8.11 1.04 7.56 526.48 1.01 516.37 503.86 27.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.83 35.34 31.50 3.84 0.93 0.23 1.40

 MEAN 22.73 27.43 23.50 3.93 0.91 0.25 1.62

 HUB 30.96 10.46 6.50 3.96 0.91 0.30 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.978 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 359.8881 128.7966 336.0519 1104.5126 0.3258 -0.1422 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0679 7.5055 515.3987 503.6225 28.6068 20.9700 32.4000 11.4300

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 342.3465 76.7783 333.6259 1105.5490 0.3097 -0.0509 2.2705

 

NASA/TM—2013-218094 L–226
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0595 7.5493 516.3688 503.3405 432.2457 0.0269 0.1843

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 340.0002 0.0000 340.0002 1105.6613 0.3075 0.0492 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5332 516.4789 503.3973 0.0000 0.0600 0.0771 -0.0832

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7874 8.0345 1.0346 525.6272 6.1666 307.2637 2.3819

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38959.824 0.365 86.735 377575.625 0.530733E-02

 

Melt Ratio at Stator LE, Throat, TE

0.39206E+00 0.44463E+00 0.59554E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.206 EfDer = 0.947 SH = 0.557108E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.395 1982.604 8.035 525.618 1.000 1.000 0.980

 W Kg/sec = 17.907 Wdry = 39.176 WH2O = 0.219 lbm/sec H2O = 3.563g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.557 1969.497 1.374 0.253 53.529 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59324.609 30843.330 2.391 509.668 213.122 384.739 1.805

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 279.35 -0.10 279.35 0.25 0.38 314.86

 MEAN 15.91 0.00 -0.02 279.35 -0.10 279.35 0.25 0.35

 HUB 13.07 0.00 -0.02 279.35 -0.10 279.35 0.25 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.62 47.36 1.26 316.96 422.57 7.69 519.45 502.98 27.13

 MEAN 44.59 44.80 -0.21 275.32 392.29 7.69 519.45 502.98 27.13

 HUB 39.00 38.84 0.16 226.13 359.47 7.69 519.45 502.98 27.13

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 315.70 94.80 301.13 1111.91 0.28 2.05 1.78 7.43

 MEAN 15.50 321.05 110.26 301.52 1111.64 0.29 2.13 1.86 5.75

 HUB 12.59 342.62 161.56 302.14 1111.38 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 310.39 370.35 215.59 0.33 1702.49 0.92 0.87

 MEAN 268.13 340.34 157.87 0.31 1710.36 0.92 0.87 0.87 1.25

 HUB 217.83 307.33 56.27 0.28 2035.26 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.26 1.03 7.82 530.26 1.01 522.38 505.52 25.22

 MEAN 8.26 1.03 7.81 530.28 1.01 522.14 505.62 25.40

 HUB 8.31 1.03 7.79 531.17 1.01 521.89 506.32 25.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 17.47 35.60 31.50 4.10 0.93 0.20 1.40

 MEAN 20.09 27.64 23.50 4.14 0.90 0.22 1.64

 HUB 28.13 10.55 6.50 4.05 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.947 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 362.1640 112.2859 344.3177 1109.5616 0.3264 -0.2459 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2686 7.6905 520.1980 506.4580 26.8891 18.0617 33.0000 14.9383

 

NASA/TM—2013-218094 L–227
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 357.4572 81.6256 348.0128 1109.8452 0.3221 -0.2588 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2449 7.6825 520.4641 506.3932 410.5396 0.0701 0.1520

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 347.7498 0.0000 347.7498 1110.4167 0.3132 0.0148 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6991 521.0057 506.4770 0.0000 0.0600 0.1002 -0.2237

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7002 8.2307 1.0244 530.5620 4.9547 357.4706 2.7711

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31348.420 0.325 69.790 400188.813 0.585908E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0797 Tt4 = 530.5620 T1 = 491.4104

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 246706.89 549.2332 86.5482 1.2638 0.8286 9.4886 1.0797 37.3740

NASA/TM—2013-218094 L–228
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.949 EfDer = 0.999 SH = 0.231821E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.390 1807.241 7.939 506.408 1.000 1.000 0.980

 W Kg/sec = 21.996 Wdry = 48.278 WH2O = 0.112 lbm/sec H2O = 1.546g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.532 1829.042 1.378 0.250 53.423 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 69888.047 37934.949 3.204 831.557 259.531 619.754 2.388

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 201.71 -0.07 201.71 0.18 0.35 329.27

 MEAN 17.06 0.00 -0.02 201.71 -0.07 201.71 0.18 0.31

 HUB 12.51 0.00 -0.02 201.71 -0.07 201.71 0.18 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.21 50.47 7.74 325.36 382.87 7.76 503.16 488.04 20.78

 MEAN 53.15 47.20 5.95 269.06 336.33 7.76 503.16 488.04 20.78

 HUB 44.38 38.62 5.76 197.30 282.20 7.76 503.16 488.04 20.78

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.23 175.41 278.61 1095.80 0.30 7.29 6.52 16.04

 MEAN 18.04 343.83 199.82 279.80 1094.91 0.31 7.43 6.80 12.53

 HUB 15.00 387.04 264.77 282.31 1093.18 0.35 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 325.36 316.40 149.94 0.29 3620.23 0.92 0.91

 MEAN 284.45 292.32 84.63 0.27 3605.19 0.92 0.91 0.91 1.29

 HUB 236.57 283.71 28.20 0.26 3972.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.92 515.52 1.02 506.87 495.14 23.03

 MEAN 8.42 1.06 7.88 515.49 1.02 506.05 495.31 23.61

 HUB 8.47 1.07 7.78 516.41 1.02 504.45 496.35 24.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.19 28.29 24.20 4.09 0.93 0.30 1.80

 MEAN 35.53 16.83 12.70 4.13 0.92 0.27 2.22

 HUB 43.16 -5.70 -9.30 3.60 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 360.6538 199.4344 300.4948 1094.1565 0.3296 -0.0723 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4352 7.8330 505.4413 495.9193 24.8086 33.5717 35.4000 1.8283

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 305.5260 74.7410 296.2430 1097.3046 0.2784 0.2386 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4333 7.9979 508.3699 495.4578 554.9116 0.0133 0.3569

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 303.2363 0.0000 303.2363 1097.4059 0.2763 0.2621 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9909 508.4830 496.1304 0.0000 0.0600 0.0378 0.2264

NASA/TM—2013-218094 L–229
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 8.4191 1.0605 515.8066 9.3989 220.1721 1.7068

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58976.383 0.557 161.276 471293.594 0.337813E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.519 EfDer = 0.989 SH = 0.437736E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.390 1807.241 8.419 515.802 1.000 1.000 0.980

 W Kg/sec = 21.996 Wdry = 48.179 WH2O = 0.212 lbm/sec H2O = 2.991g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.255 1812.303 1.376 0.252 53.490 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68199.953 37903.984 2.388 590.487 247.290 468.502 1.895

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 277.17 -0.10 277.17 0.25 0.39 325.00

 MEAN 18.08 0.00 -0.02 277.17 -0.10 277.17 0.25 0.36

 HUB 15.21 0.00 -0.02 277.17 -0.10 277.17 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.47 46.36 3.11 324.10 426.53 8.06 509.71 498.15 31.85

 MEAN 45.82 42.30 3.52 285.11 397.71 8.06 509.71 498.15 31.85

 HUB 40.89 37.84 3.05 239.88 366.62 8.06 509.71 498.15 31.85

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.29 109.66 301.99 1102.29 0.29 2.33 2.04 9.02

 MEAN 18.01 328.52 128.57 302.32 1102.09 0.30 2.40 2.13 7.35

 HUB 15.22 354.97 185.17 302.84 1101.90 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.05 369.20 212.39 0.33 2241.21 0.92 0.91

 MEAN 284.04 339.95 155.47 0.31 2317.24 0.92 0.91 0.91 1.26

 HUB 240.08 307.78 54.92 0.28 2820.24 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.23 521.41 1.01 513.22 501.57 29.49

 MEAN 8.74 1.04 8.22 521.60 1.01 513.03 501.76 29.65

 HUB 8.81 1.05 8.21 522.85 1.01 512.86 502.74 29.78

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.96 35.12 31.50 3.62 0.93 0.23 1.40

 MEAN 23.04 27.21 23.50 3.71 0.92 0.24 1.63

 HUB 31.44 10.28 6.50 3.78 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.7443 128.9297 341.1972 1100.3076 0.3315 -0.1912 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7514 8.1206 511.3979 502.5922 31.2876 20.7003 30.6000 9.8997

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 336.9402 71.4337 329.2810 1101.9642 0.3058 -0.0333 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7438 8.2034 512.9413 502.1540 491.5697 0.0241 0.1688

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 349.4140 0.0000 349.4140 1101.2135 0.3173 0.0344 0.5911

NASA/TM—2013-218094 L–230
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1423 512.2495 502.5110 0.0000 0.0600 0.0679 -0.1474

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8117 8.7204 1.0358 521.9297 6.1499 297.8423 2.3089

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38780.395 0.374 106.049 437369.469 0.465806E-02

 

Melt Ratio at Stator LE, Throat, TE

0.28245E+00 0.32757E+00 0.46066E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.159 EfDer = 0.952 SH = 0.493950E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.390 1807.241 8.720 521.923 1.000 1.000 0.980

 W Kg/sec = 21.996 Wdry = 48.151 WH2O = 0.239 lbm/sec H2O = 3.442g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.825 1801.641 1.375 0.252 53.509 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66890.664 37895.496 2.270 545.479 240.253 424.468 1.767

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 294.30 -0.10 294.30 0.27 0.39 315.54

 MEAN 17.74 0.00 -0.02 294.30 -0.10 294.30 0.27 0.37

 HUB 15.05 0.00 -0.02 294.30 -0.10 294.30 0.27 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.09 46.36 0.73 316.53 432.28 8.31 515.06 502.25 30.42

 MEAN 43.56 43.40 0.16 279.76 406.12 8.31 515.06 502.25 30.42

 HUB 38.90 38.84 0.06 237.36 378.15 8.31 515.06 502.25 30.42

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 332.40 84.68 321.43 1106.63 0.30 2.26 1.98 8.75

 MEAN 17.51 339.32 109.30 321.23 1106.86 0.31 2.34 2.07 6.78

 HUB 14.85 365.65 174.46 321.35 1107.10 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 312.43 393.94 227.75 0.36 1679.51 0.92 0.87

 MEAN 276.10 361.96 166.80 0.33 1915.21 0.92 0.87 0.87 1.20

 HUB 234.20 326.86 59.75 0.30 2592.19 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.95 1.03 8.41 526.11 1.01 517.36 504.78 28.87

 MEAN 8.98 1.03 8.42 526.70 1.01 517.58 505.14 28.67

 HUB 9.07 1.04 8.42 528.39 1.01 517.80 506.30 28.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.76 35.32 31.50 3.82 0.93 0.16 1.40

 MEAN 18.79 27.44 23.50 3.94 0.90 0.19 1.62

 HUB 28.50 10.53 6.50 4.03 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.952 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 378.7224 110.0138 362.3915 1104.8369 0.3428 -0.2055 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9924 8.3019 515.6992 506.0461 30.3565 16.8871 31.5000 14.6129

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 364.1768 79.4427 355.4062 1105.7456 0.3293 -0.1392 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9773 8.3376 516.5479 505.7702 451.3937 0.0360 0.1242

 

NASA/TM—2013-218094 L–231
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 371.2444 0.0000 371.2444 1105.2823 0.3359 -0.0304 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2808 516.1187 505.9771 0.0000 0.0600 0.0980 -0.2371

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6993 8.9413 1.0253 527.0300 5.1407 337.0226 2.6126

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 32467.641 0.333 88.786 442965.531 0.513358E-02

 

Melt Ratio at Stator LE, Throat, TE

0.84750E+00 0.89858E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.902 EfDer = 0.896 SH = 0.561168E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.390 1807.241 8.941 527.029 1.000 1.000 0.980

 W Kg/sec = 21.996 Wdry = 48.119 WH2O = 0.272 lbm/sec H2O = 3.956g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.193 1792.902 1.374 0.253 53.530 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66120.719 37885.324 2.179 513.330 235.554 395.845 1.680

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 309.13 -0.11 309.13 0.28 0.39 301.33

 MEAN 16.97 0.00 -0.02 309.13 -0.11 309.13 0.28 0.37

 HUB 14.32 0.00 -0.02 309.13 -0.11 309.13 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.51 46.36 -1.85 303.75 433.46 8.48 519.48 505.89 30.09

 MEAN 40.90 43.80 -2.90 267.65 408.96 8.48 519.48 505.89 30.09

 HUB 36.16 37.84 -1.68 225.84 382.90 8.48 519.48 505.89 30.09

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 341.82 57.68 336.91 1109.89 0.31 2.16 1.89 8.34

 MEAN 16.57 347.07 85.69 336.33 1110.46 0.31 2.24 1.97 6.35

 HUB 13.89 370.63 156.01 336.20 1111.02 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 297.76 413.70 240.08 0.37 1091.12 0.92 0.82

 MEAN 261.39 379.46 175.70 0.34 1422.03 0.92 0.82 0.82 1.15

 HUB 219.06 342.06 63.05 0.31 2168.49 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.08 1.02 8.51 529.75 1.01 520.51 507.93 30.17

 MEAN 9.12 1.02 8.54 530.57 1.01 521.05 508.35 29.68

 HUB 9.22 1.03 8.55 532.43 1.01 521.58 509.51 29.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.72 35.47 31.50 3.97 0.93 0.09 1.40

 MEAN 14.29 27.58 23.50 4.08 0.89 0.14 1.62

 HUB 24.89 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.896 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 380.3008 86.1723 370.4093 1108.7682 0.3430 -0.1688 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1358 8.4339 519.4948 509.2286 31.2434 13.0964 32.4000 19.3036

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 379.7025 85.1562 370.0302 1108.8038 0.3424 -0.1929 2.2705

 

NASA/TM—2013-218094 L–232
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1133 8.4153 519.5323 509.2596 432.2457 0.0469 0.0876

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 378.0727 0.0000 378.0727 1108.9028 0.3409 -0.0829 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3757 519.6312 509.3978 0.0000 0.0600 0.1276 -0.2580

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5034 9.0641 1.0137 530.9192 3.8903 412.2439 3.1957

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 24628.252 0.278 67.348 461567.781 0.603701E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.752 EfDer = 0.833 SH = 0.657059E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.390 1807.241 9.064 530.918 1.000 1.000 0.980

 W Kg/sec = 21.996 Wdry = 48.073 WH2O = 0.318 lbm/sec H2O = 4.659g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.398 1786.323 1.373 0.253 53.561 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65733.000 37870.785 2.184 509.668 233.355 384.739 1.649

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 309.52 -0.11 309.52 0.28 0.38 285.57

 MEAN 15.91 0.00 -0.02 309.52 -0.11 309.52 0.28 0.36

 HUB 13.07 0.00 -0.02 309.52 -0.11 309.52 0.28 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.04 47.36 -4.32 288.93 423.49 8.60 523.37 509.13 31.13

 MEAN 39.05 44.80 -5.75 250.97 398.55 8.60 523.37 509.13 31.13

 HUB 33.68 38.84 -5.16 206.13 371.93 8.60 523.37 509.13 31.13

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 340.22 39.70 337.89 1112.99 0.31 2.05 1.78 7.43

 MEAN 15.50 343.80 66.57 337.29 1113.63 0.31 2.13 1.86 5.75

 HUB 12.59 363.10 134.66 337.21 1114.24 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.93 416.34 243.24 0.37 714.11 0.92 0.76

 MEAN 244.42 381.31 177.84 0.34 1033.38 0.92 0.76 0.76 1.11

 HUB 198.56 343.21 63.90 0.31 1696.74 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.15 1.01 8.59 532.69 1.00 523.57 510.77 31.91

 MEAN 9.19 1.01 8.61 533.49 1.00 524.17 511.13 31.33

 HUB 9.27 1.02 8.62 535.14 1.01 524.74 512.11 30.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.70 35.75 31.50 4.25 0.93 0.05 1.40

 MEAN 11.16 27.80 23.50 4.30 0.87 0.09 1.64

 HUB 21.77 10.73 6.50 4.23 0.87 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.833 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 392.4443 67.7910 386.5449 1110.9052 0.3533 -0.2807 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1898 8.4438 521.6422 512.3715 33.8386 9.9472 33.0000 23.0528

 

NASA/TM—2013-218094 L–233
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 404.5717 92.3843 393.8825 1110.0923 0.3644 -0.4301 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1371 8.3503 520.8829 512.6508 410.5396 0.1086 0.0598

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 393.5164 0.0000 393.5164 1110.8291 0.3543 -0.0957 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3723 521.5792 512.5975 0.0000 0.0600 0.1435 -0.3931

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2901 9.1163 1.0058 533.7725 2.8539 517.4156 4.0110

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 18119.623 0.226 49.550 491559.125 0.702378E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0540 Tt4 = 533.7725 T1 = 506.4083

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 172972.30 473.0085 88.5317 1.1483 0.7106 5.9489 1.0540 37.3740

NASA/TM—2013-218094 L–234
 5μm, 4g/m3

, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.918 EfDer = 0.951 SH = 0.216939E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.715 2491.186 4.265 477.903 1.000 1.000 0.980

 W Kg/sec = 11.689 Wdry = 25.660 WH2O = 0.056 lbm/sec H2O = 0.825g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.085 2595.293 1.379 0.250 53.419 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65153.953 20160.357 3.335 831.557 249.376 619.754 2.485

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 188.04 -0.06 188.04 0.18 0.46 467.22

 MEAN 17.06 0.00 -0.02 188.04 -0.06 188.04 0.18 0.39

 HUB 12.51 0.00 -0.02 188.04 -0.06 188.04 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.26 50.47 16.79 448.49 486.38 4.17 475.08 466.80 32.99

 MEAN 63.12 47.20 15.92 370.88 415.89 4.17 475.08 466.80 32.99

 HUB 55.35 38.62 16.73 271.96 330.70 4.17 475.08 466.80 32.99

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 400.74 312.08 251.39 1074.77 0.37 7.29 6.52 16.04

 MEAN 18.04 404.58 314.27 254.79 1071.54 0.38 7.43 6.80 12.53

 HUB 15.00 436.86 351.47 259.45 1067.61 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 448.49 286.02 136.41 0.27 6439.46 0.92 0.87

 MEAN 392.10 266.41 77.83 0.25 5669.20 0.92 0.87 0.87 1.79

 HUB 326.10 260.69 25.37 0.24 5272.84 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.93 1.16 4.49 500.28 1.05 487.44 483.06 29.99

 MEAN 4.85 1.14 4.40 497.60 1.04 484.52 481.97 33.20

 HUB 4.81 1.13 4.29 496.23 1.04 480.97 482.10 37.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 51.15 28.49 24.20 4.29 0.93 0.59 1.80

 MEAN 50.97 16.99 12.70 4.29 0.95 0.53 2.22

 HUB 53.57 -5.59 -9.30 3.71 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.951 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 416.0851 313.6549 273.3998 1071.0575 0.3885 -0.0344 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8569 4.3837 484.2385 482.7358 34.7603 48.9227 35.4000 -13.5227

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 271.0297 66.3021 262.7949 1079.7751 0.2510 0.5268 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8438 4.6393 492.1823 480.8011 554.9116 0.0378 0.6205

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 270.0361 0.0000 270.0361 1079.7723 0.2501 0.4930 1.3089

NASA/TM—2013-218094 L–235
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6170 492.2282 482.2071 0.0000 0.0600 0.0907 0.4794

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8068 4.8189 1.1300 498.0333 20.1333 165.5014 1.2830

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 126329.250 0.628 183.582 261214.828 0.403095E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.524 EfDer = 0.954 SH = 0.598272E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.715 2491.186 4.819 498.031 1.000 1.000 0.980

 W Kg/sec = 11.689 Wdry = 25.562 WH2O = 0.154 lbm/sec H2O = 2.435g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.865 2542.348 1.374 0.253 53.542 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60856.477 20129.814 2.615 590.487 225.794 468.502 2.075

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 247.31 -0.09 247.31 0.23 0.47 455.91

 MEAN 18.08 0.00 -0.02 247.31 -0.09 247.31 0.23 0.43

 HUB 15.21 0.00 -0.02 247.31 -0.09 247.31 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.04 46.36 14.68 446.75 510.71 4.65 493.20 486.13 47.51

 MEAN 57.82 42.30 15.52 393.02 464.43 4.65 493.20 486.13 47.51

 HUB 53.21 37.84 15.37 330.66 412.99 4.65 493.20 486.13 47.51

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 368.50 261.02 260.11 1093.94 0.34 2.33 2.04 9.02

 MEAN 18.01 367.31 256.58 262.83 1091.38 0.34 2.40 2.13 7.35

 HUB 15.22 388.37 283.10 265.86 1088.85 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 443.92 317.98 182.90 0.29 5331.86 0.92 0.87

 MEAN 391.53 295.46 134.95 0.27 4622.49 0.92 0.87 0.87 1.73

 HUB 330.94 270.13 47.84 0.25 4311.00 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.41 1.12 5.01 516.34 1.04 505.62 496.28 33.38

 MEAN 5.33 1.11 4.94 513.91 1.03 503.25 495.37 35.98

 HUB 5.29 1.10 4.86 512.84 1.03 500.92 495.50 38.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 45.10 35.11 31.50 3.61 0.93 0.56 1.40

 MEAN 44.31 27.18 23.50 3.68 0.95 0.53 1.63

 HUB 46.80 10.20 6.50 3.70 0.95 0.52 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 392.1014 257.2978 295.8739 1090.2059 0.3597 -0.1034 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3415 4.8926 502.2312 496.2551 37.4654 41.0109 30.6000 -10.4109

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 285.9327 60.6198 279.4330 1096.3420 0.2608 0.3849 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3344 5.0924 507.9117 494.2018 491.5697 0.0273 0.4793

 

NASA/TM—2013-218094 L–236
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.4682 0.0000 296.4682 1095.7985 0.2705 0.3675 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0576 507.4296 494.9498 0.0000 0.0600 0.0709 0.3002

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8247 5.3165 1.1032 514.3613 16.3313 185.7310 1.4398

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 103498.055 0.525 150.403 237501.219 0.683387E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.554 EfDer = 0.970 SH = 0.801966E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.715 2491.186 5.316 514.360 1.000 1.000 0.980

 W Kg/sec = 11.689 Wdry = 25.509 WH2O = 0.206 lbm/sec H2O = 3.483g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.805 2501.671 1.371 0.254 53.608 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57036.309 20113.355 2.619 545.479 208.264 424.468 2.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.93 -0.09 250.93 0.23 0.46 438.14

 MEAN 17.74 0.00 -0.02 250.93 -0.09 250.93 0.23 0.42

 HUB 15.05 0.00 -0.02 250.93 -0.09 250.93 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.10 46.36 13.74 436.32 503.40 5.13 509.42 496.26 37.54

 MEAN 56.95 43.40 13.55 385.63 460.15 5.13 509.42 496.26 37.54

 HUB 52.52 38.84 13.68 327.18 412.39 5.13 509.42 496.26 37.54

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 359.88 244.76 263.84 1109.84 0.32 2.26 1.98 8.75

 MEAN 17.51 360.78 243.47 266.25 1107.65 0.33 2.34 2.07 6.78

 HUB 14.85 383.92 274.01 268.91 1105.50 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 430.66 322.76 185.91 0.29 4850.33 0.92 0.89

 MEAN 380.59 299.48 137.12 0.27 4263.83 0.92 0.89 0.89 1.69

 HUB 322.83 273.31 48.83 0.25 4070.29 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.90 1.11 5.49 530.90 1.03 520.74 504.66 27.67

 MEAN 5.83 1.10 5.42 528.90 1.03 518.68 504.02 29.39

 HUB 5.80 1.09 5.35 528.24 1.03 516.67 504.36 31.15

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 42.85 35.17 31.50 3.67 0.93 0.53 1.40

 MEAN 42.44 27.25 23.50 3.75 0.94 0.51 1.62

 HUB 45.54 10.29 6.50 3.79 0.94 0.51 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.970 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 386.7586 245.0662 299.2069 1106.4474 0.3495 -0.1113 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8379 5.3739 517.6092 504.8708 30.4893 39.3193 31.5000 -7.8193

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 294.1394 64.1645 287.0556 1111.6971 0.2646 0.3334 2.3726

 

NASA/TM—2013-218094 L–237
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8332 5.5606 522.5413 502.9861 451.3937 0.0212 0.4546

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 299.1032 0.0000 299.1032 1111.3840 0.2691 0.3542 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5382 522.2593 503.2300 0.0000 0.0600 0.0567 0.2804

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8515 5.8182 1.0944 529.2734 14.9914 190.8676 1.4796

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 95582.367 0.515 138.900 236214.281 0.858682E-02

 

Melt Ratio at Stator LE, Throat, TE

0.25141E+00 0.33050E+00 0.56987E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =12.013 EfDer = 0.980 SH = 0.899243E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.715 2491.186 5.818 529.250 1.000 1.000 0.980

 W Kg/sec = 11.689 Wdry = 25.484 WH2O = 0.231 lbm/sec H2O = 4.154g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.630 2466.177 1.370 0.255 53.640 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53616.199 20105.457 2.657 513.330 193.165 395.845 2.049

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.67 -0.09 250.67 0.23 0.44 414.49

 MEAN 16.97 0.00 -0.02 250.67 -0.09 250.67 0.23 0.40

 HUB 14.32 0.00 -0.02 250.67 -0.09 250.67 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.10 46.36 12.74 418.71 488.08 5.62 524.33 503.06 26.93

 MEAN 55.81 43.80 12.01 368.94 446.11 5.62 524.33 503.06 26.93

 HUB 51.17 37.84 13.33 311.31 399.75 5.62 524.33 503.06 26.93

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.98 225.04 262.79 1124.05 0.31 2.16 1.89 8.34

 MEAN 16.57 346.81 223.76 264.97 1122.07 0.31 2.24 1.97 6.35

 HUB 13.89 368.45 253.53 267.35 1120.12 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.45 321.61 185.40 0.29 4250.49 0.92 0.90

 MEAN 360.31 298.09 136.55 0.27 3710.03 0.92 0.90 0.90 1.64

 HUB 301.96 271.70 48.43 0.24 3522.82 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.36 1.09 5.97 543.68 1.03 534.31 509.66 20.55

 MEAN 6.29 1.08 5.90 541.84 1.02 532.43 509.08 21.63

 HUB 6.27 1.08 5.82 541.21 1.02 530.58 509.33 22.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.58 35.20 31.50 3.70 0.93 0.50 1.40

 MEAN 40.18 27.26 23.50 3.76 0.94 0.49 1.62

 HUB 43.48 10.27 6.50 3.77 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.980 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 367.4749 225.0177 290.5251 1121.2528 0.3277 -0.0879 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3027 5.8598 531.6738 509.7841 22.3142 37.7585 32.4000 -5.3585

 

NASA/TM—2013-218094 L–238
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 291.4368 65.3607 284.0130 1125.3629 0.2590 0.3002 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3001 6.0187 535.5947 508.6056 432.2457 0.0163 0.4338

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.1937 0.0000 289.1937 1125.4418 0.2570 0.3423 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0114 535.6990 509.2786 0.0000 0.0600 0.0463 0.2825

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8616 6.2878 1.0807 542.2378 12.9947 205.6480 1.5942

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83042.813 0.493 120.678 241763.719 0.990792E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.560 EfDer = 0.989 SH = 0.119497E-01

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.715 2491.186 6.288 542.235 1.000 1.000 0.980

 W Kg/sec = 11.689 Wdry = 25.408 WH2O = 0.307 lbm/sec H2O = 5.829g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.468 2436.517 1.367 0.257 53.736 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50776.730 20081.309 2.812 509.668 181.220 384.739 2.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.07 -0.08 239.07 0.21 0.41 389.52

 MEAN 15.91 0.00 -0.02 239.07 -0.08 239.07 0.21 0.37

 HUB 13.07 0.00 -0.02 239.07 -0.08 239.07 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.03 47.36 11.67 398.27 464.59 6.10 537.80 511.16 24.59

 MEAN 55.36 44.80 10.56 345.94 420.58 6.10 537.80 511.16 24.59

 HUB 49.93 38.84 11.09 284.14 371.40 6.10 537.80 511.16 24.59

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 328.46 211.61 251.21 1136.54 0.29 2.05 1.78 7.43

 MEAN 15.50 326.32 205.69 253.33 1134.52 0.29 2.13 1.86 5.75

 HUB 12.59 342.09 227.36 255.60 1132.52 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 390.01 308.11 178.40 0.27 3797.82 0.92 0.90

 MEAN 336.91 285.30 131.23 0.25 3188.97 0.92 0.90 0.90 1.63

 HUB 273.70 259.77 46.34 0.23 2863.54 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.80 1.08 6.43 555.05 1.02 546.68 517.67 20.79

 MEAN 6.72 1.07 6.35 552.99 1.02 544.73 517.02 21.85

 HUB 6.67 1.06 6.27 551.89 1.02 542.81 517.02 22.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.11 35.38 31.50 3.88 0.93 0.50 1.40

 MEAN 39.07 27.38 23.50 3.88 0.94 0.47 1.64

 HUB 41.65 10.28 6.50 3.78 0.94 0.45 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 356.4271 209.4589 288.3874 1133.0927 0.3146 -0.1664 2.0437

 

NASA/TM—2013-218094 L–239
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7244 6.2889 543.4775 517.9210 22.8130 35.9913 33.0000 -2.9913

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.4162 67.2302 286.6374 1136.3239 0.2591 0.1864 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7218 6.4225 546.6039 516.9085 410.5396 0.0267 0.4089

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.4656 0.0000 286.4656 1136.6654 0.2520 0.3321 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4335 546.9641 517.5077 0.0000 0.0600 0.0397 0.2154

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8713 6.7169 1.0683 553.3094 11.0765 223.7549 1.7345

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71556.344 0.470 103.986 253887.156 0.137842E-01

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1578 Tt4 = 553.3094 T1 = 477.9028

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 480008.84 697.5491 85.0848 1.5750 0.8285 15.9182 1.1578 37.3740

NASA/TM—2013-218094 L–240
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.820 EfDer = 0.951 SH = 0.189374E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 24.934 2407.715 4.199 471.460 1.000 1.000 0.980

 W Kg/sec = 11.334 Wdry = 24.887 WH2O = 0.047 lbm/sec H2O = 0.719g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.217 2525.419 1.379 0.250 53.410 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 63237.621 19549.883 3.410 831.557 243.858 619.754 2.541

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 182.51 -0.06 182.51 0.17 0.45 454.64

 MEAN 17.06 0.00 -0.02 182.51 -0.06 182.51 0.17 0.38

 HUB 12.51 0.00 -0.02 182.51 -0.06 182.51 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.17 50.47 16.70 433.46 470.38 4.11 468.80 462.60 37.49

 MEAN 63.02 47.20 15.82 358.46 402.30 4.11 468.80 462.60 37.49

 HUB 55.23 38.62 16.61 262.85 320.05 4.11 468.80 462.60 37.49

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 387.73 300.80 244.65 1066.93 0.36 7.29 6.52 16.04

 MEAN 18.04 391.67 303.34 247.77 1063.91 0.37 7.43 6.80 12.53

 HUB 15.00 423.13 339.87 252.05 1060.22 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 433.46 278.30 132.66 0.26 6206.87 0.92 0.87

 MEAN 378.96 259.05 75.62 0.24 5472.13 0.92 0.87 0.87 1.78

 HUB 315.17 253.26 24.70 0.24 5098.81 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.82 1.15 4.40 492.33 1.04 480.30 478.28 33.89

 MEAN 4.74 1.13 4.32 489.86 1.04 477.58 477.19 37.38

 HUB 4.70 1.12 4.22 488.60 1.04 474.28 477.27 42.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.88 28.47 24.20 4.27 0.93 0.59 1.80

 MEAN 50.76 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.44 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.951 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 402.8748 302.7512 265.8002 1063.4613 0.3788 -0.0350 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7498 4.3082 477.3061 477.8948 39.0366 48.7185 35.4000 -13.3185

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 264.0760 64.6010 256.0524 1071.6307 0.2464 0.5230 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7383 4.5452 484.6949 476.1440 554.9116 0.0363 0.6158

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 263.0409 0.0000 263.0409 1071.6282 0.2455 0.4895 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5244 484.7409 477.3961 0.0000 0.0600 0.0893 0.4757

NASA/TM—2013-218094 L–241
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8087 4.7151 1.1229 490.2582 18.8008 166.0762 1.2874

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 117792.625 0.627 165.975 255670.578 0.339530E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.325 EfDer = 0.956 SH = 0.493407E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 24.934 2407.715 4.715 490.256 1.000 1.000 0.980

 W Kg/sec = 11.334 Wdry = 24.811 WH2O = 0.123 lbm/sec H2O = 1.999g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.575 2476.571 1.375 0.252 53.508 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59271.133 19526.318 2.661 590.487 221.864 468.502 2.112

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 240.88 -0.08 240.88 0.22 0.46 444.12

 MEAN 18.08 0.00 -0.02 240.88 -0.08 240.88 0.22 0.42

 HUB 15.21 0.00 -0.02 240.88 -0.08 240.88 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.85 46.36 14.49 431.78 494.50 4.56 485.66 480.83 52.21

 MEAN 57.62 42.30 15.32 379.85 449.86 4.56 485.66 480.83 52.21

 HUB 53.00 37.84 15.16 319.58 400.26 4.56 485.66 480.83 52.21

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 356.79 250.54 254.03 1085.00 0.33 2.33 2.04 9.02

 MEAN 18.01 355.96 246.78 256.53 1082.60 0.33 2.40 2.13 7.35

 HUB 15.22 376.72 273.26 259.31 1080.25 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 429.05 310.48 178.51 0.29 5117.67 0.92 0.87

 MEAN 378.41 288.33 131.63 0.27 4446.06 0.92 0.87 0.87 1.72

 HUB 319.85 263.46 46.59 0.24 4161.15 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.26 1.12 4.89 507.30 1.03 497.21 490.74 37.08

 MEAN 5.19 1.10 4.82 505.06 1.03 495.02 489.84 39.86

 HUB 5.16 1.09 4.75 504.11 1.03 492.87 489.95 42.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.60 35.10 31.50 3.60 0.93 0.55 1.40

 MEAN 43.89 27.16 23.50 3.66 0.95 0.53 1.63

 HUB 46.50 10.19 6.50 3.69 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 380.2552 247.4764 288.7031 1081.4696 0.3516 -0.1051 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1982 4.7793 494.0432 490.6732 41.4968 40.6032 30.6000 -10.0032

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 279.4667 59.2489 273.1139 1087.2061 0.2571 0.3767 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1921 4.9629 499.3079 488.8354 491.5697 0.0258 0.4716

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 289.6720 0.0000 289.6720 1086.6830 0.2666 0.3613 0.5911

NASA/TM—2013-218094 L–242
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9306 498.8498 489.5150 0.0000 0.0600 0.0685 0.2925

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8276 5.1758 1.0977 505.4905 15.2354 187.1101 1.4505

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 96223.336 0.523 135.583 232657.516 0.561069E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.265 EfDer = 0.972 SH = 0.655338E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 24.934 2407.715 5.176 505.489 1.000 1.000 0.980

 W Kg/sec = 11.334 Wdry = 24.771 WH2O = 0.163 lbm/sec H2O = 2.824g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.909 2438.971 1.373 0.253 53.561 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55735.516 19513.680 2.655 545.479 205.447 424.468 2.066

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 245.21 -0.08 245.21 0.23 0.45 427.16

 MEAN 17.74 0.00 -0.02 245.21 -0.08 245.21 0.23 0.41

 HUB 15.05 0.00 -0.02 245.21 -0.08 245.21 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.83 46.36 13.47 421.70 487.88 5.00 500.75 490.67 41.56

 MEAN 56.66 43.40 13.26 372.71 446.21 5.00 500.75 490.67 41.56

 HUB 52.22 38.84 13.38 316.22 400.22 5.00 500.75 490.67 41.56

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 348.78 234.20 258.46 1099.94 0.32 2.26 1.98 8.75

 MEAN 17.51 350.07 233.66 260.68 1097.90 0.32 2.34 2.07 6.78

 HUB 14.85 372.93 264.27 263.13 1095.90 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 416.23 316.13 182.04 0.29 4641.10 0.92 0.89

 MEAN 367.83 293.18 134.18 0.27 4092.07 0.92 0.89 0.89 1.67

 HUB 312.02 267.42 47.74 0.24 3925.72 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.71 1.10 5.33 520.87 1.03 511.27 499.14 31.56

 MEAN 5.64 1.09 5.27 519.05 1.03 509.38 498.52 33.44

 HUB 5.63 1.09 5.20 518.50 1.03 507.53 498.85 35.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 42.18 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.87 27.24 23.50 3.74 0.94 0.50 1.62

 HUB 45.12 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 375.6573 235.1925 292.9214 1096.7272 0.3425 -0.1135 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6560 5.2229 508.3568 499.3832 34.8184 38.7617 31.5000 -7.2617

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 288.3598 62.9037 281.4151 1101.6283 0.2618 0.3241 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6521 5.3940 512.9222 497.7737 451.3937 0.0198 0.4446

 

NASA/TM—2013-218094 L–243
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 293.2446 0.0000 293.2446 1101.3586 0.2663 0.3457 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3726 512.6902 498.3148 0.0000 0.0600 0.0541 0.2697

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8503 5.6386 1.0894 519.4589 13.9814 192.7484 1.4942

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 88774.953 0.512 125.088 231657.281 0.741412E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.69384E-02 0.76522E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.615 EfDer = 0.983 SH = 0.827915E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 24.934 2407.715 5.639 519.449 1.000 1.000 0.980

 W Kg/sec = 11.334 Wdry = 24.728 WH2O = 0.206 lbm/sec H2O = 3.780g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.051 2405.956 1.371 0.255 53.617 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52600.465 19500.139 2.682 513.330 191.374 395.845 2.068

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 245.91 -0.08 245.91 0.22 0.43 404.37

 MEAN 16.97 0.00 -0.02 245.91 -0.08 245.91 0.22 0.39

 HUB 14.32 0.00 -0.02 245.91 -0.08 245.91 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.72 46.36 12.36 404.68 473.61 5.45 514.71 498.98 33.89

 MEAN 55.41 43.80 11.61 356.58 433.22 5.45 514.71 498.98 33.89

 HUB 50.75 37.84 12.91 300.88 388.65 5.45 514.71 498.98 33.89

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 335.78 214.45 258.38 1113.19 0.30 2.16 1.89 8.34

 MEAN 16.57 337.10 214.10 260.39 1111.37 0.30 2.24 1.97 6.35

 HUB 13.89 358.66 244.32 262.57 1109.57 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 396.69 316.19 182.24 0.28 4050.43 0.92 0.90

 MEAN 348.24 292.91 134.14 0.26 3549.90 0.92 0.90 0.90 1.62

 HUB 291.85 266.84 47.52 0.24 3394.86 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.13 1.09 5.77 532.78 1.03 523.94 505.58 26.41

 MEAN 6.07 1.08 5.70 531.13 1.02 522.22 505.05 27.74

 HUB 6.05 1.07 5.64 530.62 1.02 520.53 505.34 29.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.69 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.43 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.94 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.983 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 357.5772 215.3038 285.4921 1110.5421 0.3220 -0.0902 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0823 5.6689 521.4733 505.6588 28.4358 37.0218 32.4000 -4.6218

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 286.8073 64.3225 279.5014 1114.3159 0.2574 0.2817 2.2705

 

NASA/TM—2013-218094 L–244
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0803 5.8106 525.0294 504.3329 432.2457 0.0151 0.4216

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 284.4369 0.0000 284.4369 1114.3538 0.2552 0.3312 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8058 525.0735 504.3773 0.0000 0.0600 0.0439 0.2691

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8727 6.0693 1.0764 531.4146 12.0623 208.4571 1.6159

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76942.086 0.489 108.415 237483.266 0.863467E-02

 

Melt Ratio at Stator LE, Throat, TE

0.50822E+00 0.59188E+00 0.83101E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.122 EfDer = 0.991 SH = 0.888232E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 24.934 2407.715 6.069 531.387 1.000 1.000 0.980

 W Kg/sec = 11.334 Wdry = 24.713 WH2O = 0.221 lbm/sec H2O = 4.277g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.127 2378.737 1.370 0.255 53.636 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49875.109 19495.391 2.833 509.668 179.900 384.739 2.139

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 234.86 -0.08 234.86 0.21 0.40 380.28

 MEAN 15.91 0.00 -0.02 234.86 -0.08 234.86 0.21 0.37

 HUB 13.07 0.00 -0.02 234.86 -0.08 234.86 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.62 47.36 11.26 384.93 450.99 5.89 527.07 504.01 25.34

 MEAN 54.92 44.80 10.12 334.35 408.66 5.89 527.07 504.01 25.34

 HUB 49.47 38.84 10.63 274.62 361.41 5.89 527.07 504.01 25.34

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 318.89 201.37 247.27 1125.11 0.28 2.05 1.78 7.43

 MEAN 15.50 317.39 196.53 249.22 1123.22 0.28 2.13 1.86 5.75

 HUB 12.59 333.31 218.95 251.31 1121.36 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.94 303.26 175.57 0.27 3614.07 0.92 0.91

 MEAN 325.62 280.68 129.10 0.25 3046.99 0.92 0.91 0.91 1.61

 HUB 264.53 255.41 45.58 0.23 2757.65 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.54 1.08 6.19 543.27 1.02 535.30 510.06 21.25

 MEAN 6.46 1.06 6.12 541.40 1.02 533.51 509.42 22.31

 HUB 6.42 1.06 6.05 540.45 1.02 531.75 509.41 23.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.16 35.38 31.50 3.88 0.93 0.49 1.40

 MEAN 38.26 27.38 23.50 3.88 0.94 0.46 1.64

 HUB 41.06 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 347.1141 200.1311 283.6119 1121.8525 0.3094 -0.1696 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4672 6.0603 532.2856 510.2590 23.3442 35.2088 33.0000 -2.2088

 

NASA/TM—2013-218094 L–245
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 289.8647 66.1908 282.2061 1124.8351 0.2577 0.1686 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4653 6.1796 535.1385 509.4338 410.5396 0.0254 0.3961

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 282.0279 0.0000 282.0279 1125.1776 0.2507 0.3194 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1903 535.4908 509.9966 0.0000 0.0600 0.0383 0.1987

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8747 6.4607 1.0645 541.7042 10.3187 227.7472 1.7655

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65997.039 0.464 92.993 249354.516 0.101687E-01

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1490 Tt4 = 541.7042 T1 = 471.4601

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 445730.06 628.0527 83.2174 1.5386 0.8327 15.8204 1.1490 37.3740

NASA/TM—2013-218094 L–246
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.828 EfDer = 0.951 SH = 0.172602E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.520 2375.659 4.337 469.488 1.000 1.000 0.980

 W Kg/sec = 11.600 Wdry = 25.476 WH2O = 0.044 lbm/sec H2O = 0.680g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.291 2497.024 1.379 0.250 53.404 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62374.938 20010.354 3.449 831.557 241.118 619.754 2.570

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 180.02 -0.06 180.02 0.17 0.44 449.53

 MEAN 17.06 0.00 -0.02 180.02 -0.06 180.02 0.17 0.38

 HUB 12.51 0.00 -0.02 180.02 -0.06 180.02 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.18 50.47 16.71 427.69 464.09 4.25 466.89 461.36 38.47

 MEAN 63.03 47.20 15.83 353.68 396.92 4.25 466.89 461.36 38.47

 HUB 55.24 38.62 16.62 259.35 315.76 4.25 466.89 461.36 38.47

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 382.62 296.73 241.56 1064.50 0.36 7.29 6.52 16.04

 MEAN 18.04 386.51 299.29 244.57 1061.56 0.36 7.43 6.80 12.53

 HUB 15.00 417.50 335.34 248.70 1057.96 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 427.69 274.78 130.97 0.26 6122.73 0.92 0.87

 MEAN 373.91 255.70 74.63 0.24 5399.01 0.92 0.87 0.87 1.78

 HUB 310.97 249.89 24.37 0.24 5030.92 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.96 1.14 4.54 489.81 1.04 478.09 476.82 34.82

 MEAN 4.88 1.13 4.46 487.41 1.04 475.45 475.71 38.35

 HUB 4.85 1.12 4.36 486.18 1.04 472.23 475.73 43.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.85 28.46 24.20 4.26 0.93 0.59 1.80

 MEAN 50.75 16.97 12.70 4.27 0.95 0.53 2.22

 HUB 53.44 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.951 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.5534 298.7058 262.3425 1061.1267 0.3747 -0.0351 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8925 4.4469 475.1750 476.3827 40.0201 48.7083 35.4000 -13.3083

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 260.8631 63.8151 252.9372 1069.0944 0.2440 0.5226 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8811 4.6858 482.3636 474.7490 554.9116 0.0358 0.6151

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 259.8201 0.0000 259.8201 1069.0931 0.2430 0.4889 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6648 482.4092 475.9192 0.0000 0.0600 0.0893 0.4750

NASA/TM—2013-218094 L–247
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8090 4.8574 1.1200 487.7967 18.3109 166.0929 1.2875

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 114636.203 0.627 165.321 262391.438 0.306532E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.298 EfDer = 0.956 SH = 0.443208E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.520 2375.659 4.857 487.795 1.000 1.000 0.980

 W Kg/sec = 11.600 Wdry = 25.406 WH2O = 0.113 lbm/sec H2O = 1.861g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.894 2449.756 1.376 0.252 53.492 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58542.746 19988.910 2.686 590.487 219.800 468.502 2.131

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 237.92 -0.08 237.92 0.22 0.46 439.31

 MEAN 18.08 0.00 -0.02 237.92 -0.08 237.92 0.22 0.42

 HUB 15.21 0.00 -0.02 237.92 -0.08 237.92 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.82 46.36 14.46 426.03 488.04 4.70 483.30 479.13 53.34

 MEAN 57.60 42.30 15.30 374.79 444.00 4.70 483.30 479.13 53.34

 HUB 52.97 37.84 15.13 315.33 395.08 4.70 483.30 479.13 53.34

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 352.19 246.87 251.19 1082.17 0.33 2.33 2.04 9.02

 MEAN 18.01 351.42 243.28 253.60 1079.84 0.33 2.40 2.13 7.35

 HUB 15.22 371.95 269.57 256.28 1077.54 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 423.34 306.98 176.47 0.28 5042.67 0.92 0.87

 MEAN 373.37 285.02 130.09 0.26 4382.98 0.92 0.87 0.87 1.72

 HUB 315.60 260.38 46.03 0.24 4104.88 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.41 1.11 5.03 504.39 1.03 494.54 489.01 38.07

 MEAN 5.33 1.10 4.96 502.22 1.03 492.42 488.10 40.89

 HUB 5.30 1.09 4.89 501.30 1.03 490.32 488.18 43.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.50 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.81 27.16 23.50 3.66 0.95 0.53 1.63

 HUB 46.45 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.4347 243.9647 285.3637 1078.7216 0.3480 -0.1054 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3439 4.9213 491.4593 488.8979 42.5512 40.5280 30.6000 -9.9280

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 276.4072 58.6003 270.1239 1084.3147 0.2549 0.3750 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3379 5.1060 496.5783 487.1746 491.5697 0.0254 0.4700

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 286.4677 0.0000 286.4677 1083.8021 0.2643 0.3599 0.5911

NASA/TM—2013-218094 L–248
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0734 496.1308 487.8156 0.0000 0.0600 0.0680 0.2908

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8282 5.3214 1.0955 502.6360 14.8423 187.3397 1.4522

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93590.617 0.522 134.970 238836.969 0.503357E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.202 EfDer = 0.972 SH = 0.587133E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.520 2375.659 5.321 502.635 1.000 1.000 0.980

 W Kg/sec = 11.600 Wdry = 25.370 WH2O = 0.150 lbm/sec H2O = 2.618g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.396 2413.323 1.374 0.253 53.539 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 55124.016 19977.434 2.676 545.479 203.855 424.468 2.082

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 242.52 -0.08 242.52 0.22 0.44 422.67

 MEAN 17.74 0.00 -0.02 242.52 -0.08 242.52 0.22 0.41

 HUB 15.05 0.00 -0.02 242.52 -0.08 242.52 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.77 46.36 13.41 416.08 481.67 5.14 497.99 488.90 42.65

 MEAN 56.60 43.40 13.20 367.75 440.58 5.14 497.99 488.90 42.65

 HUB 52.15 38.84 13.31 312.01 395.24 5.14 497.99 488.90 42.65

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 344.39 230.50 255.89 1096.76 0.31 2.26 1.98 8.75

 MEAN 17.51 345.74 230.14 258.02 1094.78 0.32 2.34 2.07 6.78

 HUB 14.85 368.41 260.62 260.39 1092.83 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.69 312.96 180.19 0.29 4567.88 0.92 0.89

 MEAN 362.94 290.19 132.80 0.27 4030.40 0.92 0.89 0.89 1.67

 HUB 307.86 264.64 47.24 0.24 3871.50 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.86 1.10 5.48 517.60 1.03 508.23 497.33 32.52

 MEAN 5.79 1.09 5.41 515.84 1.03 506.39 496.70 34.43

 HUB 5.77 1.08 5.34 515.32 1.03 504.59 497.01 36.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 42.01 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.73 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 45.03 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.972 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.0850 231.6479 289.9022 1093.6240 0.3393 -0.1140 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8041 5.3673 505.3834 497.5328 35.8434 38.6268 31.5000 -7.1268

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 285.5481 62.2904 278.6711 1098.3992 0.2600 0.3213 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8003 5.5388 509.8169 496.0248 451.3937 0.0194 0.4421

 

NASA/TM—2013-218094 L–249
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 290.3684 0.0000 290.3684 1098.1445 0.2644 0.3434 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5173 509.5996 496.6305 0.0000 0.0600 0.0535 0.2669

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8504 5.7868 1.0875 516.2507 13.6169 193.2331 1.4979

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86274.617 0.512 124.420 237908.875 0.668832E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.513 EfDer = 0.983 SH = 0.766326E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.520 2375.659 5.787 516.245 1.000 1.000 0.980

 W Kg/sec = 11.600 Wdry = 25.324 WH2O = 0.196 lbm/sec H2O = 3.616g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.673 2381.288 1.372 0.254 53.597 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52097.145 19963.072 2.699 513.330 190.191 395.845 2.081 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 243.56 -0.08 243.56 0.22 0.43 400.22

 MEAN 16.97 0.00 -0.02 243.56 -0.08 243.56 0.22 0.39

 HUB 14.32 0.00 -0.02 243.56 -0.08 243.56 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.62 46.36 12.26 399.29 467.78 5.60 511.58 497.61 36.11

 MEAN 55.31 43.80 11.51 351.83 427.97 5.60 511.58 497.61 36.11

 HUB 50.64 37.84 12.80 296.88 384.06 5.60 511.58 497.61 36.11

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.70 210.77 256.13 1109.69 0.30 2.16 1.89 8.34

 MEAN 16.57 333.13 210.66 258.07 1107.91 0.30 2.24 1.97 6.35

 HUB 13.89 354.55 240.86 260.18 1106.17 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 391.41 313.43 180.64 0.28 3980.92 0.92 0.90

 MEAN 343.60 290.30 132.94 0.26 3492.95 0.92 0.90 0.90 1.62

 HUB 287.96 264.41 47.10 0.24 3346.73 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.28 1.09 5.91 529.20 1.03 520.56 504.27 28.42

 MEAN 6.22 1.08 5.85 527.61 1.02 518.89 503.74 29.84

 HUB 6.20 1.07 5.78 527.14 1.02 517.26 504.03 31.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.45 35.19 31.50 3.69 0.93 0.49 1.40

 MEAN 39.23 27.25 23.50 3.75 0.94 0.47 1.62

 HUB 42.79 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.983 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 353.4651 211.8489 282.9446 1107.0929 0.3193 -0.0908 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2320 5.8151 518.1616 504.3580 30.6130 36.8233 32.4000 -4.4233

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 284.3749 63.7770 277.1310 1110.7599 0.2560 0.2782 2.2705

 

NASA/TM—2013-218094 L–250
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2302 5.9568 521.6072 503.0938 432.2457 0.0148 0.4182

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 282.0337 0.0000 282.0337 1110.8069 0.2539 0.3280 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9518 521.6604 503.1872 0.0000 0.0600 0.0433 0.2652

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8722 6.2192 1.0747 527.9051 11.7388 209.1775 1.6215

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74751.391 0.488 107.802 244014.828 0.809461E-02

 

Melt Ratio at Stator LE, Throat, TE

0.34229E+00 0.41891E+00 0.64188E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.984 EfDer = 0.992 SH = 0.842143E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.520 2375.659 6.219 527.882 1.000 1.000 0.980

 W Kg/sec = 11.600 Wdry = 25.305 WH2O = 0.215 lbm/sec H2O = 4.185g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.853 2354.856 1.371 0.255 53.621 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49462.949 19956.975 2.847 509.668 179.044 384.739 2.149

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 232.91 -0.08 232.91 0.21 0.40 376.46

 MEAN 15.91 0.00 -0.02 232.91 -0.08 232.91 0.21 0.36

 HUB 13.07 0.00 -0.02 232.91 -0.08 232.91 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.49 47.36 11.13 379.80 445.60 6.04 523.63 502.97 27.76

 MEAN 54.78 44.80 9.98 329.90 403.90 6.04 523.63 502.97 27.76

 HUB 49.33 38.84 10.49 270.96 357.37 6.04 523.63 502.97 27.76

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 315.14 197.66 245.44 1121.27 0.28 2.05 1.78 7.43

 MEAN 15.50 313.84 193.18 247.33 1119.44 0.28 2.13 1.86 5.75

 HUB 12.59 329.78 215.82 249.35 1117.64 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.92 301.02 174.27 0.27 3547.46 0.92 0.91

 MEAN 321.29 278.54 128.11 0.25 2995.15 0.92 0.91 0.91 1.60

 HUB 261.01 253.41 45.19 0.23 2718.26 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.69 1.08 6.34 539.39 1.02 531.60 508.50 22.53

 MEAN 6.61 1.06 6.27 537.59 1.02 529.87 507.87 23.63

 HUB 6.57 1.06 6.20 536.69 1.02 528.16 507.85 24.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.84 35.37 31.50 3.87 0.93 0.48 1.40

 MEAN 37.99 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.88 10.27 6.50 3.77 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 343.3263 196.7251 281.3755 1118.1299 0.3071 -0.1705 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6168 6.2062 528.6502 508.6719 24.7113 34.9595 33.0000 -1.9595

 

NASA/TM—2013-218094 L–251
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 287.6975 65.6960 280.0962 1121.0199 0.2566 0.1628 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6150 6.3247 531.4024 507.8784 410.5396 0.0250 0.3920

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 279.9157 0.0000 279.9157 1121.3625 0.2496 0.3152 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3356 531.7501 508.3893 0.0000 0.0600 0.0379 0.1933

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8763 6.6104 1.0629 537.8859 10.0071 229.3938 1.7782

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63853.898 0.462 92.086 256341.719 0.925743E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1457 Tt4 = 537.8859 T1 = 469.4884

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 433106.72 624.5987 82.2912 1.5241 0.8332 15.8281 1.1457 37.3740

NASA/TM—2013-218094 L–252
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.872 EfDer = 0.951 SH = 0.171826E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.380 2299.789 4.829 471.199 1.000 1.000 0.980

 W Kg/sec = 12.446 Wdry = 27.333 WH2O = 0.047 lbm/sec H2O = 0.752g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.449 2412.891 1.379 0.250 53.404 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60268.254 21469.504 3.572 831.557 232.792 619.754 2.662

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.94 -0.06 173.94 0.17 0.43 434.38

 MEAN 17.06 0.00 -0.02 173.94 -0.06 173.94 0.17 0.36

 HUB 12.51 0.00 -0.02 173.94 -0.06 173.94 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.21 50.47 16.74 414.03 449.14 4.74 468.78 463.29 39.22

 MEAN 63.07 47.20 15.87 342.39 384.09 4.74 468.78 463.29 39.22

 HUB 55.29 38.62 16.67 251.07 305.49 4.74 468.78 463.29 39.22

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 370.50 287.16 234.11 1065.77 0.35 7.29 6.52 16.04

 MEAN 18.04 374.20 289.73 236.82 1063.02 0.35 7.43 6.80 12.53

 HUB 15.00 404.02 324.61 240.54 1059.67 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 414.03 266.28 126.88 0.25 5925.27 0.92 0.87

 MEAN 361.97 247.59 72.24 0.23 5226.58 0.92 0.87 0.87 1.78

 HUB 301.04 241.69 23.57 0.23 4869.88 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 490.23 1.04 479.25 477.91 35.81

 MEAN 5.40 1.12 4.96 487.99 1.04 476.78 476.84 39.16

 HUB 5.36 1.11 4.85 486.84 1.03 473.78 476.82 43.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.81 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.74 16.96 12.70 4.26 0.95 0.53 2.22

 HUB 53.46 -5.60 -9.30 3.70 0.95 0.40 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.951 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 384.8633 289.1661 253.9738 1062.6180 0.3622 -0.0354 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.4039 4.9422 476.5232 477.4634 40.7835 48.7072 35.4000 -13.3072

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 253.1650 61.9319 245.4730 1070.0499 0.2366 0.5220 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3926 5.1895 483.2351 475.9814 554.9116 0.0346 0.6136

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 252.1013 0.0000 252.1013 1070.0532 0.2356 0.4873 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1672 483.2799 477.0560 0.0000 0.0600 0.0893 0.4733

NASA/TM—2013-218094 L–253
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8087 5.3676 1.1116 488.3528 17.1558 165.9748 1.2866

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 107396.727 0.627 166.174 280462.750 0.294069E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.233 EfDer = 0.956 SH = 0.418414E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.380 2299.789 5.368 488.351 1.000 1.000 0.980

 W Kg/sec = 12.446 Wdry = 27.266 WH2O = 0.115 lbm/sec H2O = 1.942g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.759 2370.169 1.376 0.251 53.484 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56814.473 21448.547 2.766 590.487 213.506 468.502 2.194

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 230.90 -0.08 230.90 0.22 0.44 425.04

 MEAN 18.08 0.00 -0.02 230.90 -0.08 230.90 0.22 0.40

 HUB 15.21 0.00 -0.02 230.90 -0.08 230.90 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.76 46.36 14.40 412.43 472.73 5.20 484.12 480.06 53.89

 MEAN 57.53 42.30 15.23 362.82 430.13 5.20 484.12 480.06 53.89

 HUB 52.90 37.84 15.06 305.26 382.81 5.20 484.12 480.06 53.89

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 341.29 238.07 244.55 1082.25 0.32 2.33 2.04 9.02

 MEAN 18.01 340.70 234.95 246.72 1080.09 0.32 2.40 2.13 7.35

 HUB 15.22 360.66 260.77 249.15 1077.95 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.82 298.83 171.74 0.28 4863.10 0.92 0.88

 MEAN 361.45 277.26 126.50 0.26 4232.87 0.92 0.88 0.88 1.71

 HUB 305.52 253.14 44.74 0.23 3970.98 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.93 1.11 5.54 503.85 1.03 494.60 489.49 39.43

 MEAN 5.86 1.09 5.47 501.84 1.03 492.63 488.61 42.13

 HUB 5.83 1.09 5.40 501.01 1.03 490.68 488.67 44.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.23 35.08 31.50 3.58 0.93 0.55 1.40

 MEAN 43.60 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.31 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.0515 235.6091 277.5281 1079.0338 0.3374 -0.1063 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8687 5.4312 491.7180 489.3561 43.7521 40.3298 30.6000 -9.7298

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 269.3013 57.0938 263.1796 1084.2378 0.2484 0.3705 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8631 5.6208 496.4804 487.8008 491.5697 0.0242 0.4657

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 279.0125 0.0000 279.0125 1083.7555 0.2574 0.3561 0.5911

NASA/TM—2013-218094 L–254
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5870 496.0591 488.3895 0.0000 0.0600 0.0669 0.2861

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8292 5.8460 1.0891 502.2350 13.8850 187.9253 1.4568

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87489.641 0.521 135.372 255620.688 0.472192E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.029 EfDer = 0.973 SH = 0.546689E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.380 2299.789 5.846 502.234 1.000 1.000 0.980

 W Kg/sec = 12.446 Wdry = 27.231 WH2O = 0.150 lbm/sec H2O = 2.684g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.748 2337.183 1.374 0.253 53.526 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53713.801 21437.584 2.742 545.479 198.969 424.468 2.133

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 236.32 -0.08 236.32 0.22 0.43 409.33

 MEAN 17.74 0.00 -0.02 236.32 -0.08 236.32 0.22 0.39

 HUB 15.05 0.00 -0.02 236.32 -0.08 236.32 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.61 46.36 13.25 402.79 467.07 5.66 497.82 489.40 44.00

 MEAN 56.43 43.40 13.03 356.00 427.36 5.66 497.82 489.40 44.00

 HUB 51.97 38.84 13.13 302.05 383.57 5.66 497.82 489.40 44.00

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 334.10 221.57 250.06 1095.86 0.30 2.26 1.98 8.75

 MEAN 17.51 335.64 221.71 252.00 1094.03 0.31 2.34 2.07 6.78

 HUB 14.85 357.87 251.96 254.14 1092.23 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 397.58 305.79 176.00 0.28 4391.01 0.92 0.89

 MEAN 351.35 283.39 129.64 0.26 3882.76 0.92 0.89 0.89 1.65

 HUB 298.03 258.28 46.08 0.24 3742.76 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.39 1.09 6.00 516.18 1.03 507.35 497.45 34.19

 MEAN 6.33 1.08 5.94 514.56 1.02 505.65 496.84 36.05

 HUB 6.31 1.08 5.87 514.12 1.02 503.99 497.14 37.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.54 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 41.34 27.22 23.50 3.72 0.94 0.50 1.62

 HUB 44.75 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 360.4337 223.1613 283.0396 1092.9237 0.3298 -0.1154 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3406 5.8885 504.6850 497.6261 37.4733 38.2539 31.5000 -6.7539

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 279.2386 60.9140 272.5136 1097.3494 0.2545 0.3131 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3372 6.0631 508.7897 496.2660 451.3937 0.0183 0.4351

 

NASA/TM—2013-218094 L–255
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 283.8871 0.0000 283.8871 1097.1088 0.2588 0.3372 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0410 508.5841 496.8200 0.0000 0.0600 0.0518 0.2591

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8525 6.3235 1.0817 514.9501 12.7174 194.5500 1.5081

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 80473.719 0.509 124.516 255029.781 0.618347E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.23279E-02

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.239 EfDer = 0.985 SH = 0.700976E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.380 2299.789 6.323 514.944 1.000 1.000 0.980

 W Kg/sec = 12.446 Wdry = 27.188 WH2O = 0.192 lbm/sec H2O = 3.628g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.420 2308.148 1.373 0.254 53.576 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50951.453 21424.338 2.753 513.330 186.434 395.845 2.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 238.20 -0.08 238.20 0.22 0.41 387.93

 MEAN 16.97 0.00 -0.02 238.20 -0.08 238.20 0.22 0.38

 HUB 14.32 0.00 -0.02 238.20 -0.08 238.20 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.36 46.36 12.00 386.54 454.11 6.12 510.48 497.67 37.65

 MEAN 55.04 43.80 11.24 340.59 415.69 6.12 510.48 497.67 37.65

 HUB 50.35 37.84 12.51 287.39 373.34 6.12 510.48 497.67 37.65

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 322.21 201.85 251.15 1107.91 0.29 2.16 1.89 8.34

 MEAN 16.57 323.90 202.38 252.90 1106.27 0.29 2.24 1.97 6.35

 HUB 13.89 345.06 232.67 254.81 1104.67 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.91 307.29 177.06 0.28 3812.53 0.92 0.90

 MEAN 332.63 284.47 130.25 0.26 3355.57 0.92 0.90 0.90 1.60

 HUB 278.76 258.95 46.09 0.23 3233.02 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.83 1.08 6.45 526.98 1.02 518.80 504.02 30.12

 MEAN 6.77 1.07 6.38 525.54 1.02 517.27 503.53 31.50

 HUB 6.75 1.07 6.32 525.15 1.02 515.77 503.81 32.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.79 35.18 31.50 3.68 0.93 0.48 1.40

 MEAN 38.67 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.40 10.25 6.50 3.75 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 343.9055 203.5155 277.2228 1105.4825 0.3111 -0.0923 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7773 6.3457 516.5704 504.1119 32.2990 36.2832 32.4000 -3.8832

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 279.0013 62.5718 271.8943 1108.8589 0.2516 0.2666 2.2705

 

NASA/TM—2013-218094 L–256
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7758 6.4882 519.7369 502.9783 432.2457 0.0139 0.4089

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 276.6748 0.0000 276.6748 1108.9053 0.2495 0.3191 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4834 519.7897 503.0663 0.0000 0.0600 0.0417 0.2546

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8746 6.7646 1.0698 525.8114 10.9431 211.3962 1.6387

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 69547.148 0.484 107.610 261932.859 0.738663E-02

 

Melt Ratio at Stator LE, Throat, TE

0.34318E+00 0.41727E+00 0.63167E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.616 EfDer = 0.993 SH = 0.768194E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.380 2299.789 6.765 525.789 1.000 1.000 0.980

 W Kg/sec = 12.446 Wdry = 27.170 WH2O = 0.210 lbm/sec H2O = 4.174g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 59.906 2284.185 1.372 0.254 53.597 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48539.617 21418.551 2.893 509.668 176.181 384.739 2.184

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 228.57 -0.08 228.57 0.21 0.39 365.17

 MEAN 15.91 0.00 -0.02 228.57 -0.08 228.57 0.21 0.35

 HUB 13.07 0.00 -0.02 228.57 -0.08 228.57 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.14 47.36 10.78 367.67 432.99 6.57 521.68 502.87 29.52

 MEAN 54.42 44.80 9.62 319.37 392.79 6.57 521.68 502.87 29.52

 HUB 48.94 38.84 10.10 262.31 347.98 6.57 521.68 502.87 29.52

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 306.40 188.66 241.42 1118.69 0.27 2.05 1.78 7.43

 MEAN 15.50 305.59 185.12 243.14 1117.01 0.27 2.13 1.86 5.75

 HUB 12.59 321.53 208.26 244.97 1115.35 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 360.05 296.07 171.38 0.26 3386.09 0.92 0.91

 MEAN 311.03 273.81 125.91 0.25 2870.16 0.92 0.91 0.91 1.59

 HUB 252.67 248.96 44.42 0.22 2623.00 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.24 1.07 6.88 536.44 1.02 529.06 508.11 24.22

 MEAN 7.16 1.06 6.81 534.81 1.02 527.47 507.52 25.32

 HUB 7.13 1.05 6.74 534.03 1.02 525.91 507.52 26.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.01 35.37 31.50 3.87 0.93 0.47 1.40

 MEAN 37.28 27.38 23.50 3.88 0.94 0.45 1.64

 HUB 40.37 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 334.6695 188.5137 276.5254 1115.7406 0.3000 -0.1734 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1676 6.7422 526.2949 508.2693 26.4295 34.2831 33.0000 -1.2831

 

NASA/TM—2013-218094 L–257
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 283.0660 64.6384 275.5871 1118.3788 0.2531 0.1469 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1662 6.8598 528.7995 507.5655 410.5396 0.0239 0.3808

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 275.4133 0.0000 275.4133 1118.7131 0.2462 0.3037 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8714 529.1363 508.0278 0.0000 0.0600 0.0372 0.1781

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8781 7.1613 1.0586 535.0904 9.3054 232.7060 1.8039

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59242.875 0.457 91.666 275521.469 0.837301E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1356 Tt4 = 535.0904 T1 = 471.1995

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 404150.13 625.3379 79.4486 1.4831 0.8351 15.8721 1.1356 37.3740

NASA/TM—2013-218094 L–258
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.434 EfDer = 0.963 SH = 0.218578E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.230 2174.106 5.592 480.729 1.000 1.000 0.980

 W Kg/sec = 14.195 Wdry = 31.161 WH2O = 0.068 lbm/sec H2O = 1.086g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.030 2258.313 1.379 0.250 53.419 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60562.797 24483.221 3.590 831.557 231.641 619.754 2.675

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.79 -0.06 174.79 0.16 0.40 406.55

 MEAN 17.06 0.00 -0.02 174.79 -0.06 174.79 0.16 0.35

 HUB 12.51 0.00 -0.02 174.79 -0.06 174.79 0.16 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.94 50.47 15.47 391.41 428.72 5.49 478.29 471.24 38.05

 MEAN 61.63 47.20 14.43 323.68 367.91 5.49 478.29 471.24 38.05

 HUB 53.64 38.62 15.02 237.35 294.81 5.49 478.29 471.24 38.05

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 354.27 263.72 236.55 1074.44 0.33 7.29 6.52 16.04

 MEAN 18.04 360.30 269.72 238.90 1072.13 0.34 7.43 6.80 12.53

 HUB 15.00 392.36 308.68 242.22 1069.21 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 391.41 268.81 127.68 0.25 5441.87 0.92 0.88

 MEAN 342.19 249.65 72.48 0.23 4865.63 0.92 0.88 0.88 1.69

 HUB 284.59 243.41 24.09 0.23 4630.89 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.79 497.23 1.03 487.20 483.94 36.22

 MEAN 6.16 1.10 5.71 495.48 1.03 485.11 483.20 38.94

 HUB 6.13 1.10 5.60 494.77 1.03 482.47 483.47 42.66

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 48.11 28.36 24.20 4.16 0.93 0.54 1.80

 MEAN 48.47 16.88 12.70 4.18 0.95 0.49 2.22

 HUB 51.88 -5.68 -9.30 3.62 0.95 0.36 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.963 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 371.6423 269.1918 256.2299 1071.6855 0.3468 -0.0404 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1718 5.6864 484.8129 483.8335 40.5222 46.4132 35.4000 -11.0132

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.6891 62.7940 248.8900 1078.0087 0.2381 0.4829 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1633 5.9284 490.5721 482.4895 554.9116 0.0277 0.5719

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.3411 0.0000 255.3411 1078.0337 0.2369 0.4592 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9093 490.6289 483.5214 0.0000 0.0600 0.0745 0.4430

NASA/TM—2013-218094 L–259
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8264 6.1409 1.0981 495.8234 15.0965 172.8784 1.3401

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 94680.711 0.618 167.094 315130.844 0.350875E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.418 EfDer = 0.971 SH = 0.482358E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.230 2174.106 6.141 495.822 1.000 1.000 0.980

 W Kg/sec = 14.195 Wdry = 31.079 WH2O = 0.151 lbm/sec H2O = 2.521g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.090 2223.696 1.375 0.252 53.505 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57544.738 24457.607 2.752 590.487 214.567 468.502 2.183

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.87 -0.08 233.87 0.22 0.42 398.77

 MEAN 18.08 0.00 -0.02 233.87 -0.08 233.87 0.22 0.38

 HUB 15.21 0.00 -0.02 233.87 -0.08 233.87 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.05 46.36 12.69 389.89 454.72 5.95 491.49 486.47 52.48

 MEAN 55.72 42.30 13.42 342.99 415.20 5.95 491.49 486.47 52.48

 HUB 50.99 37.84 13.15 288.57 371.50 5.95 491.49 486.47 52.48

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 327.66 212.88 249.08 1088.42 0.30 2.33 2.04 9.02

 MEAN 18.01 329.35 213.32 250.92 1086.67 0.30 2.40 2.13 7.35

 HUB 15.22 351.22 243.64 252.97 1084.95 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 387.42 304.15 174.54 0.28 4348.68 0.92 0.89

 MEAN 341.70 281.85 128.37 0.26 3843.40 0.92 0.89 0.89 1.62

 HUB 288.82 256.98 45.18 0.24 3710.15 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.68 1.09 6.28 508.90 1.03 500.39 494.37 40.85

 MEAN 6.62 1.08 6.22 507.38 1.02 498.78 493.76 43.03

 HUB 6.60 1.08 6.15 506.98 1.02 497.20 494.05 45.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.52 35.02 31.50 3.52 0.93 0.50 1.40

 MEAN 40.37 27.09 23.50 3.59 0.94 0.48 1.63

 HUB 43.92 10.13 6.50 3.63 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.971 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 354.1971 213.9222 282.2993 1085.5724 0.3263 -0.1192 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6316 6.1680 497.8172 494.5274 44.7103 37.1543 30.6000 -6.5543

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 275.0645 58.3156 268.8118 1089.8561 0.2524 0.3084 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6283 6.3459 501.7609 493.1890 491.5697 0.0178 0.4127

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.7551 0.0000 284.7551 1089.3735 0.2614 0.3124 0.5911

NASA/TM—2013-218094 L–260
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3128 501.3326 493.7620 0.0000 0.0600 0.0509 0.2294

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8498 6.6144 1.0771 507.7519 11.9310 200.0176 1.5505

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75335.297 0.502 132.953 288427.938 0.536700E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.989 EfDer = 0.986 SH = 0.609419E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.230 2174.106 6.614 507.751 1.000 1.000 0.980

 W Kg/sec = 14.195 Wdry = 31.039 WH2O = 0.190 lbm/sec H2O = 3.345g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.669 2197.420 1.374 0.253 53.546 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54801.793 24445.197 2.704 545.479 201.755 424.468 2.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 241.10 -0.08 241.10 0.22 0.41 384.85

 MEAN 17.74 0.00 -0.02 241.10 -0.08 241.10 0.22 0.38

 HUB 15.05 0.00 -0.02 241.10 -0.08 241.10 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.66 46.36 11.30 380.78 450.76 6.40 503.16 494.61 45.06

 MEAN 54.39 43.40 10.99 336.55 414.07 6.40 503.16 494.61 45.06

 HUB 49.83 38.84 10.99 285.54 373.78 6.40 503.16 494.61 45.06

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.51 195.39 256.59 1099.82 0.29 2.26 1.98 8.75

 MEAN 17.51 326.23 199.43 258.18 1098.39 0.30 2.34 2.07 6.78

 HUB 14.85 350.24 234.73 259.95 1097.00 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 375.85 313.69 180.46 0.29 3872.38 0.92 0.90

 MEAN 332.15 290.30 132.72 0.26 3492.74 0.92 0.90 0.90 1.56

 HUB 281.74 264.16 47.01 0.24 3487.00 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.13 1.08 6.72 519.35 1.02 511.14 501.26 36.57

 MEAN 7.08 1.07 6.67 518.21 1.02 509.81 500.89 38.08

 HUB 7.08 1.07 6.60 518.19 1.02 508.51 501.39 39.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.29 35.12 31.50 3.62 0.93 0.46 1.40

 MEAN 37.68 27.21 23.50 3.71 0.94 0.45 1.62

 HUB 42.08 10.25 6.50 3.75 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 352.7383 200.7348 290.0514 1097.2224 0.3215 -0.1295 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0906 6.6093 508.7643 501.6800 39.5585 34.6858 31.5000 -3.1858

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 287.3254 62.6781 280.4057 1100.7633 0.2610 0.2376 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0889 6.7663 512.0605 500.4946 451.3937 0.0138 0.3772

 

NASA/TM—2013-218094 L–261
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.8998 0.0000 291.8998 1100.4989 0.2652 0.2840 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7460 511.8259 500.7963 0.0000 0.0600 0.0401 0.1903

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 7.0776 1.0700 518.5450 10.8331 209.2292 1.6219

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68674.586 0.486 121.198 288826.250 0.658625E-02

 

Melt Ratio at Stator LE, Throat, TE

0.93559E-01 0.13859E+00 0.28793E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.971 EfDer = 0.996 SH = 0.699680E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.230 2174.106 7.078 518.531 1.000 1.000 0.980

 W Kg/sec = 14.195 Wdry = 31.011 WH2O = 0.219 lbm/sec H2O = 4.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.853 2174.431 1.373 0.254 53.575 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52342.805 24436.350 2.692 513.330 190.653 395.845 2.076

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.71 -0.08 244.71 0.22 0.40 365.46

 MEAN 16.97 0.00 -0.02 244.71 -0.08 244.71 0.22 0.37

 HUB 14.32 0.00 -0.02 244.71 -0.08 244.71 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 56.20 46.36 9.84 365.41 439.86 6.84 513.82 500.81 37.14

 MEAN 52.77 43.80 8.97 321.98 404.49 6.84 513.82 500.81 37.14

 HUB 48.00 37.84 10.16 271.69 365.71 6.84 513.82 500.81 37.14

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 313.09 175.23 259.46 1109.89 0.28 2.16 1.89 8.34

 MEAN 16.57 316.98 180.06 260.87 1108.65 0.29 2.24 1.97 6.35

 HUB 13.89 339.87 215.99 262.41 1107.44 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 358.20 317.49 182.97 0.29 3310.00 0.92 0.91

 MEAN 314.45 293.45 134.39 0.26 2985.74 0.92 0.91 0.91 1.50

 HUB 263.53 266.68 47.54 0.24 3001.34 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.54 1.07 7.14 528.40 1.02 520.68 505.93 30.70

 MEAN 7.49 1.06 7.09 527.43 1.02 519.52 505.64 31.75

 HUB 7.50 1.06 7.03 527.48 1.02 518.38 506.10 32.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 34.03 35.19 31.50 3.69 0.93 0.42 1.40

 MEAN 34.62 27.26 23.50 3.76 0.93 0.41 1.62

 HUB 39.46 10.27 6.50 3.77 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 338.5242 181.0734 286.0263 1107.7930 0.3056 -0.1045 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.5058 7.0438 518.7318 506.2014 32.5389 32.3365 32.4000 0.0635

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.9481 64.8026 281.5876 1110.3810 0.2602 0.1832 2.2705

 

NASA/TM—2013-218094 L–262
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.5050 7.1645 521.1609 505.3148 432.2457 0.0120 0.3468

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.4213 0.0000 286.4213 1110.4341 0.2579 0.2561 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1621 521.2163 505.3105 0.0000 0.0600 0.0366 0.1775

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8878 7.4946 1.0589 527.6722 9.2358 230.0817 1.7836

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58681.129 0.457 103.561 297545.250 0.717359E-02

 

Melt Ratio at Stator LE, Throat, TE

0.71845E+00 0.79094E+00 0.99381E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 7.135 EfDer = 1.000 SH = 0.782596E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.230 2174.106 7.495 527.660 1.000 1.000 0.980

 W Kg/sec = 14.195 Wdry = 30.985 WH2O = 0.244 lbm/sec H2O = 4.687g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.782 2155.543 1.372 0.254 53.602 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50224.594 24428.203 2.805 509.668 181.713 384.739 2.117

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.49 -0.08 236.49 0.21 0.38 344.60

 MEAN 15.91 0.00 -0.02 236.49 -0.08 236.49 0.21 0.34

 HUB 13.07 0.00 -0.02 236.49 -0.08 236.49 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.77 47.36 8.41 347.58 420.47 7.27 523.27 505.68 31.45

 MEAN 51.94 44.80 7.14 301.91 383.57 7.27 523.27 505.68 31.45

 HUB 46.37 38.84 7.53 247.97 342.72 7.27 523.27 505.68 31.45

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 298.79 161.89 251.13 1118.91 0.27 2.05 1.78 7.43

 MEAN 15.50 300.58 163.04 252.51 1117.63 0.27 2.13 1.86 5.75

 HUB 12.59 318.80 192.66 254.01 1116.37 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 340.37 308.09 178.47 0.28 2905.88 0.92 0.91

 MEAN 294.03 284.47 130.99 0.25 2528.06 0.92 0.91 0.91 1.48

 HUB 238.87 258.18 46.21 0.23 2426.60 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.92 1.06 7.54 536.32 1.02 529.31 510.60 28.01

 MEAN 7.86 1.05 7.48 535.19 1.01 528.10 510.22 28.97

 HUB 7.85 1.05 7.42 534.89 1.01 526.91 510.45 29.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.81 35.40 31.50 3.90 0.93 0.40 1.40

 MEAN 32.85 27.42 23.50 3.92 0.93 0.39 1.64

 HUB 37.18 10.31 6.50 3.81 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 331.9006 166.0318 287.3873 1116.2163 0.2973 -0.1917 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8681 7.4090 526.8274 511.0396 30.2939 30.0162 33.0000 2.9838

 

NASA/TM—2013-218094 L–263
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.2492 67.4204 287.4484 1118.1117 0.2641 0.0450 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8660 7.5012 528.6315 510.5194 410.5396 0.0253 0.3155

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.2335 0.0000 287.2335 1118.4827 0.2568 0.2310 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5150 528.9988 510.8878 0.0000 0.0600 0.0397 0.0803

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8762 7.8604 1.0488 535.4654 7.8068 254.9794 1.9766

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 49777.727 0.430 87.848 313895.125 0.879951E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.1139 Tt4 = 535.4654 T1 = 480.7291

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 347149.44 612.6539 79.0296 1.4056 0.8518 14.4343 1.1139 37.3740

NASA/TM—2013-218094 L–264
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.619 EfDer = 0.993 SH = 0.269088E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.278 1987.623 6.513 491.407 1.000 1.000 0.980

 W Kg/sec = 17.854 Wdry = 39.172 WH2O = 0.106 lbm/sec H2O = 1.518g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.291 2042.061 1.378 0.250 53.436 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67058.445 30786.734 3.287 831.557 253.010 619.754 2.450

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 193.54 -0.07 193.54 0.18 0.38 367.62

 MEAN 17.06 0.00 -0.02 193.54 -0.07 193.54 0.18 0.33

 HUB 12.51 0.00 -0.02 193.54 -0.07 193.54 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.60 50.47 11.13 357.83 406.88 6.37 488.42 479.69 35.53

 MEAN 56.82 47.20 9.62 295.91 353.64 6.37 488.42 479.69 35.53

 HUB 48.28 38.62 9.66 216.99 290.81 6.37 488.42 479.69 35.53

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 341.33 215.64 264.59 1082.25 0.32 7.29 6.52 16.04

 MEAN 18.04 353.62 232.50 266.45 1080.73 0.33 7.43 6.80 12.53

 HUB 15.00 393.92 287.31 269.50 1078.45 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 357.83 300.38 142.20 0.28 4449.97 0.92 0.91

 MEAN 312.84 278.30 80.34 0.26 4194.45 0.92 0.91 0.91 1.44

 HUB 260.18 270.86 27.13 0.25 4310.42 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.61 503.72 1.03 494.43 489.64 36.78

 MEAN 7.04 1.08 6.54 503.01 1.02 493.04 489.52 38.51

 HUB 7.05 1.08 6.44 503.33 1.02 490.96 490.47 41.23

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.18 28.25 24.20 4.05 0.93 0.41 1.80

 MEAN 41.11 16.78 12.70 4.08 0.94 0.37 2.22

 HUB 46.83 -5.75 -9.30 3.55 0.94 0.25 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.3257 232.0449 286.0401 1080.0819 0.3410 -0.0580 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0477 6.5111 492.5578 490.2345 40.2543 39.0501 35.4000 -3.6501

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 288.8456 70.6604 280.0694 1084.6102 0.2663 0.3482 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0451 6.7115 496.7159 489.2433 554.9116 0.0150 0.4466

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 286.7787 0.0000 286.7787 1084.6866 0.2644 0.3580 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7032 496.8127 490.1497 0.0000 0.0600 0.0412 0.3324

NASA/TM—2013-218094 L–265
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8707 7.0314 1.0796 503.3531 11.9481 197.9215 1.5343

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75074.844 0.586 166.638 391011.625 0.403092E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.792 EfDer = 0.999 SH = 0.527807E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.278 1987.623 7.031 503.352 1.000 1.000 0.980

 W Kg/sec = 17.854 Wdry = 39.071 WH2O = 0.207 lbm/sec H2O = 3.093g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.892 2017.696 1.375 0.252 53.519 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 64549.129 30755.096 2.486 590.487 237.539 468.502 1.972

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.33 -0.09 262.33 0.24 0.41 361.83

 MEAN 18.08 0.00 -0.02 262.33 -0.09 262.33 0.24 0.38

 HUB 15.21 0.00 -0.02 262.33 -0.09 262.33 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.65 46.36 7.29 356.45 442.65 6.76 497.91 492.75 50.53

 MEAN 50.09 42.30 7.79 313.57 408.90 6.76 497.91 492.75 50.53

 HUB 45.17 37.84 7.33 263.82 372.11 6.76 497.91 492.75 50.53

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.77 156.19 282.47 1092.10 0.30 2.33 2.04 9.02

 MEAN 18.01 329.22 167.18 283.62 1091.20 0.30 2.40 2.13 7.35

 HUB 15.22 355.74 212.98 284.94 1090.33 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.19 344.95 198.01 0.32 3191.16 0.92 0.91

 MEAN 312.39 318.63 145.21 0.29 3012.48 0.92 0.91 0.91 1.39

 HUB 264.05 289.48 51.06 0.27 3243.63 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.45 1.06 7.02 512.11 1.02 503.87 498.14 43.41

 MEAN 7.43 1.06 6.98 511.62 1.02 503.04 498.06 44.55

 HUB 7.46 1.06 6.94 512.26 1.02 502.24 498.90 45.66

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.94 35.03 31.50 3.53 0.93 0.35 1.40

 MEAN 30.52 27.11 23.50 3.61 0.93 0.35 1.63

 HUB 36.78 10.16 6.50 3.66 0.93 0.37 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 360.9959 167.6460 319.7075 1089.6940 0.3313 -0.1605 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4402 6.9050 501.6906 499.0080 46.8047 27.6713 30.6000 2.9287

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 313.8390 66.5361 306.7048 1092.4187 0.2873 0.1128 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4384 7.0313 504.2078 498.1248 491.5697 0.0140 0.2664

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 324.9582 0.0000 324.9582 1091.7985 0.2976 0.1614 0.5911

NASA/TM—2013-218094 L–266
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9914 503.6474 498.6872 0.0000 0.0600 0.0395 0.0273

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 7.4265 1.0562 511.9957 8.6448 246.3412 1.9096

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 54663.969 0.436 121.334 360808.844 0.576167E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.14225E-02

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.895 EfDer = 0.997 SH = 0.627449E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.278 1987.623 7.426 511.992 1.000 1.000 0.980

 W Kg/sec = 17.854 Wdry = 39.031 WH2O = 0.246 lbm/sec H2O = 3.808g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.243 2000.594 1.373 0.253 53.552 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62338.039 30742.842 2.403 545.479 226.977 424.468 1.870

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 274.26 -0.09 274.26 0.25 0.41 350.38

 MEAN 17.74 0.00 -0.02 274.26 -0.09 274.26 0.25 0.38

 HUB 15.05 0.00 -0.02 274.26 -0.09 274.26 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.77 46.36 5.41 348.12 443.25 7.11 506.06 498.83 46.21

 MEAN 48.29 43.40 4.89 307.68 412.24 7.11 506.06 498.83 46.21

 HUB 43.60 38.84 4.76 261.05 378.70 7.11 506.06 498.83 46.21

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 325.01 135.06 295.61 1099.60 0.30 2.26 1.98 8.75

 MEAN 17.51 332.45 150.65 296.36 1099.08 0.30 2.34 2.07 6.78

 HUB 14.85 360.07 203.17 297.28 1098.57 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 343.61 361.77 208.55 0.33 2677.45 0.92 0.91

 MEAN 303.66 333.52 153.00 0.30 2639.12 0.92 0.91 0.91 1.33

 HUB 257.58 302.22 54.41 0.28 3018.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.79 1.05 7.34 519.31 1.01 510.98 503.06 40.54

 MEAN 7.78 1.05 7.31 519.20 1.01 510.48 503.17 41.14

 HUB 7.84 1.06 7.28 520.24 1.02 510.01 504.19 41.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 24.55 35.20 31.50 3.70 0.93 0.29 1.40

 MEAN 26.95 27.31 23.50 3.81 0.92 0.30 1.62

 HUB 34.35 10.37 6.50 3.87 0.92 0.34 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.5457 151.6434 333.7066 1097.4303 0.3340 -0.1730 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7978 7.2285 508.9817 504.1311 43.1793 24.4381 31.5000 7.0619

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 333.2354 72.6931 325.2100 1099.3984 0.3031 0.0162 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7933 7.3199 510.8115 503.4194 451.3937 0.0190 0.2243

 

NASA/TM—2013-218094 L–267
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 338.8701 0.0000 338.8701 1099.0408 0.3083 0.1070 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2894 510.4852 503.6435 0.0000 0.0600 0.0532 -0.0461

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8544 7.7766 1.0471 519.5396 7.5938 266.2502 2.0640

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 48152.688 0.408 106.881 363558.125 0.654037E-02

 

Melt Ratio at Stator LE, Throat, TE

0.26562E+00 0.31312E+00 0.45032E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 2.343 EfDer = 0.980 SH = 0.676168E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.278 1987.623 7.777 519.526 1.000 1.000 0.980

 W Kg/sec = 17.854 Wdry = 39.012 WH2O = 0.266 lbm/sec H2O = 4.227g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.307 1986.016 1.373 0.254 53.568 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 60518.188 30736.840 2.350 513.330 218.417 395.845 1.812

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 282.94 -0.10 282.94 0.26 0.40 333.79

 MEAN 16.97 0.00 -0.02 282.94 -0.10 282.94 0.26 0.37

 HUB 14.32 0.00 -0.02 282.94 -0.10 282.94 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.75 46.36 3.39 334.07 437.86 7.43 513.22 502.99 39.86

 MEAN 46.14 43.80 2.34 294.36 408.36 7.43 513.22 502.99 39.86

 HUB 41.29 37.84 3.45 248.38 376.56 7.43 513.22 502.99 39.86

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 324.10 111.82 304.20 1105.99 0.29 2.16 1.89 8.34

 MEAN 16.57 330.99 129.43 304.64 1105.71 0.30 2.24 1.97 6.35

 HUB 13.89 356.77 184.62 305.29 1105.44 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 327.48 372.89 215.66 0.34 2113.00 0.92 0.90

 MEAN 287.48 343.20 158.05 0.31 2146.80 0.92 0.90 0.90 1.28

 HUB 240.93 310.44 56.30 0.28 2565.82 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.06 1.04 7.61 525.28 1.01 517.00 506.12 35.83

 MEAN 8.07 1.04 7.59 525.37 1.01 516.74 506.29 36.10

 HUB 8.13 1.05 7.57 526.52 1.01 516.49 507.27 36.34

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 20.18 35.33 31.50 3.83 0.93 0.24 1.40

 MEAN 23.02 27.42 23.50 3.92 0.91 0.26 1.62

 HUB 31.16 10.45 6.50 3.95 0.91 0.30 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.980 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 359.1733 130.1572 334.7605 1104.4169 0.3252 -0.1412 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0823 7.5217 515.5474 507.0304 37.4084 21.2464 32.4000 11.1536

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 340.9933 76.4748 332.3071 1105.4740 0.3085 -0.0476 2.2705

 

NASA/TM—2013-218094 L–268
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0742 7.5666 516.5353 506.6286 432.2457 0.0263 0.1881

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 338.5596 0.0000 338.5596 1105.5659 0.3062 0.0544 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5522 516.6233 506.5775 0.0000 0.0600 0.0754 -0.0764

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7988 8.0498 1.0351 525.6509 6.1971 305.2563 2.3663

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 39344.324 0.367 87.330 376733.781 0.687332E-02

 

Melt Ratio at Stator LE, Throat, TE

0.81885E+00 0.87129E+00 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.021 EfDer = 0.950 SH = 0.748718E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.278 1987.623 8.050 525.645 1.000 1.000 0.980

 W Kg/sec = 17.854 Wdry = 38.984 WH2O = 0.294 lbm/sec H2O = 4.793g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.206 1974.437 1.372 0.254 53.591 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 59093.355 30727.879 2.400 509.668 212.331 384.739 1.812

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 278.25 -0.10 278.25 0.25 0.38 315.65

 MEAN 15.91 0.00 -0.02 278.25 -0.10 278.25 0.25 0.35

 HUB 13.07 0.00 -0.02 278.25 -0.10 278.25 0.25 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.80 47.36 1.44 317.77 422.45 7.71 519.56 506.59 36.40

 MEAN 44.78 44.80 -0.02 276.02 392.00 7.71 519.56 506.59 36.40

 HUB 39.18 38.84 0.34 226.70 358.97 7.71 519.56 506.59 36.40

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.97 96.56 299.80 1111.81 0.28 2.05 1.78 7.43

 MEAN 15.50 320.31 111.65 300.22 1111.52 0.29 2.13 1.86 5.75

 HUB 12.59 341.89 162.38 300.87 1111.24 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 311.17 368.70 214.61 0.33 1734.04 0.92 0.87

 MEAN 268.81 338.87 157.16 0.30 1731.83 0.92 0.87 0.87 1.25

 HUB 218.38 306.04 56.00 0.28 2045.60 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.28 1.03 7.84 530.37 1.01 522.57 509.60 34.71

 MEAN 8.28 1.03 7.83 530.37 1.01 522.30 509.70 34.97

 HUB 8.33 1.03 7.81 531.22 1.01 522.03 510.46 35.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 17.85 35.60 31.50 4.10 0.93 0.21 1.40

 MEAN 20.40 27.63 23.50 4.13 0.90 0.22 1.64

 HUB 28.36 10.54 6.50 4.04 0.90 0.26 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.950 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.2254 113.6972 342.8655 1109.4551 0.3256 -0.2448 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2890 7.7133 520.4073 510.8010 37.1862 18.3460 33.0000 14.6540

 

NASA/TM—2013-218094 L–269
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 355.8295 81.2540 346.4281 1109.7723 0.3206 -0.2506 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2661 7.7086 520.7134 510.7415 410.5396 0.0686 0.1555

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 346.1987 0.0000 346.1987 1110.3296 0.3118 0.0196 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.7245 521.2456 510.8608 0.0000 0.0600 0.0983 -0.2168

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7073 8.2521 1.0251 530.6541 5.0090 353.0594 2.7369

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31895.590 0.329 70.796 399344.688 0.815354E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0799 Tt4 = 530.6541 T1 = 491.4065

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 249131.42 552.9795 86.2905 1.2671 0.8322 9.6194 1.0799 37.3740

NASA/TM—2013-218094 L–270
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.077 EfDer = 0.999 SH = 0.364448E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.266 1812.330 7.939 506.406 1.000 1.000 0.980

 W Kg/sec = 21.939 Wdry = 48.090 WH2O = 0.176 lbm/sec H2O = 2.429g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.303 1834.192 1.377 0.251 53.467 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 69759.617 37817.164 3.210 831.557 259.074 619.754 2.392

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 201.34 -0.07 201.34 0.18 0.35 330.20

 MEAN 17.06 0.00 -0.02 201.34 -0.07 201.34 0.18 0.31

 HUB 12.51 0.00 -0.02 201.34 -0.07 201.34 0.18 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.33 50.47 7.86 326.27 383.45 7.76 503.18 491.24 32.64

 MEAN 53.28 47.20 6.08 269.82 336.71 7.76 503.18 491.24 32.64

 HUB 44.51 38.62 5.89 197.85 282.33 7.76 503.18 491.24 32.64

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.39 176.67 278.01 1095.66 0.30 7.29 6.52 16.04

 MEAN 18.04 343.93 200.82 279.22 1094.76 0.31 7.43 6.80 12.53

 HUB 15.00 387.05 265.39 281.73 1093.02 0.35 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 326.27 315.71 149.61 0.29 3646.04 0.92 0.91

 MEAN 285.25 291.71 84.43 0.27 3623.10 0.92 0.91 0.91 1.29

 HUB 237.23 283.14 28.15 0.26 3981.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.93 515.58 1.02 506.95 499.24 35.93

 MEAN 8.43 1.06 7.88 515.52 1.02 506.11 499.48 36.86

 HUB 8.48 1.07 7.78 516.42 1.02 504.51 500.74 38.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.43 28.29 24.20 4.09 0.93 0.30 1.80

 MEAN 35.72 16.83 12.70 4.13 0.93 0.27 2.22

 HUB 43.29 -5.71 -9.30 3.59 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 360.7246 200.4254 299.9198 1093.9731 0.3297 -0.0719 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4388 7.8367 505.5172 500.2537 38.6191 33.7534 35.4000 1.6466

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 304.9046 74.5890 295.6405 1097.1298 0.2779 0.2414 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4369 8.0031 508.4606 499.5267 554.9116 0.0133 0.3598

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 302.5833 0.0000 302.5833 1097.1910 0.2758 0.2656 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9966 508.5397 500.1643 0.0000 0.0600 0.0375 0.2302

NASA/TM—2013-218094 L–271
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8768 8.4228 1.0609 515.7946 9.4317 219.2038 1.6993

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59473.793 0.559 162.217 470427.344 0.510140E-02

 

Melt Ratio at Stator LE, Throat, TE

0.14846E-01 0.55932E-01 0.26416E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.664 EfDer = 0.990 SH = 0.589823E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.266 1812.330 8.423 515.770 1.000 1.000 0.980

 W Kg/sec = 21.939 Wdry = 47.981 WH2O = 0.285 lbm/sec H2O = 4.030g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.000 1817.427 1.374 0.253 53.540 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68043.922 37783.211 2.393 590.487 246.772 468.502 1.899

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 276.55 -0.10 276.55 0.25 0.39 325.91

 MEAN 18.08 0.00 -0.02 276.55 -0.10 276.55 0.25 0.36

 HUB 15.21 0.00 -0.02 276.55 -0.10 276.55 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.61 46.36 3.25 325.01 426.82 8.07 509.73 501.46 42.91

 MEAN 45.96 42.30 3.66 285.92 397.85 8.07 509.73 501.46 42.91

 HUB 41.03 37.84 3.19 240.55 366.59 8.07 509.73 501.46 42.91

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.07 111.17 301.21 1102.12 0.29 2.33 2.04 9.02

 MEAN 18.01 328.30 129.78 301.56 1101.90 0.30 2.40 2.13 7.35

 HUB 15.22 354.77 186.00 302.11 1101.69 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.95 368.21 211.78 0.33 2272.15 0.92 0.91

 MEAN 284.84 339.09 155.05 0.31 2339.10 0.92 0.91 0.91 1.26

 HUB 240.76 307.03 54.76 0.28 2832.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.24 521.43 1.01 513.29 504.80 39.02

 MEAN 8.74 1.04 8.23 521.59 1.01 513.08 505.01 39.25

 HUB 8.81 1.05 8.21 522.83 1.01 512.89 506.05 39.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 20.26 35.11 31.50 3.61 0.93 0.23 1.40

 MEAN 23.29 27.21 23.50 3.71 0.92 0.25 1.63

 HUB 31.62 10.27 6.50 3.77 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.3388 130.1469 340.3007 1100.1389 0.3312 -0.1901 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7585 8.1292 511.4564 505.9365 41.2764 20.9292 30.6000 9.6708

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 336.0350 71.2418 328.3963 1101.8055 0.3050 -0.0309 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7512 8.2126 513.0082 505.3423 491.5697 0.0236 0.1719

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 348.3751 0.0000 348.3751 1101.0416 0.3164 0.0386 0.5911

NASA/TM—2013-218094 L–272
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1535 512.3013 505.6450 0.0000 0.0600 0.0665 -0.1414

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8216 8.7283 1.0363 521.8826 6.1804 296.2618 2.2966

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 39143.926 0.375 106.766 436585.938 0.606698E-02

 

Melt Ratio at Stator LE, Throat, TE

0.68668E+00 0.73869E+00 0.88467E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.326 EfDer = 0.955 SH = 0.620740E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.266 1812.330 8.728 521.865 1.000 1.000 0.980

 W Kg/sec = 21.939 Wdry = 47.966 WH2O = 0.300 lbm/sec H2O = 4.327g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.537 1806.795 1.373 0.253 53.550 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66688.438 37778.535 2.277 545.479 239.592 424.468 1.772

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 293.41 -0.10 293.41 0.27 0.39 316.44

 MEAN 17.74 0.00 -0.02 293.41 -0.10 293.41 0.27 0.37

 HUB 15.05 0.00 -0.02 293.41 -0.10 293.41 0.27 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.26 46.36 0.90 317.42 432.33 8.32 515.07 504.88 38.26

 MEAN 43.73 43.40 0.33 280.54 406.02 8.32 515.07 504.88 38.26

 HUB 39.06 38.84 0.22 238.02 377.88 8.32 515.07 504.88 38.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 331.75 86.36 320.31 1106.53 0.30 2.26 1.98 8.75

 MEAN 17.51 338.73 110.66 320.15 1106.73 0.31 2.34 2.07 6.78

 HUB 14.85 365.14 175.34 320.29 1106.94 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 313.31 392.56 226.95 0.35 1712.84 0.92 0.87

 MEAN 276.88 360.73 166.22 0.33 1939.00 0.92 0.87 0.87 1.20

 HUB 234.86 325.77 59.53 0.29 2605.25 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.96 1.03 8.43 526.13 1.01 517.45 507.70 36.74

 MEAN 8.99 1.03 8.44 526.70 1.01 517.64 508.06 36.51

 HUB 9.08 1.04 8.43 528.36 1.01 517.84 509.26 36.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 15.09 35.32 31.50 3.82 0.93 0.16 1.40

 MEAN 19.07 27.44 23.50 3.94 0.90 0.20 1.62

 HUB 28.70 10.53 6.50 4.03 0.90 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 377.9530 111.3820 361.1683 1104.7274 0.3421 -0.2045 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0052 8.3170 515.7980 509.1885 38.8771 17.1394 31.5000 14.3606

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 362.8484 79.1529 354.1098 1105.6664 0.3282 -0.1326 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9906 8.3559 516.6822 508.9384 451.3937 0.0353 0.1273

 

NASA/TM—2013-218094 L–273
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 369.9199 0.0000 369.9199 1105.2207 0.3347 -0.0262 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2990 516.2756 509.4147 0.0000 0.0600 0.0963 -0.2311

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7025 8.9553 1.0260 527.0617 5.1965 333.7129 2.5869

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 32954.918 0.336 89.886 442100.531 0.672677E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.730 EfDer = 0.900 SH = 0.742183E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.266 1812.330 8.955 527.060 1.000 1.000 0.980

 W Kg/sec = 21.939 Wdry = 47.907 WH2O = 0.358 lbm/sec H2O = 5.235g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.864 1797.896 1.372 0.254 53.589 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65907.953 37760.125 2.186 513.330 234.843 395.845 1.686

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 308.13 -0.11 308.13 0.28 0.39 302.17

 MEAN 16.97 0.00 -0.02 308.13 -0.11 308.13 0.28 0.37

 HUB 14.32 0.00 -0.02 308.13 -0.11 308.13 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.68 46.36 -1.68 304.61 433.35 8.50 519.60 509.45 39.71

 MEAN 41.07 43.80 -2.73 268.40 408.70 8.50 519.60 509.45 39.71

 HUB 36.33 37.84 -1.51 226.48 382.47 8.50 519.60 509.45 39.71

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 340.91 59.40 335.69 1109.83 0.31 2.16 1.89 8.34

 MEAN 16.57 346.27 87.11 335.13 1110.37 0.31 2.24 1.97 6.35

 HUB 13.89 369.93 156.87 335.03 1110.90 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 298.60 412.19 239.20 0.37 1123.54 0.92 0.82

 MEAN 262.13 378.08 175.01 0.34 1445.62 0.92 0.82 0.82 1.15

 HUB 219.68 340.86 62.81 0.31 2180.44 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.10 1.02 8.53 529.85 1.01 520.72 511.71 39.81

 MEAN 9.14 1.02 8.56 530.65 1.01 521.23 512.12 39.20

 HUB 9.24 1.03 8.57 532.48 1.01 521.72 513.32 38.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.03 35.47 31.50 3.97 0.93 0.10 1.40

 MEAN 14.57 27.57 23.50 4.07 0.89 0.14 1.62

 HUB 25.09 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.900 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 379.3403 87.6038 369.0862 1108.6906 0.3422 -0.1682 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1541 8.4552 519.6932 513.1552 41.2633 13.3523 32.4000 19.0477

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 378.2752 84.8361 368.6394 1108.7523 0.3412 -0.1889 2.2705

 

NASA/TM—2013-218094 L–274
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1321 8.4387 519.7590 513.1959 432.2457 0.0463 0.0904

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 376.6222 0.0000 376.6222 1108.8502 0.3397 -0.0793 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3997 519.8587 513.3947 0.0000 0.0600 0.1262 -0.2532

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5167 9.0836 1.0143 530.9962 3.9363 407.3881 3.1580

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25060.230 0.281 68.353 460744.219 0.801908E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.574 EfDer = 0.837 SH = 0.873412E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.266 1812.330 9.084 530.994 1.000 1.000 0.980

 W Kg/sec = 21.939 Wdry = 47.844 WH2O = 0.422 lbm/sec H2O = 6.199g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.029 1791.223 1.370 0.255 53.632 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65500.777 37740.156 2.191 509.668 232.572 384.739 1.654

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 308.42 -0.11 308.42 0.28 0.38 286.36

 MEAN 15.91 0.00 -0.02 308.42 -0.11 308.42 0.28 0.36

 HUB 13.07 0.00 -0.02 308.42 -0.11 308.42 0.28 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.22 47.36 -4.14 289.74 423.24 8.62 523.54 513.10 41.24

 MEAN 39.23 44.80 -5.57 251.67 398.14 8.62 523.54 513.10 41.24

 HUB 33.84 38.84 -5.00 206.71 371.34 8.62 523.54 513.10 41.24

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 339.12 41.45 336.58 1112.95 0.30 2.05 1.78 7.43

 MEAN 15.50 342.81 67.95 336.01 1113.55 0.31 2.13 1.86 5.75

 HUB 12.59 362.27 135.59 335.94 1114.13 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 283.73 414.71 242.28 0.37 745.57 0.92 0.77

 MEAN 245.10 379.85 177.15 0.34 1054.78 0.92 0.77 0.77 1.12

 HUB 199.12 341.90 63.53 0.31 1708.50 0.92 0.77

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.17 1.01 8.61 532.84 1.00 523.83 514.94 42.18

 MEAN 9.21 1.01 8.64 533.61 1.00 524.40 515.29 41.46

 HUB 9.29 1.02 8.65 535.23 1.01 524.95 516.30 40.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.02 35.75 31.50 4.25 0.93 0.05 1.40

 MEAN 11.43 27.80 23.50 4.30 0.87 0.10 1.64

 HUB 21.98 10.71 6.50 4.21 0.87 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.837 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 391.2049 69.1981 385.0363 1110.8628 0.3522 -0.2797 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.2131 8.4709 521.9172 516.7477 44.7235 10.1883 33.0000 22.8117

 

NASA/TM—2013-218094 L–275
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 402.8957 92.0016 392.2507 1110.0863 0.3629 -0.4258 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1611 8.3798 521.1939 517.0855 410.5396 0.1078 0.0622

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 391.9032 0.0000 391.9032 1110.8091 0.3528 -0.0935 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.4015 521.8792 517.0259 0.0000 0.0600 0.1428 -0.3894

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3081 9.1403 1.0062 533.8916 2.8967 509.6528 3.9508

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 18514.080 0.230 50.498 490745.313 0.933878E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10000E+01 0.10000E+01 0.10000E+01

 trTOT = 1.0543 Tt4 = 533.8916 T1 = 506.4063

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 175146.95 477.7191 88.3032 1.1513 0.7180 6.0767 1.0543 37.3740

NASA/TM—2013-218094 L–276
Appendix M: NPSS cycle analysis and compressor code analysis for the descent conditions 

NPSS Cycle Analysis: 10μm, 9 g/m3

, ISA +27R 

************************************************************************************************************************************ 

Date:02/15/13 Time:13:36:04 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.69 Stator 1 exit: 481.37 Stator 2 inlet: 491.02 Stator 2 exit: 495.99 

 Stator 3 inlet: 505.90 Stator 3 exit: 510.41 Stator 4 inlet: 519.64 Stator 4 exit: 523.46 

 Stator 5 inlet: 531.01 Stator 5 exit: 534.32 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.87 

Fan Bypass Relative Humidity 1.31 

LPC Inlet Relative Humidity 1.21 

LPC Exit Relative Humidity 0.11 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 781.11 Fan/LPC Inlet Flow Velocity 188.24 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 464.88 

Additional Water at LPC Exit 0.0061626 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 27.00 254.87 640.1 1.1047 707.08 8.6946 781.11 9.515 0.736 10.000 1747.5 1653.4 1151.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 254.87 4.267 467.83 -18.66 0.0000 833.73 2.854 416.97 2543.5 0.7800 1.40077 0.0000507 254.86 0.013 0.0001

FS1 Inlet.Fl_O 254.87 4.267 467.83 -18.66 0.0000 833.73 3.892 455.67 4168.2 0.3649 1.40077 0.0000507 254.86 0.013 0.0001

FS12 Splitter.Fl_02 228.58 4.265 467.83 -18.66 0.0000 748.10 3.838 453.93 3531.8 0.3909 1.40077 0.0000507 228.57 0.012 0.0001

FS2 Splitter.Fl_01 26.29 4.265 467.83 -18.66 0.0000 86.04 4.171 464.88 830.5 0.1780 1.40077 0.0000507 26.29 0.001 0.0001

FS14 Fan.Fl_O 228.58 4.825 486.38 -14.21 0.0000 674.26 4.048 462.57 2606.7 0.5069 1.40061 0.0000507 228.57 0.012 0.0001

FS23 LPC.Fl_O 26.29 6.677 544.44 -0.29 0.0000 59.28 6.390 537.64 412.6 0.2516 1.39985 0.0000507 26.29 0.001 0.0001

FS24 VaporIN.Fl_O 26.45 6.677 552.66 -33.63 0.0000 60.09 6.380 545.53 412.6 0.2560 1.39887 0.0062133 26.29 0.163 0.0062

FS25 Bleed2.Fl_O 23.81 6.677 552.66 -33.63 0.0000 54.09 6.439 546.96 412.6 0.2286 1.39887 0.0062133 23.66 0.147 0.0062

FS3 HPC.Fl_O 22.65 40.596 1000.05 75.91 0.0000 11.39 35.690 965.15 49.7 0.4356 1.37975 0.0062133 22.51 0.140 0.0062

FS36 Bleed3.Fl_O 17.56 40.596 1000.05 75.91 0.0000 8.82 37.782 980.45 49.3 0.3242 1.37975 0.0062133 17.45 0.108 0.0062

FS4 Burner.Fl_O 17.75 39.662 1747.45 63.44 0.0113 12.07 37.446 1722.72 74.6 0.2950 1.32906 0.0062133 17.45 0.108 0.0197

FS45 HPT.Fl_O 23.73 9.517 1155.18 -42.70 0.0084 54.67 8.617 1124.88 265.4 0.3840 1.36413 0.0062133 23.38 0.145 0.0163

FS49 LPT.Fl_O 24.00 3.263 904.96 -104.42 0.0083 142.80 3.071 889.97 860.2 0.2976 1.37997 0.0062133 23.66 0.147 0.0162

FS5 TEGV.Fl_O 24.00 3.263 905.03 -104.42 0.0083 142.80 3.071 890.04 860.2 0.2976 1.37997 0.0062133 23.66 0.147 0.0162

FS8 Core_Nozz.Fl_O 24.00 3.263 905.10 -104.42 0.0083 142.81 2.854 872.27 613.4 0.4444 1.37996 0.0062133 23.66 0.147 0.0162

FS17 FanDuctLkg.Fl_O 228.58 4.825 486.38 -14.21 0.0000 674.26 4.048 462.57 2606.7 0.5069 1.40061 0.0000507 228.57 0.012 0.0001

FS171 Bleed15.Fl_O 231.23 4.825 487.14 -14.44 0.0000 682.60 3.914 458.85 2481.9 0.5548 1.40059 0.0001208 231.20 0.028 0.0001

FS172 FanDuct.Fl_O 231.23 4.825 487.14 -14.44 0.0000 682.60 3.914 458.85 2481.9 0.5548 1.40059 0.0001208 231.20 0.028 0.0001

FS173 Byp_Nozz.Fl_O 231.23 4.825 487.14 -14.44 0.0000 682.60 2.854 419.19 2006.9 0.8993 1.40059 0.0001208 231.20 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 748.10 1.131 0.9059 2577.527 1.0397 0.9075 -1437.9 1547.91 54.70

LPC 86.04 1.566 0.8352 2577.527 1.1638 0.8453 -683.4 7.00 3.80

HPC 54.09 6.080 0.8183 8960.406 1.8095 0.8569 -3600.2 61.59 58.25

HPT 12.07 4.167 0.8767 221.263 1.3642 0.8546 3600.2 

LPT 54.67 2.917 0.8553 72.024 1.2747 0.8357 2121.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 869.22 1.128 0.9077 2552.950 0.0415 0.8607 1.0235 0.9980 0.9905

LPC 74.31 1.526 0.7803 0.681 0.0000 1.1579 1.0753 1.0703 0.0003

HPC 49.19 5.840 0.8267 8721.527 10.9614 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.080 0.8767 1.330 4.0796 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.442 0.8617 0.810 2.4416 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–1
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2543.48 6187.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8761 778.37 21.14 9.517

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2785 778.37 21.14 3.263

TEGV 0.0000 0.2976 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 755.95 15.66 14.140

FanDuct 0.0000 0.5548 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 894.28 49.62 27.707

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 755.95 15.66 14.140

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1000.05 75.91 40.596

Splitter 8.6946 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 755.95 15.66 14.140

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9249.3 2044.3 3600.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6452 552.66 -33.63 6.677

LP_Shaft 2447.9 4551.3 2121.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7183 1000.05 75.91 39.662

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3786 1000.05 75.91 22.419

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1000.05 75.91 40.596

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1000.05 75.91 40.596

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1000.05 75.91 40.596

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.38 -14.21 4.825

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.38 -14.21 4.825

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.38 -14.21 4.825

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.38 -14.21 4.825

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1747.40 0.9995 0.0230 0.19641 0.01126 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.444 627.6 468.2

Byp_Nozz 1.690 0.9800 1.0000 0.9800 2006.86 0.899 884.9 6359.6

NASA/TM—2013-218094 M–2
************************************************************************************************************************************ 

Date:02/15/13 Time:13:36:29 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 467.03 Stator 1 exit: 474.23 Stator 2 inlet: 483.26 Stator 2 exit: 487.89 

 Stator 3 inlet: 497.16 Stator 3 exit: 501.36 Stator 4 inlet: 510.00 Stator 4 exit: 513.56 

 Stator 5 inlet: 520.63 Stator 5 exit: 523.71 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.35 

Fan Bypass Relative Humidity 1.69 

LPC Inlet Relative Humidity 1.54 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 731.04 Fan/LPC Inlet Flow Velocity 181.73 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 458.77 

Additional Water at LPC Exit 0.0055688 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 27.00 247.99 626.9 1.0745 673.55 8.7804 731.04 9.234 0.763 10.000 1719.3 1625.8 1133.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 247.99 4.201 461.52 -20.16 0.0000 818.27 2.947 416.97 2561.0 0.7300 1.40081 0.0000491 247.98 0.012 0.0000

FS1 Inlet.Fl_O 247.99 4.201 461.52 -20.16 0.0000 818.27 3.847 450.03 4168.2 0.3570 1.40081 0.0000491 247.98 0.012 0.0000

FS12 Splitter.Fl_02 222.64 4.199 461.52 -20.16 0.0000 734.98 3.796 448.37 3531.8 0.3826 1.40081 0.0000491 222.63 0.011 0.0000

FS2 Splitter.Fl_01 25.36 4.199 461.52 -20.16 0.0000 83.71 4.112 458.77 830.5 0.1730 1.40081 0.0000491 25.35 0.001 0.0000

FS14 Fan.Fl_O 222.64 4.718 478.80 -16.02 0.0000 666.30 3.981 456.09 2606.7 0.4985 1.40067 0.0000491 222.63 0.011 0.0000

FS23 LPC.Fl_O 25.36 6.436 533.24 -2.97 0.0000 58.71 6.164 526.71 412.6 0.2490 1.40002 0.0000491 25.35 0.001 0.0000

FS24 VaporIN.Fl_O 25.50 6.436 540.79 -33.10 0.0000 59.45 6.156 533.97 412.6 0.2529 1.39914 0.0056179 25.35 0.142 0.0056

FS25 Bleed2.Fl_O 22.95 6.436 540.79 -33.10 0.0000 53.51 6.211 535.34 412.6 0.2259 1.39914 0.0056179 22.82 0.128 0.0056

FS3 HPC.Fl_O 21.83 38.794 977.14 73.53 0.0000 11.35 34.141 943.22 49.7 0.4336 1.38124 0.0056179 21.71 0.122 0.0056

FS36 Bleed3.Fl_O 16.92 38.794 977.14 73.53 0.0000 8.80 36.123 958.07 49.3 0.3228 1.38124 0.0056179 16.83 0.095 0.0056

FS4 Burner.Fl_O 17.11 37.901 1719.25 61.22 0.0111 12.08 35.783 1694.83 74.6 0.2949 1.33055 0.0056179 16.83 0.095 0.0190

FS45 HPT.Fl_O 22.87 9.209 1137.76 -42.06 0.0083 54.05 8.361 1108.66 265.4 0.3784 1.36541 0.0056179 22.55 0.127 0.0156

FS49 LPT.Fl_O 23.13 3.313 901.95 -100.03 0.0082 135.33 3.139 888.66 860.2 0.2803 1.38030 0.0056179 22.82 0.128 0.0155

FS5 TEGV.Fl_O 23.13 3.313 902.02 -100.03 0.0082 135.34 3.139 888.73 860.2 0.2803 1.38029 0.0056179 22.82 0.128 0.0155

FS8 Core_Nozz.Fl_O 23.13 3.313 902.09 -100.03 0.0082 135.34 2.947 873.41 613.4 0.4150 1.38029 0.0056179 22.82 0.128 0.0155

FS17 FanDuctLkg.Fl_O 222.64 4.718 478.80 -16.02 0.0000 666.30 3.981 456.09 2606.7 0.4985 1.40067 0.0000491 222.63 0.011 0.0000

FS171 Bleed15.Fl_O 225.19 4.718 479.50 -16.22 0.0000 674.43 3.856 452.59 2481.9 0.5447 1.40066 0.0001118 225.16 0.025 0.0001

FS172 FanDuct.Fl_O 225.19 4.718 479.50 -16.22 0.0000 674.43 3.856 452.59 2481.9 0.5447 1.40066 0.0001118 225.16 0.025 0.0001

FS173 Byp_Nozz.Fl_O 225.19 4.718 479.50 -16.22 0.0000 674.43 2.947 419.08 2006.9 0.8481 1.40066 0.0001118 225.16 0.025 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 734.98 1.124 0.9051 2513.129 1.0374 0.9067 -1304.2 2083.10 54.58

LPC 83.71 1.533 0.8357 2513.129 1.1554 0.8453 -616.9 6.80 3.37

HPC 53.51 6.028 0.8175 8941.716 1.8069 0.8562 -3378.0 61.47 58.08

HPT 12.08 4.116 0.8754 220.202 1.3611 0.8533 3378.0 

LPT 54.05 2.780 0.8497 70.281 1.2595 0.8303 1921.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 853.97 1.121 0.9069 2489.166 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 71.52 1.497 0.7773 0.664 0.0000 1.1704 1.0709 1.0751 0.0003

HPC 48.66 5.791 0.8260 8703.336 10.9759 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.029 0.8754 1.323 4.0293 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.339 0.8560 0.791 2.3386 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–3
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.00 5634.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8445 760.80 20.21 9.209

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2685 760.80 20.21 3.313

TEGV 0.0000 0.2803 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.93 14.88 13.555

FanDuct 0.0000 0.5447 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 873.88 47.94 26.498

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.93 14.88 13.555

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 977.14 73.53 38.794

Splitter 8.7804 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.93 14.88 13.555

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9130.4 1943.1 3378.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5497 540.79 -33.10 6.436

LP_Shaft 2370.6 4256.3 1921.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6202 977.14 73.53 37.901

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2927 977.14 73.53 21.489

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 977.14 73.53 38.794

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 977.14 73.53 38.794

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 977.14 73.53 38.794

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 478.80 -16.02 4.718

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 478.80 -16.02 4.718

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 478.80 -16.02 4.718

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 478.80 -16.02 4.718

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1719.20 0.9995 0.0230 0.18710 0.01112 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.415 586.4 421.6

Byp_Nozz 1.601 0.9800 1.0000 0.9800 2006.86 0.848 834.4 5840.0

NASA/TM—2013-218094 M–4
************************************************************************************************************************************ 

Date:02/15/13 Time:13:36:53 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 39/ 2/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 464.96 Stator 1 exit: 471.97 Stator 2 inlet: 480.76 Stator 2 exit: 485.27 

 Stator 3 inlet: 494.29 Stator 3 exit: 498.37 Stator 4 inlet: 506.78 Stator 4 exit: 510.23 

 Stator 5 inlet: 517.12 Stator 5 exit: 520.10 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.52 

Fan Bypass Relative Humidity 1.84 

LPC Inlet Relative Humidity 1.66 

LPC Exit Relative Humidity 0.16 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 715.01 Fan/LPC Inlet Flow Velocity 179.23 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 416.97 Fan/LPC Inlet Static Temperature 456.91 

Additional Water at LPC Exit 0.0050613 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 27.00 254.64 639.4 1.0706 684.51 8.8138 715.01 9.110 0.772 10.000 1707.2 1614.2 1126.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 254.64 4.339 459.59 -20.61 0.0000 811.78 3.088 416.97 2565.2 0.7140 1.40083 0.0000469 254.62 0.012 0.0000

FS1 Inlet.Fl_O 254.64 4.339 459.59 -20.61 0.0000 811.78 3.980 448.35 4168.2 0.3536 1.40083 0.0000469 254.62 0.012 0.0000

FS12 Splitter.Fl_02 228.69 4.337 459.59 -20.61 0.0000 729.43 3.927 446.72 3531.8 0.3791 1.40083 0.0000469 228.68 0.011 0.0000

FS2 Splitter.Fl_01 25.95 4.337 459.59 -20.61 0.0000 82.76 4.249 456.91 830.5 0.1710 1.40083 0.0000469 25.95 0.001 0.0000

FS14 Fan.Fl_O 228.69 4.859 476.37 -16.59 0.0000 662.88 4.110 454.08 2606.7 0.4949 1.40070 0.0000469 228.68 0.011 0.0000

FS23 LPC.Fl_O 25.95 6.588 529.41 -3.87 0.0000 58.47 6.313 522.98 412.6 0.2479 1.40008 0.0000469 25.95 0.001 0.0000

FS24 VaporIN.Fl_O 26.08 6.588 536.31 -31.27 0.0000 59.15 6.305 529.62 412.6 0.2515 1.39928 0.0051081 25.95 0.133 0.0051

FS25 Bleed2.Fl_O 23.47 6.588 536.31 -31.27 0.0000 53.24 6.361 530.96 412.6 0.2246 1.39928 0.0051081 23.35 0.119 0.0051

FS3 HPC.Fl_O 22.33 39.531 968.21 74.17 0.0000 11.34 34.801 934.65 49.7 0.4329 1.38186 0.0051081 22.22 0.113 0.0051

FS36 Bleed3.Fl_O 17.31 39.531 968.21 74.17 0.0000 8.79 36.816 949.34 49.3 0.3224 1.38186 0.0051081 17.22 0.088 0.0051

FS4 Burner.Fl_O 17.50 38.620 1707.24 61.93 0.0110 12.08 36.463 1682.95 74.6 0.2948 1.33124 0.0051081 17.22 0.088 0.0184

FS45 HPT.Fl_O 23.39 9.425 1130.26 -40.18 0.0082 53.83 8.565 1101.60 265.4 0.3764 1.36601 0.0051081 23.08 0.118 0.0151

FS49 LPT.Fl_O 23.66 3.453 899.99 -96.70 0.0081 132.66 3.279 887.29 860.2 0.2742 1.38052 0.0051081 23.35 0.119 0.0150

FS5 TEGV.Fl_O 23.66 3.453 900.06 -96.70 0.0081 132.66 3.279 887.36 860.2 0.2742 1.38052 0.0051081 23.35 0.119 0.0150

FS8 Core_Nozz.Fl_O 23.66 3.453 900.14 -96.70 0.0081 132.67 3.088 872.86 613.4 0.4048 1.38051 0.0051081 23.35 0.119 0.0150

FS17 FanDuctLkg.Fl_O 228.69 4.859 476.37 -16.59 0.0000 662.88 4.110 454.08 2606.7 0.4949 1.40070 0.0000469 228.68 0.011 0.0000

FS171 Bleed15.Fl_O 231.30 4.859 477.05 -16.76 0.0000 670.91 3.983 450.67 2481.9 0.5404 1.40068 0.0001037 231.27 0.024 0.0001

FS172 FanDuct.Fl_O 231.30 4.859 477.05 -16.76 0.0000 670.91 3.983 450.67 2481.9 0.5404 1.40068 0.0001037 231.27 0.024 0.0001

FS173 Byp_Nozz.Fl_O 231.30 4.859 477.05 -16.76 0.0000 670.91 3.088 419.03 2006.9 0.8311 1.40068 0.0001037 231.27 0.024 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 729.43 1.120 0.9047 2486.043 1.0365 0.9062 -1301.3 2440.82 54.52

LPC 82.76 1.519 0.8360 2486.043 1.1519 0.8454 -614.5 6.72 3.30

HPC 53.24 6.000 0.8171 8932.940 1.8053 0.8558 -3416.3 61.51 58.09

HPT 12.08 4.097 0.8748 219.842 1.3601 0.8526 3416.3 

LPT 53.83 2.730 0.8474 69.608 1.2538 0.8282 1915.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 847.52 1.118 0.9065 2462.339 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.35 1.485 0.7760 0.657 0.0000 1.1764 1.0696 1.0773 0.0003

HPC 48.42 5.764 0.8255 8694.794 10.9768 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.012 0.8747 1.321 4.0116 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.301 0.8537 0.783 2.3011 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–5
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2565.20 5658.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8637 754.02 21.45 9.425

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2746 754.02 21.45 3.453

TEGV 0.0000 0.2742 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.37 16.18 13.836

FanDuct 0.0000 0.5404 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.96 48.86 27.013 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.37 16.18 13.836

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 968.21 74.17 39.531

Splitter 8.8138 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.37 16.18 13.836

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9083.6 1975.3 3416.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6078 536.31 -31.27 6.588

LP_Shaft 2340.2 4299.7 1915.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6798 968.21 74.17 38.620

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3449 968.21 74.17 21.921

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 968.21 74.17 39.531

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 968.21 74.17 39.531

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 968.21 74.17 39.531

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 476.37 -16.59 4.859

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 476.37 -16.59 4.859

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 476.37 -16.59 4.859

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 476.37 -16.59 4.859

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1707.17 0.9995 0.0230 0.19014 0.01104 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.405 571.7 420.4

Byp_Nozz 1.573 0.9800 1.0000 0.9800 2006.86 0.831 817.6 5877.9

NASA/TM—2013-218094 M–6
************************************************************************************************************************************ 

Date:02/15/13 Time:13:37:09 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 466.46 Stator 1 exit: 473.03 Stator 2 inlet: 481.24 Stator 2 exit: 485.45 

 Stator 3 inlet: 493.88 Stator 3 exit: 497.66 Stator 4 inlet: 505.52 Stator 4 exit: 508.71 

 Stator 5 inlet: 515.14 Stator 5 exit: 517.88 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.13 

Fan Bypass Relative Humidity 2.36 

LPC Inlet Relative Humidity 2.11 

LPC Exit Relative Humidity 0.24 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 675.10 Fan/LPC Inlet Flow Velocity 173.34 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 423.42 Fan/LPC Inlet Static Temperature 458.91 

Additional Water at LPC Exit 0.0045890 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 27.00 275.80 689.1 1.0618 731.69 8.9012 675.10 8.753 0.795 10.000 1696.8 1603.9 1121.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 275.80 4.831 461.41 -20.25 0.0000 791.32 3.578 423.42 2579.3 0.6690 1.40081 0.0000588 275.79 0.016 0.0001

FS1 Inlet.Fl_O 275.80 4.831 461.41 -20.25 0.0000 791.32 4.453 450.77 4168.2 0.3433 1.40081 0.0000588 275.79 0.016 0.0001

FS12 Splitter.Fl_02 247.95 4.829 461.41 -20.25 0.0000 711.76 4.397 449.21 3531.8 0.3682 1.40081 0.0000588 247.93 0.015 0.0001

FS2 Splitter.Fl_01 27.86 4.829 461.41 -20.25 0.0000 79.96 4.738 458.91 830.5 0.1650 1.40081 0.0000588 27.85 0.002 0.0001

FS14 Fan.Fl_O 247.95 5.368 477.11 -16.48 0.0000 651.06 4.576 455.82 2606.7 0.4828 1.40069 0.0000588 247.93 0.015 0.0001

FS23 LPC.Fl_O 27.86 7.146 526.76 -4.58 0.0000 57.73 6.854 520.53 412.6 0.2445 1.40011 0.0000588 27.85 0.002 0.0001

FS24 VaporIN.Fl_O 27.98 7.146 533.05 -29.43 0.0000 58.34 6.847 526.59 412.6 0.2477 1.39939 0.0046478 27.85 0.129 0.0046

FS25 Bleed2.Fl_O 25.18 7.146 533.05 -29.43 0.0000 52.51 6.906 527.88 412.6 0.2213 1.39939 0.0046478 25.07 0.117 0.0046

FS3 HPC.Fl_O 23.96 42.284 959.12 74.50 0.0000 11.33 37.245 925.98 49.7 0.4319 1.38247 0.0046478 23.85 0.111 0.0046

FS36 Bleed3.Fl_O 18.57 42.284 959.12 74.50 0.0000 8.78 39.390 940.48 49.3 0.3217 1.38247 0.0046478 18.49 0.086 0.0046

FS4 Burner.Fl_O 18.77 41.310 1696.80 62.30 0.0110 12.08 39.002 1672.62 74.6 0.2947 1.33183 0.0046478 18.49 0.086 0.0179

FS45 HPT.Fl_O 25.09 10.194 1125.30 -38.32 0.0082 53.28 9.285 1097.42 265.4 0.3718 1.36642 0.0046478 24.78 0.115 0.0146

FS49 LPT.Fl_O 25.39 3.943 907.98 -91.54 0.0081 125.20 3.768 896.68 860.2 0.2574 1.38013 0.0046478 25.07 0.117 0.0145

FS5 TEGV.Fl_O 25.39 3.943 908.05 -91.54 0.0081 125.21 3.768 896.75 860.2 0.2574 1.38013 0.0046478 25.07 0.117 0.0145

FS8 Core_Nozz.Fl_O 25.39 3.943 908.13 -91.54 0.0081 125.21 3.578 884.14 613.3 0.3774 1.38013 0.0046478 25.07 0.117 0.0145

FS17 FanDuctLkg.Fl_O 247.95 5.368 477.11 -16.48 0.0000 651.06 4.576 455.82 2606.7 0.4828 1.40069 0.0000588 247.93 0.015 0.0001

FS171 Bleed15.Fl_O 250.74 5.368 477.74 -16.63 0.0000 658.84 4.445 452.63 2481.9 0.5261 1.40068 0.0001097 250.72 0.028 0.0001

FS172 FanDuct.Fl_O 250.74 5.368 477.74 -16.63 0.0000 658.84 4.445 452.63 2481.9 0.5261 1.40068 0.0001097 250.72 0.028 0.0001

FS173 Byp_Nozz.Fl_O 250.74 5.368 477.74 -16.63 0.0000 658.84 3.578 425.39 2006.9 0.7836 1.40068 0.0001097 250.72 0.028 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 711.76 1.112 0.9037 2405.184 1.0340 0.9051 -1319.9 5050.19 54.11

LPC 79.96 1.480 0.8375 2405.184 1.1416 0.8462 -617.4 6.44 3.07

HPC 52.51 5.917 0.8157 8909.144 1.7993 0.8545 -3613.2 61.84 58.33

HPT 12.08 4.052 0.8741 219.259 1.3570 0.8520 3613.2 

LPT 53.28 2.585 0.8423 67.626 1.2371 0.8237 1937.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 826.99 1.109 0.9055 2382.251 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.85 1.449 0.7723 0.635 0.0000 1.1962 1.0683 1.0844 0.0003

HPC 47.76 5.686 0.8241 8671.632 10.9658 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.968 0.8740 1.318 3.9678 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.192 0.8485 0.761 2.1925 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–7
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2579.35 5787.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9268 747.77 22.54 10.194

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2947 747.77 22.54 3.943

TEGV 0.0000 0.2574 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 726.41 17.34 14.876

FanDuct 0.0000 0.5261 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 858.21 49.55 28.931

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 726.41 17.34 14.876

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 959.12 74.50 42.284

Splitter 8.9012 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 726.41 17.34 14.876

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9031.8 2101.1 3613.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7983 533.05 -29.43 7.146

LP_Shaft 2268.5 4485.3 1937.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8756 959.12 74.50 41.310

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5162 959.12 74.50 23.512

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 959.12 74.50 42.284

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 959.12 74.50 42.284

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 959.12 74.50 42.284

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 477.11 -16.48 5.368

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 477.11 -16.48 5.368

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 477.11 -16.48 5.368

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 477.11 -16.48 5.368

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1696.73 0.9995 0.0230 0.20325 0.01099 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.377 536.3 423.2

Byp_Nozz 1.500 0.9800 1.0000 0.9800 2006.86 0.784 776.7 6053.1

NASA/TM—2013-218094 M–8
************************************************************************************************************************************ 

Date:02/15/13 Time:13:37:27 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 16/ 30/ 1/14 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 474.92 Stator 1 exit: 480.59 Stator 2 inlet: 487.60 Stator 2 exit: 491.01 

 Stator 3 inlet: 498.31 Stator 3 exit: 501.31 Stator 4 inlet: 508.15 Stator 4 exit: 510.62 

 Stator 5 inlet: 516.13 Stator 5 exit: 518.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.08 

Fan Bypass Relative Humidity 3.23 

LPC Inlet Relative Humidity 2.94 

LPC Exit Relative Humidity 0.50 

HPC Relative Humidity 0.05 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 624.43 Fan/LPC Inlet Flow Velocity 174.79 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 438.58 Fan/LPC Inlet Static Temperature 468.53 

Additional Water at LPC Exit 0.0045731 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 27.00 301.85 742.1 1.0707 794.61 8.4735 624.43 8.166 0.828 10.000 1697.6 1604.2 1124.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 301.85 5.595 471.08 -18.23 0.0000 755.58 4.358 438.58 2595.4 0.6080 1.40073 0.0001104 301.82 0.033 0.0001

FS1 Inlet.Fl_O 301.85 5.595 471.08 -18.23 0.0000 755.58 5.199 461.29 4168.2 0.3255 1.40073 0.0001104 301.82 0.033 0.0001

FS12 Splitter.Fl_02 269.99 5.592 471.08 -18.23 0.0000 676.16 5.146 460.00 3531.8 0.3467 1.40073 0.0001104 269.96 0.030 0.0001

FS2 Splitter.Fl_01 31.86 5.592 471.08 -18.23 0.0000 79.80 5.487 468.53 830.5 0.1647 1.40073 0.0001104 31.86 0.004 0.0001

FS14 Fan.Fl_O 269.99 6.143 485.30 -14.82 0.0000 624.76 5.323 465.81 2606.7 0.4569 1.40061 0.0001104 269.96 0.030 0.0001

FS23 LPC.Fl_O 31.86 7.846 527.25 -4.76 0.0000 60.17 7.497 520.44 412.6 0.2557 1.40010 0.0001104 31.86 0.004 0.0001

FS24 VaporIN.Fl_O 32.01 7.846 533.51 -29.52 0.0000 60.81 7.488 526.46 412.6 0.2591 1.39938 0.0046835 31.86 0.149 0.0047

FS25 Bleed2.Fl_O 27.21 7.846 533.51 -29.52 0.0000 51.69 7.591 528.51 412.6 0.2177 1.39938 0.0046835 27.08 0.127 0.0047

FS3 HPC.Fl_O 25.89 45.691 956.02 73.52 0.0000 11.30 40.270 923.12 49.7 0.4309 1.38265 0.0046835 25.77 0.121 0.0047

FS36 Bleed3.Fl_O 20.06 45.691 956.02 73.52 0.0000 8.76 42.577 937.51 49.3 0.3210 1.38265 0.0046835 19.97 0.094 0.0047

FS4 Burner.Fl_O 20.28 44.639 1697.62 61.28 0.0111 12.08 42.145 1673.43 74.6 0.2948 1.33175 0.0046835 19.97 0.094 0.0180

FS45 HPT.Fl_O 27.11 11.173 1128.71 -38.44 0.0082 52.60 10.205 1101.58 265.4 0.3662 1.36616 0.0046835 26.76 0.125 0.0147

FS49 LPT.Fl_O 27.43 4.716 930.43 -86.93 0.0082 114.48 4.542 920.88 860.2 0.2339 1.37877 0.0046835 27.08 0.127 0.0146

FS5 TEGV.Fl_O 27.43 4.716 930.50 -86.93 0.0082 114.48 4.542 920.95 860.2 0.2339 1.37876 0.0046835 27.08 0.127 0.0146

FS8 Core_Nozz.Fl_O 27.43 4.716 930.57 -86.93 0.0082 114.49 4.358 910.61 613.4 0.3398 1.37876 0.0046835 27.08 0.127 0.0146

FS17 FanDuctLkg.Fl_O 269.99 6.143 485.30 -14.82 0.0000 624.76 5.323 465.81 2606.7 0.4569 1.40061 0.0001104 269.96 0.030 0.0001

FS171 Bleed15.Fl_O 274.79 6.143 486.14 -15.08 0.0000 636.42 5.176 462.88 2481.9 0.5008 1.40059 0.0001899 274.74 0.052 0.0002

FS172 FanDuct.Fl_O 274.79 6.143 486.14 -15.08 0.0000 636.42 5.176 462.88 2481.9 0.5008 1.40059 0.0001899 274.74 0.052 0.0002

FS173 Byp_Nozz.Fl_O 274.79 6.143 486.14 -15.08 0.0000 636.42 4.358 440.67 2006.9 0.7175 1.40059 0.0001899 274.74 0.052 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 676.16 1.098 0.9024 2254.369 1.0302 0.9037 -1301.7 -9825.89 52.68

LPC 79.80 1.403 0.8525 2254.369 1.1192 0.8594 -607.2 5.95 2.64

HPC 51.69 5.824 0.8140 8882.085 1.7919 0.8528 -3870.2 62.23 58.62

HPT 12.08 3.995 0.8740 218.636 1.3526 0.8521 3870.2 

LPT 52.60 2.369 0.8338 63.949 1.2106 0.8163 1908.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 785.63 1.096 0.9042 2232.874 0.0417 0.8607 1.0235 0.9980 0.9905

LPC 60.49 1.384 0.7656 0.595 0.0000 1.3192 1.0505 1.1135 0.0003

HPC 47.01 5.596 0.8224 8645.295 10.9531 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.912 0.8740 1.314 3.9123 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.030 0.8400 0.719 2.0298 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–9
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2595.42 5858.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0012 746.41 22.00 11.173

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3183 746.41 22.00 4.716

TEGV 0.0000 0.2339 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 725.24 16.85 16.172

FanDuct 0.0000 0.5008 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 855.94 48.79 31.310

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 725.24 16.85 16.172

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 956.02 73.52 45.691

Splitter 8.4735 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 725.24 16.85 16.172

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9008.3 2256.5 3870.2 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8013 533.51 -29.52 7.846

LP_Shaft 2148.5 4666.6 1908.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1065 956.02 73.52 44.639

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7183 956.02 73.52 25.496

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 956.02 73.52 45.691

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 956.02 73.52 45.691

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 956.02 73.52 45.691

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 485.30 -14.82 6.143

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 485.30 -14.82 6.143

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 485.30 -14.82 6.143

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 485.30 -14.82 6.143

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1697.56 0.9995 0.0230 0.22072 0.01105 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 489.8 417.6

Byp_Nozz 1.409 0.9800 1.0000 0.9800 2006.86 0.718 723.9 6182.8

NASA/TM—2013-218094 M–10
************************************************************************************************************************************ 

Date:02/15/13 Time:13:37:53 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 28/ 42/ 1/26 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 482.83 Stator 1 exit: 487.00 Stator 2 inlet: 491.75 Stator 2 exit: 493.63 

 Stator 3 inlet: 498.89 Stator 3 exit: 500.36 Stator 4 inlet: 505.39 Stator 4 exit: 506.46 

 Stator 5 inlet: 510.15 Stator 5 exit: 510.93 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.92 

Fan Bypass Relative Humidity 4.06 

LPC Inlet Relative Humidity 3.92 

LPC Exit Relative Humidity 1.25 

HPC Relative Humidity 0.06 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 576.87 Fan/LPC Inlet Flow Velocity 193.94 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 454.14 Fan/LPC Inlet Static Temperature 478.74 

Additional Water at LPC Exit 0.0041775 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 27.00 326.67 752.5 1.1211 843.62 7.1384 576.87 7.285 0.858 10.000 1703.7 1608.2 1132.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 326.67 6.516 481.87 -16.15 0.0000 710.13 5.297 454.14 2590.6 0.5520 1.40063 0.0001988 326.61 0.065 0.0002

FS1 Inlet.Fl_O 326.67 6.516 481.87 -16.15 0.0000 710.13 6.113 473.14 4168.2 0.3034 1.40063 0.0001988 326.61 0.065 0.0002

FS12 Splitter.Fl_02 286.53 6.513 481.87 -16.15 0.0000 623.18 6.078 472.44 3531.8 0.3157 1.40063 0.0001988 286.47 0.057 0.0002

FS2 Splitter.Fl_01 40.14 6.513 481.87 -16.15 0.0000 87.30 6.366 478.74 830.5 0.1808 1.40063 0.0001988 40.13 0.008 0.0002

FS14 Fan.Fl_O 286.53 7.056 494.23 -13.19 0.0000 582.56 6.257 477.54 2606.7 0.4177 1.40050 0.0001988 286.47 0.057 0.0002

FS23 LPC.Fl_O 40.14 8.233 522.29 -6.46 0.0000 71.90 7.698 512.35 412.6 0.3113 1.40016 0.0001988 40.13 0.008 0.0002

FS24 VaporIN.Fl_O 40.31 8.233 528.05 -29.08 0.0000 72.60 7.685 517.77 412.6 0.3152 1.39950 0.0043763 40.13 0.176 0.0044

FS25 Bleed2.Fl_O 28.22 8.233 528.05 -29.08 0.0000 50.82 7.975 523.27 412.6 0.2138 1.39950 0.0043763 28.09 0.123 0.0044

FS3 HPC.Fl_O 26.85 47.467 944.18 72.31 0.0000 11.21 41.942 912.29 49.7 0.4264 1.38340 0.0043763 26.73 0.117 0.0044

FS36 Bleed3.Fl_O 20.81 47.467 944.18 72.31 0.0000 8.69 44.288 926.20 49.3 0.3180 1.38340 0.0043763 20.72 0.091 0.0044

FS4 Burner.Fl_O 21.04 46.374 1703.69 59.79 0.0113 12.08 43.782 1679.43 74.6 0.2949 1.33133 0.0043763 20.72 0.091 0.0180

FS45 HPT.Fl_O 28.12 11.974 1137.29 -38.19 0.0084 51.10 11.002 1111.75 265.4 0.3540 1.36552 0.0043763 27.76 0.122 0.0146

FS49 LPT.Fl_O 28.45 5.623 961.64 -81.02 0.0083 101.24 5.463 954.06 860.2 0.2054 1.37680 0.0043763 28.09 0.123 0.0145

FS5 TEGV.Fl_O 28.45 5.623 961.71 -81.02 0.0083 101.24 5.463 954.13 860.2 0.2054 1.37680 0.0043763 28.09 0.123 0.0145

FS8 Core_Nozz.Fl_O 28.45 5.623 961.78 -81.02 0.0083 101.24 5.297 946.16 613.4 0.2959 1.37679 0.0043763 28.09 0.123 0.0145

FS17 FanDuctLkg.Fl_O 286.53 7.056 494.23 -13.19 0.0000 582.56 6.257 477.54 2606.7 0.4177 1.40050 0.0001988 286.47 0.057 0.0002

FS171 Bleed15.Fl_O 298.62 7.056 495.60 -13.83 0.0000 607.99 6.063 474.57 2481.9 0.4704 1.40046 0.0003673 298.51 0.110 0.0004

FS172 FanDuct.Fl_O 298.62 7.056 495.60 -13.83 0.0000 607.99 6.063 474.57 2481.9 0.4704 1.40046 0.0003673 298.51 0.110 0.0004

FS173 Byp_Nozz.Fl_O 298.62 7.056 495.60 -13.83 0.0000 607.99 5.297 456.58 2006.9 0.6532 1.40046 0.0003673 298.51 0.110 0.0004

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.18 1.083 0.9031 2043.757 1.0256 0.9042 -1201.1 -2757.63 49.89

LPC 87.30 1.264 0.8262 2043.757 1.0839 0.8319 -550.5 6.38 2.41

HPC 50.82 5.766 0.8128 8854.683 1.7881 0.8517 -3949.4 61.50 57.82

HPT 12.08 3.873 0.8750 216.456 1.3437 0.8539 3949.4 

LPT 51.10 2.129 0.8238 58.413 1.1798 0.8079 1751.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.08 1.081 0.9049 2024.270 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.44 1.311 0.7607 0.540 0.0000 1.6336 0.8496 1.0861 0.0003

HPC 46.22 5.541 0.8212 8618.623 11.0087 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.793 0.8750 1.301 3.7932 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.849 0.8299 0.657 1.8494 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–11
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2590.55 5857.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0383 737.68 21.62 11.974

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3301 737.68 21.62 5.623

TEGV 0.0000 0.2054 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 716.82 16.55 16.864

FanDuct 0.0000 0.4704 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 845.56 47.98 32.558

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 716.82 16.55 16.864

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 944.18 72.31 47.467

Splitter 7.1384 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 716.82 16.55 16.864

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8934.4 2321.7 3949.4 WB17Y Bleed> 0.3000 1.0000 1.0000 12.0922 528.05 -29.08 8.233

LP_Shaft 1969.9 4670.1 1751.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2216 944.18 72.31 46.374

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8190 944.18 72.31 26.697

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.18 72.31 47.467

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.18 72.31 47.467

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.18 72.31 47.467

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 494.23 -13.19 7.056

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 494.23 -13.19 7.056

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 494.23 -13.19 7.056

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 494.23 -13.19 7.056

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1703.62 0.9995 0.0230 0.23434 0.01131 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.296 434.3 384.0

Byp_Nozz 1.332 0.9800 1.0000 0.9800 2006.86 0.653 670.8 6225.6

NASA/TM—2013-218094 M–12
************************************************************************************************************************************ 

Date:02/15/13 Time:13:38:36 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 44/ 72/ 2/41 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 495.88 Stator 1 exit: 498.89 Stator 2 inlet: 501.74 Stator 2 exit: 502.57 

 Stator 3 inlet: 506.00 Stator 3 exit: 506.40 Stator 4 inlet: 509.72 Stator 4 exit: 509.81 

 Stator 5 inlet: 511.74 Stator 5 exit: 511.63 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.94 

Fan Bypass Relative Humidity 5.03 

LPC Inlet Relative Humidity 5.11 

LPC Exit Relative Humidity 2.67 

HPC Relative Humidity 0.07 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 523.25 Fan/LPC Inlet Flow Velocity 202.82 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 474.18 Fan/LPC Inlet Static Temperature 493.56 

Additional Water at LPC Exit 0.0042566 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 27.00 363.30 824.5 1.1323 933.61 6.3306 523.25 6.381 0.889 10.000 1733.0 1633.7 1161.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 363.30 7.943 496.98 -13.65 0.0000 657.95 6.740 474.18 2606.6 0.4900 1.40045 0.0003932 363.16 0.143 0.0004

FS1 Inlet.Fl_O 363.30 7.943 496.98 -13.65 0.0000 657.95 7.526 489.37 4168.2 0.2788 1.40045 0.0003932 363.16 0.143 0.0004

FS12 Splitter.Fl_02 313.74 7.939 496.98 -13.65 0.0000 568.48 7.504 489.04 3531.8 0.2849 1.40045 0.0003932 313.62 0.123 0.0004

FS2 Splitter.Fl_01 49.56 7.939 496.98 -13.65 0.0000 89.80 7.749 493.56 830.5 0.1862 1.40045 0.0003932 49.54 0.019 0.0004

FS14 Fan.Fl_O 313.74 8.505 507.90 -11.03 0.0000 536.46 7.707 493.80 2606.7 0.3776 1.40032 0.0003932 313.62 0.123 0.0004

FS23 LPC.Fl_O 49.56 9.109 525.34 -6.85 0.0000 80.47 8.352 512.46 412.6 0.3543 1.40009 0.0003932 49.54 0.019 0.0004

FS24 VaporIN.Fl_O 49.77 9.109 531.18 -29.89 0.0000 81.26 8.333 517.84 412.6 0.3590 1.39942 0.0046499 49.54 0.230 0.0046

FS25 Bleed2.Fl_O 29.86 9.109 531.18 -29.89 0.0000 48.75 8.847 526.77 412.6 0.2046 1.39942 0.0046499 29.72 0.138 0.0046

FS3 HPC.Fl_O 28.41 50.687 941.26 70.05 0.0000 11.10 44.927 910.25 49.7 0.4208 1.38352 0.0046499 28.28 0.132 0.0046

FS36 Bleed3.Fl_O 22.02 50.687 941.26 70.05 0.0000 8.60 47.368 923.74 49.3 0.3142 1.38352 0.0046499 21.92 0.102 0.0046

FS4 Burner.Fl_O 22.28 49.519 1733.03 56.99 0.0118 12.09 46.750 1708.43 74.6 0.2952 1.32957 0.0046499 21.92 0.102 0.0189

FS45 HPT.Fl_O 29.77 13.456 1166.48 -39.38 0.0088 48.76 12.470 1143.02 265.4 0.3356 1.36334 0.0046499 29.38 0.137 0.0153

FS49 LPT.Fl_O 30.12 7.042 1011.30 -77.14 0.0087 87.77 6.892 1005.41 860.2 0.1772 1.37341 0.0046499 29.72 0.138 0.0152

FS5 TEGV.Fl_O 30.12 7.042 1011.37 -77.14 0.0087 87.78 6.892 1005.48 860.2 0.1772 1.37341 0.0046499 29.72 0.138 0.0152

FS8 Core_Nozz.Fl_O 30.12 7.042 1011.44 -77.14 0.0087 87.78 6.740 999.45 613.3 0.2534 1.37340 0.0046499 29.72 0.138 0.0152

FS17 FanDuctLkg.Fl_O 313.74 8.505 507.90 -11.03 0.0000 536.46 7.707 493.80 2606.7 0.3776 1.40032 0.0003932 313.62 0.123 0.0004

FS171 Bleed15.Fl_O 333.65 8.505 509.29 -12.16 0.0000 571.28 7.473 490.81 2481.9 0.4337 1.40027 0.0006462 333.43 0.215 0.0006

FS172 FanDuct.Fl_O 333.65 8.505 509.29 -12.16 0.0000 571.28 7.473 490.81 2481.9 0.4337 1.40027 0.0006462 333.43 0.215 0.0006

FS173 Byp_Nozz.Fl_O 333.65 8.505 509.29 -12.16 0.0000 571.28 6.740 476.52 2006.9 0.5860 1.40027 0.0006462 333.43 0.215 0.0006

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 568.48 1.071 0.9050 1841.626 1.0220 0.9060 -1162.0 -1871.34 46.45

LPC 89.80 1.147 0.7025 1841.626 1.0571 0.7082 -476.9 7.00 2.16

HPC 48.75 5.564 0.8084 8787.337 1.7720 0.8475 -4120.0 61.53 57.60

HPT 12.09 3.680 0.8770 213.613 1.3284 0.8570 4120.0 

LPT 48.76 1.911 0.8164 52.782 1.1501 0.8024 1639.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 660.52 1.070 0.9069 1824.067 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 46.82 1.245 0.7556 0.486 0.0000 1.9180 0.6009 0.9297 0.0003

HPC 44.34 5.349 0.8168 8553.073 11.0361 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.606 0.8770 1.284 3.6058 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.685 0.8225 0.594 1.6850 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–13
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2606.60 5908.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0989 737.74 20.08 13.456

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3494 737.74 20.08 7.042

TEGV 0.0000 0.1772 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.19 15.08 18.256

FanDuct 0.0000 0.4337 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 844.06 46.06 34.887

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.19 15.08 18.256

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 941.26 70.05 50.687

Splitter 6.3306 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 717.19 15.08 18.256

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8892.7 2433.3 4120.0 WB17Y Bleed> 0.4000 1.0000 1.0000 19.9082 531.18 -29.89 9.109

LP_Shaft 1802.7 4775.1 1639.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4097 941.26 70.05 49.519

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9835 941.26 70.05 28.891

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.26 70.05 50.687

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.26 70.05 50.687

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 941.26 70.05 50.687

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 507.90 -11.03 8.505

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 507.90 -11.03 8.505

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 507.90 -11.03 8.505

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 507.90 -11.03 8.505

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1732.98 0.9995 0.0230 0.25934 0.01183 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.045 0.9801 1.0000 0.9800 613.40 0.253 381.8 357.5

Byp_Nozz 1.262 0.9800 1.0000 0.9800 2006.86 0.586 614.8 6375.5

NASA/TM—2013-218094 M–14
************************************************************************************************************************************ 

Date:02/15/13 Time:13:39:21 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 41/ 83/ 3/37 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 509.81 Stator 1 exit: 512.17 Stator 2 inlet: 514.54 Stator 2 exit: 515.29 

 Stator 3 inlet: 518.02 Stator 3 exit: 518.45 Stator 4 inlet: 521.06 Stator 4 exit: 521.25 

 Stator 5 inlet: 522.88 Stator 5 exit: 522.92 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.60 

Fan Bypass Relative Humidity 6.08 

LPC Inlet Relative Humidity 5.78 

LPC Exit Relative Humidity 3.48 

HPC Relative Humidity 0.10 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 484.46 Fan/LPC Inlet Flow Velocity 170.52 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.18 

Ambient Static Temperature 490.63 Fan/LPC Inlet Static Temperature 507.74 

Additional Water at LPC Exit 0.0041237 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 27.00 380.62 615.9 1.4205 874.87 6.9316 484.46 5.173 0.900 10.000 1678.4 1581.4 1149.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 380.62 9.342 510.16 -11.98 0.0000 593.82 8.149 490.63 2524.5 0.4460 1.40025 0.0006510 380.37 0.248 0.0007

FS1 Inlet.Fl_O 380.62 9.342 510.16 -11.98 0.0000 593.82 8.946 503.89 4168.2 0.2494 1.40025 0.0006510 380.37 0.248 0.0007

FS12 Splitter.Fl_02 332.63 9.337 510.16 -11.98 0.0000 519.22 8.915 503.46 3531.8 0.2580 1.40025 0.0006510 332.41 0.216 0.0007

FS2 Splitter.Fl_01 47.99 9.337 510.16 -11.98 0.0000 74.91 9.183 507.74 830.5 0.1543 1.40025 0.0006510 47.96 0.031 0.0007

FS14 Fan.Fl_O 332.63 9.798 518.06 -10.08 0.0000 498.62 9.017 505.91 2606.7 0.3464 1.40015 0.0006510 332.41 0.216 0.0007

FS23 LPC.Fl_O 47.99 10.453 532.69 -6.57 0.0000 68.37 9.843 523.62 412.6 0.2943 1.39995 0.0006510 47.96 0.031 0.0007

FS24 VaporIN.Fl_O 48.19 10.453 538.30 -28.89 0.0000 69.01 9.829 528.93 412.6 0.2978 1.39930 0.0047747 47.96 0.229 0.0048

FS25 Bleed2.Fl_O 28.91 10.453 538.30 -28.89 0.0000 41.41 10.238 535.11 412.6 0.1726 1.39930 0.0047747 28.77 0.137 0.0048

FS3 HPC.Fl_O 27.51 48.322 906.32 60.70 0.0000 11.06 42.876 876.62 49.7 0.4187 1.38553 0.0047747 27.38 0.131 0.0048

FS36 Bleed3.Fl_O 21.32 48.322 906.32 60.70 0.0000 8.57 45.182 889.52 49.3 0.3128 1.38553 0.0047747 21.22 0.101 0.0048

FS4 Burner.Fl_O 21.56 47.209 1678.36 48.15 0.0115 12.07 44.575 1654.46 74.6 0.2945 1.33238 0.0047747 21.22 0.101 0.0186

FS45 HPT.Fl_O 28.82 14.109 1153.86 -38.04 0.0085 44.77 13.250 1134.66 265.4 0.3045 1.36432 0.0047747 28.44 0.136 0.0151

FS49 LPT.Fl_O 29.15 8.387 1029.77 -67.94 0.0084 71.98 8.268 1025.78 860.2 0.1445 1.37240 0.0047747 28.77 0.137 0.0150

FS5 TEGV.Fl_O 29.15 8.387 1029.84 -67.94 0.0084 71.98 8.268 1025.85 860.2 0.1445 1.37240 0.0047747 28.77 0.137 0.0150

FS8 Core_Nozz.Fl_O 29.15 8.387 1029.91 -67.94 0.0084 71.99 8.149 1021.89 613.4 0.2052 1.37239 0.0047747 28.77 0.137 0.0150

FS17 FanDuctLkg.Fl_O 332.63 9.798 518.06 -10.08 0.0000 498.62 9.017 505.91 2606.7 0.3464 1.40015 0.0006510 332.41 0.216 0.0007

FS171 Bleed15.Fl_O 351.90 9.798 519.17 -11.11 0.0000 528.08 8.807 503.59 2481.9 0.3933 1.40011 0.0008760 351.59 0.308 0.0009

FS172 FanDuct.Fl_O 351.90 9.798 519.17 -11.11 0.0000 528.08 8.807 503.59 2481.9 0.3933 1.40011 0.0008760 351.59 0.308 0.0009

FS173 Byp_Nozz.Fl_O 351.90 9.798 519.17 -11.11 0.0000 528.08 8.149 492.54 2006.9 0.5198 1.40011 0.0008760 351.59 0.308 0.0009

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 519.22 1.049 0.8951 1596.527 1.0155 0.8958 -891.9 -1535.28 44.76

LPC 74.91 1.119 0.7424 1596.527 1.0442 0.7465 -367.1 8.35 1.96

HPC 41.41 4.623 0.7925 8510.501 1.6837 0.8310 -3575.5 69.67 64.23

HPT 12.07 3.346 0.8678 211.630 1.2990 0.8482 3575.5 

LPT 44.77 1.682 0.8019 46.613 1.1169 0.7900 1259.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 603.28 1.048 0.8969 1581.304 0.0441 0.8607 1.0235 0.9980 0.9905

LPC 39.28 1.181 0.7476 0.422 0.0000 1.9071 0.6613 0.9931 0.0003

HPC 37.66 4.452 0.8007 8283.616 10.6983 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.281 0.8677 1.272 3.2811 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.513 0.8079 0.524 1.5131 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 M–15
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2524.52 5731.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0639 723.48 15.91 14.109

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3383 723.48 15.91 8.387

TEGV 0.0000 0.1445 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 705.05 11.43 18.784

FanDuct 0.0000 0.3933 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 818.93 39.20 33.932

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 705.05 11.43 18.784

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 906.32 60.70 48.322

Splitter 6.9316 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 705.05 11.43 18.784

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8670.0 2166.0 3575.5 WB17Y Bleed> 0.4000 1.0000 1.0000 19.2741 538.30 -28.89 10.453

LP_Shaft 1583.4 4176.1 1259.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3011 906.32 60.70 47.209

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8885 906.32 60.70 28.276

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 906.32 60.70 48.322

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 906.32 60.70 48.322

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 906.32 60.70 48.322

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 518.06 -10.08 9.798

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 518.06 -10.08 9.798

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 518.06 -10.08 9.798

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 518.06 -10.08 9.798

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1678.29 0.9995 0.0230 0.24302 0.01145 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.029 0.9801 1.0000 0.9800 613.40 0.205 312.5 283.1 

Byp_Nozz 1.202 0.9800 1.0000 0.9800 2006.86 0.520 554.4 6063.8

NASA/TM—2013-218094 M–16
Compressor Code Analysis: 10μm, 9 g/m3

, ISA +27R 

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.503 EfDer = 0.954 SH = 0.100590E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.291 2447.949 4.265 467.792 1.000 1.000 0.980

 W Kg/sec = 11.950 Wdry = 26.264 WH2O = 0.026 lbm/sec H2O = 0.391g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.065 2577.601 1.380 0.249 53.381 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65178.254 20620.678 3.299 831.557 252.057 619.754 2.459

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 188.11 -0.06 188.11 0.18 0.46 464.03

 MEAN 17.06 0.00 -0.02 188.11 -0.06 188.11 0.18 0.39

 HUB 12.51 0.00 -0.02 188.11 -0.06 188.11 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.89 50.47 16.42 440.71 479.23 4.17 464.95 457.96 24.04

 MEAN 62.70 47.20 15.50 364.45 410.19 4.17 464.95 457.96 24.04

 HUB 54.86 38.62 16.24 267.24 326.86 4.17 464.95 457.96 24.04

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 394.89 304.30 251.67 1063.17 0.37 7.29 6.52 16.04

 MEAN 18.04 399.49 307.51 255.02 1060.04 0.38 7.43 6.80 12.53

 HUB 15.00 432.53 345.93 259.64 1056.20 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 440.71 286.26 136.41 0.27 6279.02 0.92 0.87

 MEAN 385.29 266.61 77.78 0.25 5547.34 0.92 0.87 0.87 1.77

 HUB 320.44 260.89 25.50 0.25 5189.82 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.92 1.15 4.48 489.31 1.05 476.80 473.45 22.20

 MEAN 4.84 1.13 4.39 486.80 1.04 474.00 472.21 24.60

 HUB 4.80 1.13 4.28 485.58 1.04 470.57 472.03 27.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.41 28.46 24.20 4.26 0.93 0.58 1.80

 MEAN 50.33 16.96 12.70 4.26 0.95 0.52 2.22

 HUB 53.11 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 411.1464 306.9116 273.5811 1059.6078 0.3880 -0.0358 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8488 4.3768 473.6880 472.7832 25.8036 48.2862 35.4000 -12.8862

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 271.4115 66.3955 263.1651 1068.0946 0.2541 0.5164 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8367 4.6271 481.3259 471.5856 554.9116 0.0360 0.6094

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 270.3220 0.0000 270.3220 1068.1079 0.2531 0.4860 1.3089

NASA/TM—2013-218094 M–17
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6062 481.3726 472.2845 0.0000 0.0600 0.0865 0.4718

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8142 4.8130 1.1286 487.2221 19.4362 167.6450 1.2996

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 121344.914 0.625 180.282 271298.250 0.186233E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.069 EfDer = 0.958 SH = 0.275292E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.291 2447.949 4.813 487.220 1.000 1.000 0.980

 W Kg/sec = 11.950 Wdry = 26.218 WH2O = 0.072 lbm/sec H2O = 1.145g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.822 2525.789 1.378 0.250 53.438 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60856.727 20606.469 2.588 590.487 228.165 468.502 2.053

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 247.33 -0.09 247.33 0.23 0.47 452.94

 MEAN 18.08 0.00 -0.02 247.33 -0.09 247.33 0.23 0.43

 HUB 15.21 0.00 -0.02 247.33 -0.09 247.33 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.61 46.36 14.25 439.00 503.95 4.64 482.34 474.57 34.09

 MEAN 57.37 42.30 15.07 386.19 458.68 4.64 482.34 474.57 34.09

 HUB 52.73 37.84 14.89 324.92 408.42 4.64 482.34 474.57 34.09

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 363.22 253.32 260.30 1082.20 0.34 2.33 2.04 9.02

 MEAN 18.01 362.71 249.82 262.96 1079.72 0.34 2.40 2.13 7.35

 HUB 15.22 384.29 277.43 265.91 1077.27 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 436.22 318.13 182.90 0.29 5174.53 0.92 0.88

 MEAN 384.74 295.55 134.91 0.27 4500.82 0.92 0.88 0.88 1.71

 HUB 325.20 270.17 47.77 0.25 4224.61 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.12 4.99 504.85 1.04 494.33 484.85 23.76

 MEAN 5.32 1.10 4.92 502.56 1.03 492.06 483.82 25.64

 HUB 5.28 1.10 4.84 501.62 1.03 489.84 483.74 27.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.22 35.09 31.50 3.59 0.93 0.55 1.40

 MEAN 43.53 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.21 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 387.8056 250.5231 296.0260 1078.5219 0.3596 -0.1066 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3264 4.8778 491.0188 484.4916 26.7768 40.2408 30.6000 -9.6408

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 286.2831 60.6940 279.7753 1084.4886 0.2640 0.3703 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3200 5.0722 496.4742 483.1998 491.5697 0.0256 0.4665

 

NASA/TM—2013-218094 M–18
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.7679 0.0000 296.7679 1083.9364 0.2738 0.3577 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0383 495.9862 483.6133 0.0000 0.0600 0.0664 0.2876

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8314 5.3033 1.1019 503.0056 15.7900 188.6419 1.4623

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 99040.055 0.520 147.144 246522.469 0.312907E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =13.088 EfDer = 0.973 SH = 0.365048E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.291 2447.949 5.303 503.004 1.000 1.000 0.980

 W Kg/sec = 11.950 Wdry = 26.195 WH2O = 0.096 lbm/sec H2O = 1.620g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.762 2485.845 1.377 0.251 53.467 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57047.387 20599.141 2.591 545.479 210.525 424.468 2.016

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.99 -0.09 250.99 0.23 0.46 435.37

 MEAN 17.74 0.00 -0.02 250.99 -0.09 250.99 0.23 0.42

 HUB 15.05 0.00 -0.02 250.99 -0.09 250.99 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.66 46.36 13.30 428.74 496.88 5.11 497.99 484.33 26.36

 MEAN 56.49 43.40 13.09 378.94 454.59 5.11 497.99 484.33 26.36

 HUB 52.03 38.84 13.19 321.50 407.94 5.11 497.99 484.33 26.36

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 354.96 237.18 264.09 1097.90 0.32 2.26 1.98 8.75

 MEAN 17.51 356.47 236.82 266.43 1095.78 0.33 2.34 2.07 6.78

 HUB 14.85 380.03 268.42 269.02 1093.70 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 423.19 323.02 186.01 0.29 4700.19 0.92 0.89

 MEAN 373.98 299.67 137.16 0.27 4147.45 0.92 0.89 0.89 1.66

 HUB 317.23 273.42 48.81 0.25 3987.34 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.87 1.11 5.47 518.98 1.03 508.95 493.00 19.65

 MEAN 5.80 1.09 5.40 517.10 1.03 506.99 492.26 20.88

 HUB 5.78 1.09 5.33 516.55 1.03 505.07 492.41 22.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.93 35.16 31.50 3.66 0.93 0.52 1.40

 MEAN 41.63 27.24 23.50 3.74 0.94 0.50 1.62

 HUB 44.94 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 382.7458 238.3749 299.4525 1094.5544 0.3497 -0.1145 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8151 5.3509 505.8977 492.9403 21.7959 38.5210 31.5000 -7.0210

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 294.5491 64.2539 287.4554 1099.6708 0.2679 0.3199 2.3726

 

NASA/TM—2013-218094 M–19
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8110 5.5328 510.6455 491.8001 451.3937 0.0198 0.4414

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 299.5588 0.0000 299.5588 1099.3993 0.2725 0.3433 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5102 510.4089 492.1696 0.0000 0.0600 0.0530 0.2663

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8523 5.7970 1.0931 517.5391 14.5378 193.8804 1.5029

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91462.000 0.511 135.885 245062.141 0.413694E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.507 EfDer = 0.983 SH = 0.479069E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.291 2447.949 5.797 517.538 1.000 1.000 0.980

 W Kg/sec = 11.950 Wdry = 26.165 WH2O = 0.126 lbm/sec H2O = 2.259g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.592 2450.693 1.375 0.252 53.504 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53694.613 20589.797 2.626 513.330 195.496 395.845 2.025

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 251.03 -0.09 251.03 0.23 0.44 411.89

 MEAN 16.97 0.00 -0.02 251.03 -0.09 251.03 0.23 0.40

 HUB 14.32 0.00 -0.02 251.03 -0.09 251.03 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.62 46.36 12.26 411.44 482.05 5.59 512.54 492.91 21.78

 MEAN 55.31 43.80 11.51 362.53 441.03 5.59 512.54 492.91 21.78

 HUB 50.64 37.84 12.80 305.91 395.79 5.59 512.54 492.91 21.78

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 341.57 217.53 263.35 1111.89 0.31 2.16 1.89 8.34

 MEAN 16.57 343.04 217.26 265.47 1109.98 0.31 2.24 1.97 6.35

 HUB 13.89 365.13 248.22 267.78 1108.10 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 403.32 322.29 185.80 0.29 4108.54 0.92 0.90

 MEAN 354.06 298.64 136.79 0.27 3602.39 0.92 0.90 0.90 1.62

 HUB 296.72 272.13 48.50 0.25 3449.08 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.33 1.09 5.93 531.45 1.03 522.20 500.06 17.23

 MEAN 6.26 1.08 5.87 529.74 1.02 520.41 499.43 18.15

 HUB 6.24 1.08 5.80 529.22 1.02 518.65 499.58 19.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.56 35.20 31.50 3.70 0.93 0.49 1.40

 MEAN 39.30 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.83 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.983 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 364.0066 218.4865 291.1433 1109.1086 0.3282 -0.0907 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2719 5.8286 519.6387 499.9900 18.7100 36.8861 32.4000 -4.4861

 

NASA/TM—2013-218094 M–20
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.2521 65.5436 284.8075 1113.0703 0.2626 0.2828 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2698 5.9812 523.3663 499.0750 432.2457 0.0153 0.4199

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.9400 0.0000 289.9400 1113.1586 0.2605 0.3298 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9748 523.4641 499.2832 0.0000 0.0600 0.0434 0.2672

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8671 6.2582 1.0796 530.1193 12.5959 208.8784 1.6192

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79534.383 0.489 118.164 250851.000 0.531763E-02

 

Melt Ratio at Stator LE, Throat, TE

0.86873E-02 0.17002E-01 0.47324E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =10.057 EfDer = 0.991 SH = 0.588409E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.291 2447.949 6.258 530.113 1.000 1.000 0.980

 W Kg/sec = 11.950 Wdry = 26.136 WH2O = 0.155 lbm/sec H2O = 2.931g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.430 2421.440 1.374 0.253 53.539 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50831.969 20580.811 2.779 509.668 183.403 384.739 2.098

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.35 -0.08 239.35 0.21 0.41 387.11

 MEAN 15.91 0.00 -0.02 239.35 -0.08 239.35 0.21 0.37

 HUB 13.07 0.00 -0.02 239.35 -0.08 239.35 0.21 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.56 47.36 11.20 391.36 458.82 6.06 525.59 499.68 18.20

 MEAN 54.86 44.80 10.06 339.94 415.82 6.06 525.59 499.68 18.20

 HUB 49.40 38.84 10.56 279.21 367.82 6.06 525.59 499.68 18.20

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 324.29 204.48 251.70 1124.38 0.29 2.05 1.78 7.43

 MEAN 15.50 322.85 199.59 253.76 1122.41 0.29 2.13 1.86 5.75

 HUB 12.59 339.17 222.54 255.96 1120.47 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.24 308.72 178.76 0.27 3669.89 0.92 0.91

 MEAN 331.07 285.80 131.48 0.25 3094.42 0.92 0.91 0.91 1.61

 HUB 268.95 260.14 46.42 0.23 2802.81 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.76 1.08 6.39 542.49 1.02 534.18 505.60 14.72

 MEAN 6.68 1.07 6.31 540.54 1.02 532.31 504.88 15.49

 HUB 6.64 1.06 6.24 539.56 1.02 530.47 504.76 16.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.09 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 38.19 27.39 23.50 3.89 0.94 0.46 1.64

 HUB 41.00 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.991 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 353.1478 203.2463 288.7981 1121.0018 0.3150 -0.1699 2.0437

 

NASA/TM—2013-218094 M–21
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6842 6.2477 531.0103 505.4684 16.1117 35.1366 33.0000 -2.1366

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.0387 67.3723 287.2434 1124.1212 0.2625 0.1651 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6820 6.3744 533.9752 504.7008 410.5396 0.0258 0.3956

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.9675 0.0000 286.9675 1124.4703 0.2552 0.3190 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3869 534.3170 504.7263 0.0000 0.0600 0.0382 0.1980

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8807 6.6773 1.0670 540.8173 10.7515 228.3323 1.7700

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68097.234 0.464 101.172 263157.531 0.621333E-02

 

Melt Ratio at Stator LE, Throat, TE

0.18357E+00 0.20762E+00 0.27941E+00

 trTOT = 1.1561 Tt4 = 540.8173 T1 = 467.7921

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 459478.56 682.6473 86.0646 1.5658 0.8352 15.5029 1.1561 37.3740

NASA/TM—2013-218094 M–22
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.578 EfDer = 0.954 SH = 0.880996E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.356 2370.637 4.199 461.486 1.000 1.000 0.980

 W Kg/sec = 11.526 Wdry = 25.334 WH2O = 0.022 lbm/sec H2O = 0.342g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.726 2513.201 1.381 0.249 53.377 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62918.086 19888.846 3.392 831.557 245.188 619.754 2.528

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 181.59 -0.06 181.59 0.17 0.44 452.44

 MEAN 17.06 0.00 -0.02 181.59 -0.06 181.59 0.17 0.38

 HUB 12.51 0.00 -0.02 181.59 -0.06 181.59 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.95 50.47 16.48 426.79 463.87 4.11 458.84 453.65 27.57

 MEAN 62.78 47.20 15.58 352.94 396.97 4.11 458.84 453.65 27.57

 HUB 54.95 38.62 16.33 258.80 316.21 4.11 458.84 453.65 27.57

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 382.40 294.83 243.53 1055.54 0.36 7.29 6.52 16.04

 MEAN 18.04 386.75 297.94 246.60 1052.59 0.37 7.43 6.80 12.53

 HUB 15.00 418.48 334.97 250.83 1048.97 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.79 276.99 131.96 0.26 6083.55 0.92 0.87

 MEAN 373.12 257.81 75.19 0.24 5374.70 0.92 0.87 0.87 1.77

 HUB 310.32 252.04 24.66 0.24 5025.40 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.15 4.40 481.68 1.04 469.95 468.77 25.28

 MEAN 4.74 1.13 4.32 479.33 1.04 467.33 467.51 27.94

 HUB 4.70 1.12 4.22 478.17 1.04 464.12 467.28 31.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.44 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.39 16.96 12.70 4.26 0.95 0.52 2.22

 HUB 53.17 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.9713 297.3600 264.4962 1052.1929 0.3782 -0.0358 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7447 4.3044 467.0322 468.0496 29.2371 48.3475 35.4000 -12.9475

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.9071 64.3151 254.9191 1060.1990 0.2480 0.5168 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7337 4.5381 474.1854 466.9697 554.9116 0.0352 0.6093

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.8184 0.0000 261.8184 1060.2092 0.2469 0.4854 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5181 474.2303 467.6013 0.0000 0.0600 0.0869 0.4712

NASA/TM—2013-218094 M–23
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8136 4.7111 1.1219 479.7219 18.2419 167.3736 1.2975

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 113804.242 0.625 163.070 264121.094 0.158478E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.062 EfDer = 0.958 SH = 0.231529E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.356 2370.637 4.711 479.720 1.000 1.000 0.980

 W Kg/sec = 11.526 Wdry = 25.297 WH2O = 0.059 lbm/sec H2O = 0.959g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.087 2465.065 1.379 0.250 53.423 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58950.059 19877.605 2.648 590.487 223.017 468.502 2.101

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 239.59 -0.08 239.59 0.23 0.46 442.05

 MEAN 18.08 0.00 -0.02 239.59 -0.08 239.59 0.23 0.42

 HUB 15.21 0.00 -0.02 239.59 -0.08 239.59 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.60 46.36 14.24 425.13 488.07 4.55 475.13 469.65 38.29

 MEAN 57.36 42.30 15.06 374.00 444.23 4.55 475.13 469.65 38.29

 HUB 52.72 37.84 14.88 314.66 395.56 4.55 475.13 469.65 38.29

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 351.95 244.88 252.79 1073.53 0.33 2.33 2.04 9.02

 MEAN 18.01 351.49 241.66 255.23 1071.19 0.33 2.40 2.13 7.35

 HUB 15.22 372.40 268.59 257.95 1068.89 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 422.44 308.91 177.56 0.29 5002.19 0.92 0.88 

 MEAN 372.58 286.85 130.92 0.27 4353.86 0.92 0.88 0.88 1.71

 HUB 314.93 262.08 46.34 0.25 4090.05 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.25 1.11 4.88 496.25 1.03 486.36 479.82 26.93

 MEAN 5.18 1.10 4.81 494.11 1.03 484.24 478.78 29.00

 HUB 5.15 1.09 4.74 493.24 1.03 482.16 478.67 31.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.09 35.08 31.50 3.58 0.93 0.55 1.40

 MEAN 43.44 27.16 23.50 3.66 0.95 0.52 1.63

 HUB 46.16 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.8116 242.3427 287.2358 1070.0554 0.3512 -0.1069 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1886 4.7704 483.2553 479.4090 30.2637 40.1545 30.6000 -9.5545

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 278.1724 58.9745 271.8490 1075.6769 0.2586 0.3681 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1829 4.9508 488.3530 478.2465 491.5697 0.0248 0.4642

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 288.2902 0.0000 288.2902 1075.1506 0.2681 0.3556 0.5911

NASA/TM—2013-218094 M–24
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9191 487.8947 478.6250 0.0000 0.0600 0.0659 0.2850

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8317 5.1672 1.0968 494.5289 14.8132 188.8337 1.4638

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92774.047 0.520 132.936 240195.891 0.262328E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.995 EfDer = 0.974 SH = 0.305496E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.356 2370.637 5.167 494.528 1.000 1.000 0.980

 W Kg/sec = 11.526 Wdry = 25.279 WH2O = 0.077 lbm/sec H2O = 1.346g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.434 2427.881 1.378 0.251 53.447 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55439.027 19871.787 2.641 545.479 206.552 424.468 2.055

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.91 -0.08 243.91 0.23 0.45 425.22

 MEAN 17.74 0.00 -0.02 243.91 -0.08 243.91 0.23 0.41

 HUB 15.05 0.00 -0.02 243.91 -0.08 243.91 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.57 46.36 13.21 415.20 481.62 4.99 489.79 479.28 29.88

 MEAN 56.40 43.40 13.00 366.97 440.71 4.99 489.79 479.28 29.88

 HUB 51.93 38.84 13.09 311.35 395.58 4.99 489.79 479.28 29.88

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 344.19 228.69 257.23 1088.34 0.32 2.26 1.98 8.75

 MEAN 17.51 345.79 228.67 259.39 1086.35 0.32 2.34 2.07 6.78

 HUB 14.85 368.79 259.75 261.78 1084.40 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 409.82 314.60 181.13 0.29 4532.12 0.92 0.89

 MEAN 362.17 291.73 133.50 0.27 4004.67 0.92 0.89 0.89 1.66

 HUB 307.21 266.05 47.46 0.25 3858.61 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.69 1.10 5.32 509.47 1.03 500.03 487.84 22.45

 MEAN 5.63 1.09 5.25 507.73 1.03 498.20 487.10 23.82

 HUB 5.61 1.09 5.19 507.25 1.03 496.41 487.23 25.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.64 35.15 31.50 3.65 0.93 0.52 1.40

 MEAN 41.40 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.78 10.28 6.50 3.78 0.94 0.50 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.3841 230.1677 291.4601 1085.1791 0.3422 -0.1152 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6413 5.2087 497.1645 487.7422 24.8559 38.2983 31.5000 -6.7983

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 287.0473 62.6174 280.1342 1089.9875 0.2633 0.3148 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6377 5.3764 501.5866 486.7131 451.3937 0.0191 0.4370

 

NASA/TM—2013-218094 M–25
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.8798 0.0000 291.8798 1089.7292 0.2678 0.3393 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3555 501.3635 487.0583 0.0000 0.0600 0.0520 0.2615

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8534 5.6248 1.0886 508.1464 13.6218 194.6367 1.5088

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85531.344 0.509 122.558 239047.078 0.345940E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.334 EfDer = 0.984 SH = 0.400601E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.356 2370.637 5.625 508.145 1.000 1.000 0.980

 W Kg/sec = 11.526 Wdry = 25.255 WH2O = 0.102 lbm/sec H2O = 1.869g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.589 2395.128 1.376 0.251 53.478 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 52334.082 19864.289 2.667 513.330 192.458 395.845 2.057

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.67 -0.08 244.67 0.22 0.43 402.55

 MEAN 16.97 0.00 -0.02 244.67 -0.08 244.67 0.22 0.39

 HUB 14.32 0.00 -0.02 244.67 -0.08 244.67 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.45 46.36 12.09 398.45 467.64 5.43 503.39 487.75 24.94

 MEAN 55.13 43.80 11.33 351.09 428.00 5.43 503.39 487.75 24.94

 HUB 50.45 37.84 12.61 296.25 384.29 5.43 503.39 487.75 24.94

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.53 209.19 257.20 1101.54 0.30 2.16 1.89 8.34

 MEAN 16.57 333.15 209.36 259.15 1099.75 0.30 2.24 1.97 6.35

 HUB 13.89 354.80 240.03 261.28 1098.00 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 390.58 314.73 181.40 0.29 3951.09 0.92 0.90

 MEAN 342.88 291.52 133.52 0.27 3471.34 0.92 0.90 0.90 1.61

 HUB 287.35 265.53 47.33 0.24 3335.18 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.11 1.09 5.75 521.13 1.03 512.40 494.79 19.88

 MEAN 6.05 1.08 5.68 519.56 1.02 510.74 494.17 20.91

 HUB 6.04 1.07 5.62 519.11 1.02 509.11 494.32 21.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.12 35.19 31.50 3.69 0.93 0.49 1.40

 MEAN 38.93 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.57 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.984 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 353.6627 210.5374 284.1677 1098.9152 0.3218 -0.0917 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0629 5.6498 510.0009 494.7102 21.5673 36.5344 32.4000 -4.1344

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 285.5442 64.0392 278.2704 1102.6255 0.2590 0.2755 2.2705

 

NASA/TM—2013-218094 M–26
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0612 5.7895 513.4579 493.8964 432.2457 0.0146 0.4137

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 283.2722 0.0000 283.2722 1102.7213 0.2569 0.3239 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7836 513.5605 494.1676 0.0000 0.0600 0.0424 0.2602

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8677 6.0505 1.0757 519.9293 11.7866 210.2968 1.6302

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74237.703 0.487 106.375 244944.391 0.449708E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.808 EfDer = 0.992 SH = 0.515999E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.356 2370.637 6.051 519.928 1.000 1.000 0.980

 W Kg/sec = 11.526 Wdry = 25.225 WH2O = 0.131 lbm/sec H2O = 2.536g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.677 2367.833 1.375 0.252 53.516 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49682.199 19855.162 2.814 509.668 181.108 384.739 2.124 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 233.94 -0.08 233.94 0.21 0.40 378.54

 MEAN 15.91 0.00 -0.02 233.94 -0.08 233.94 0.21 0.37

 HUB 13.07 0.00 -0.02 233.94 -0.08 233.94 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.32 47.36 10.96 379.00 445.45 5.87 515.59 494.88 22.01

 MEAN 54.61 44.80 9.81 329.20 403.93 5.87 515.59 494.88 22.01

 HUB 49.14 38.84 10.30 270.39 357.60 5.87 515.59 494.88 22.01

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.96 196.13 246.44 1113.31 0.28 2.05 1.78 7.43

 MEAN 15.50 313.88 191.94 248.35 1111.47 0.28 2.13 1.86 5.75

 HUB 12.59 330.07 215.07 250.38 1109.66 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.14 302.26 175.01 0.27 3520.07 0.92 0.91

 MEAN 320.61 279.70 128.67 0.25 2975.96 0.92 0.91 0.91 1.60

 HUB 260.46 254.46 45.39 0.23 2708.75 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.51 1.08 6.16 531.45 1.02 523.60 500.85 18.19

 MEAN 6.44 1.06 6.10 529.67 1.02 521.87 500.16 19.12

 HUB 6.40 1.06 6.03 528.80 1.02 520.17 500.06 20.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.51 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.70 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.66 10.28 6.50 3.78 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 343.6067 195.4643 282.5938 1110.1072 0.3095 -0.1718 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4422 6.0352 520.6321 500.7744 19.9407 34.6708 33.0000 -1.6708

 

NASA/TM—2013-218094 M–27
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 288.9437 65.9805 281.3095 1113.0089 0.2596 0.1555 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4404 6.1504 523.3645 500.0756 410.5396 0.0249 0.3878

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 281.0797 0.0000 281.0797 1113.3610 0.2525 0.3110 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1617 523.7063 500.1866 0.0000 0.0600 0.0376 0.1875

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8794 6.4359 1.0637 529.9548 10.0476 230.3414 1.7856

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63510.746 0.461 91.005 257230.000 0.561794E-02

 

Melt Ratio at Stator LE, Throat, TE

0.36052E-01 0.47644E-01 0.86871E-01

 trTOT = 1.1484 Tt4 = 529.9548 T1 = 461.4861

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 429858.06 615.9444 83.7264 1.5326 0.8356 15.5776 1.1484 37.3740

NASA/TM—2013-218094 M–28
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.599 EfDer = 0.953 SH = 0.801890E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.947 2340.176 4.337 459.556 1.000 1.000 0.980

 W Kg/sec = 11.794 Wdry = 25.926 WH2O = 0.021 lbm/sec H2O = 0.323g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.780 2486.115 1.381 0.249 53.374 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62052.168 20352.652 3.430 831.557 242.407 619.754 2.557

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 179.09 -0.06 179.09 0.17 0.44 447.56

 MEAN 17.06 0.00 -0.02 179.09 -0.06 179.09 0.17 0.38

 HUB 12.51 0.00 -0.02 179.09 -0.06 179.09 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.97 50.47 16.50 421.30 457.85 4.25 456.98 452.40 28.32

 MEAN 62.80 47.20 15.60 348.40 391.79 4.25 456.98 452.40 28.32

 HUB 54.98 38.62 16.36 255.48 312.05 4.25 456.98 452.40 28.32

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 377.50 291.04 240.42 1053.14 0.36 7.29 6.52 16.04

 MEAN 18.04 381.77 294.14 243.38 1050.26 0.36 7.43 6.80 12.53

 HUB 15.00 413.00 330.65 247.46 1046.73 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 421.30 273.44 130.26 0.26 6005.52 0.92 0.87

 MEAN 368.33 254.44 74.19 0.24 5306.14 0.92 0.87 0.87 1.77

 HUB 306.33 248.65 24.32 0.24 4960.55 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.54 479.24 1.04 467.80 467.38 26.00

 MEAN 4.88 1.13 4.46 476.95 1.04 465.25 466.10 28.69

 HUB 4.84 1.12 4.36 475.82 1.04 462.13 465.83 32.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.44 28.45 24.20 4.25 0.93 0.58 1.80

 MEAN 50.39 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 53.19 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 392.8263 293.5670 261.0190 1049.8777 0.3742 -0.0359 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8877 4.4432 464.9628 466.6159 30.0031 48.3588 35.4000 -12.9588

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 259.6592 63.5206 251.7698 1057.6929 0.2455 0.5168 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8768 4.6791 471.9284 465.6169 554.9116 0.0349 0.6090

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 258.5682 0.0000 258.5682 1057.7040 0.2445 0.4850 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6588 471.9726 466.2039 0.0000 0.0600 0.0870 0.4708

NASA/TM—2013-218094 M–29
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8135 4.8538 1.1191 477.3308 17.7805 167.3095 1.2970

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 110886.727 0.625 162.590 271029.688 0.143075E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =15.049 EfDer = 0.958 SH = 0.208547E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.947 2340.176 4.854 477.329 1.000 1.000 0.980

 W Kg/sec = 11.794 Wdry = 25.893 WH2O = 0.054 lbm/sec H2O = 0.895g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.382 2439.478 1.379 0.250 53.416 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58220.656 20342.365 2.673 590.487 220.920 468.502 2.121 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.62 -0.08 236.62 0.22 0.46 437.46

 MEAN 18.08 0.00 -0.02 236.62 -0.08 236.62 0.22 0.41

 HUB 15.21 0.00 -0.02 236.62 -0.08 236.62 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.59 46.36 14.23 419.67 481.85 4.69 472.85 468.13 39.29

 MEAN 57.35 42.30 15.05 369.19 438.58 4.69 472.85 468.13 39.29

 HUB 52.71 37.84 14.87 310.62 390.54 4.69 472.85 468.13 39.29

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 347.52 241.48 249.92 1070.72 0.32 2.33 2.04 9.02

 MEAN 18.01 347.12 238.42 252.28 1068.44 0.32 2.40 2.13 7.35

 HUB 15.22 367.78 265.11 254.91 1066.20 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 417.01 305.40 175.53 0.29 4932.73 0.92 0.88

 MEAN 367.80 283.52 129.38 0.27 4295.39 0.92 0.88 0.88 1.70

 HUB 310.88 258.99 45.77 0.24 4036.98 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.40 1.11 5.02 493.43 1.03 483.78 478.27 27.79

 MEAN 5.32 1.10 4.95 491.35 1.03 481.72 477.22 29.89

 HUB 5.30 1.09 4.88 490.51 1.03 479.70 477.09 32.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 44.02 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.38 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 46.12 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.1482 239.0883 283.8798 1067.3268 0.3477 -0.1071 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3350 4.9129 480.7574 477.8318 31.1785 40.1046 30.6000 -9.5046

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 275.0824 58.3194 268.8293 1072.8108 0.2564 0.3669 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3294 5.0946 485.7171 476.7497 491.5697 0.0244 0.4630

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 285.0583 0.0000 285.0583 1072.2954 0.2658 0.3545 0.5911

NASA/TM—2013-218094 M–30
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0625 485.2697 477.1040 0.0000 0.0600 0.0656 0.2837

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8320 5.3135 1.0947 491.7609 14.4361 188.9730 1.4649

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90345.727 0.520 132.471 246562.266 0.236046E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.948 EfDer = 0.974 SH = 0.274761E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.947 2340.176 5.314 491.760 1.000 1.000 0.980

 W Kg/sec = 11.794 Wdry = 25.875 WH2O = 0.071 lbm/sec H2O = 1.252g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.893 2403.420 1.378 0.250 53.437 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54825.539 20337.039 2.662 545.479 204.928 424.468 2.071

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 241.21 -0.08 241.21 0.22 0.44 420.93

 MEAN 17.74 0.00 -0.02 241.21 -0.08 241.21 0.22 0.41

 HUB 15.05 0.00 -0.02 241.21 -0.08 241.21 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.53 46.36 13.17 409.87 475.65 5.13 487.12 477.72 30.84

 MEAN 56.35 43.40 12.95 362.25 435.28 5.13 487.12 477.72 30.84

 HUB 51.88 38.84 13.04 307.35 390.77 5.13 487.12 477.72 30.84

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.97 225.27 254.63 1085.18 0.31 2.26 1.98 8.75

 MEAN 17.51 341.63 225.40 256.72 1083.25 0.32 2.34 2.07 6.78

 HUB 14.85 364.40 256.31 259.03 1081.34 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.56 311.42 179.29 0.29 4464.22 0.92 0.89

 MEAN 357.52 288.72 132.12 0.27 3947.46 0.92 0.89 0.89 1.65

 HUB 303.27 263.25 46.95 0.24 3807.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.84 1.10 5.46 506.30 1.03 497.08 486.26 23.28

 MEAN 5.78 1.09 5.40 504.62 1.03 495.31 485.51 24.68

 HUB 5.76 1.08 5.33 504.16 1.03 493.57 485.63 26.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.50 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 41.28 27.23 23.50 3.73 0.94 0.50 1.62

 HUB 44.70 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 366.9610 226.8794 288.4200 1082.0924 0.3391 -0.1157 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7905 5.3540 494.2922 486.1375 25.7442 38.1896 31.5000 -6.6896

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 284.2022 61.9968 277.3577 1086.7778 0.2615 0.3124 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7870 5.5224 498.5878 485.1771 451.3937 0.0187 0.4349

 

NASA/TM—2013-218094 M–31
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.9655 0.0000 288.9655 1086.5244 0.2660 0.3374 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5013 498.3697 485.5032 0.0000 0.0600 0.0515 0.2591

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8540 5.7741 1.0867 505.0245 13.2679 195.0235 1.5118

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83227.336 0.509 122.034 245498.094 0.311029E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.253 EfDer = 0.985 SH = 0.360196E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.947 2340.176 5.774 505.023 1.000 1.000 0.980

 W Kg/sec = 11.794 Wdry = 25.853 WH2O = 0.093 lbm/sec H2O = 1.737g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.180 2371.649 1.377 0.251 53.465 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51817.410 20330.154 2.685 513.330 191.212 395.845 2.070

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 242.26 -0.08 242.26 0.22 0.42 398.60

 MEAN 16.97 0.00 -0.02 242.26 -0.08 242.26 0.22 0.39

 HUB 14.32 0.00 -0.02 242.26 -0.08 242.26 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.38 46.36 12.02 393.33 462.02 5.58 500.35 486.16 25.89

 MEAN 55.05 43.80 11.25 346.57 422.92 5.58 500.35 486.16 25.89

 HUB 50.37 37.84 12.53 292.44 379.81 5.58 500.35 486.16 25.89

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.60 205.83 254.87 1098.07 0.30 2.16 1.89 8.34

 MEAN 16.57 329.30 206.19 256.76 1096.33 0.30 2.24 1.97 6.35

 HUB 13.89 350.82 236.83 258.82 1094.62 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 385.57 311.88 179.74 0.28 3887.60 0.92 0.90

 MEAN 338.47 288.83 132.28 0.26 3418.81 0.92 0.90 0.90 1.60

 HUB 283.66 263.02 46.83 0.24 3290.76 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.26 1.08 5.89 517.65 1.03 509.12 493.18 20.70

 MEAN 6.20 1.07 5.83 516.13 1.02 507.50 492.56 21.76

 HUB 6.19 1.07 5.77 515.71 1.02 505.92 492.69 22.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.92 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.77 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.46 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.6446 207.3513 281.5259 1095.5070 0.3192 -0.0921 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2142 5.7973 506.7798 493.0782 22.4486 36.3726 32.4000 -3.9726

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 283.0136 63.4717 275.8044 1099.1154 0.2575 0.2721 2.2705

 

NASA/TM—2013-218094 M–32
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2125 5.9370 510.1309 492.3173 432.2457 0.0144 0.4109

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.7510 0.0000 280.7510 1099.2104 0.2554 0.3212 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9312 510.2322 492.5751 0.0000 0.0600 0.0420 0.2570

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8684 6.2018 1.0741 516.4962 11.4754 210.9562 1.6353

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72185.813 0.486 105.844 251658.875 0.404351E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.698 EfDer = 0.993 SH = 0.464083E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.947 2340.176 6.202 516.495 1.000 1.000 0.980

 W Kg/sec = 11.794 Wdry = 25.826 WH2O = 0.120 lbm/sec H2O = 2.355g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.370 2345.163 1.375 0.252 53.499 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49243.586 20321.758 2.829 509.668 180.150 384.739 2.136

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.87 -0.08 231.87 0.21 0.40 374.92

 MEAN 15.91 0.00 -0.02 231.87 -0.08 231.87 0.21 0.36

 HUB 13.07 0.00 -0.02 231.87 -0.08 231.87 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.22 47.36 10.86 374.13 440.23 6.02 512.23 493.26 22.95

 MEAN 54.50 44.80 9.70 324.97 399.28 6.02 512.23 493.26 22.95

 HUB 49.03 38.84 10.19 266.91 353.63 6.02 512.23 493.26 22.95

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 311.32 192.78 244.45 1109.57 0.28 2.05 1.78 7.43

 MEAN 15.50 310.39 188.90 246.29 1107.78 0.28 2.13 1.86 5.75

 HUB 12.59 326.55 212.14 248.26 1106.02 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.37 299.81 173.59 0.27 3459.97 0.92 0.91

 MEAN 316.49 277.38 127.59 0.25 2928.72 0.92 0.91 0.91 1.59

 HUB 257.11 252.30 44.97 0.23 2671.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.66 1.07 6.31 527.70 1.02 520.01 499.24 19.11

 MEAN 6.59 1.06 6.25 525.98 1.02 518.34 498.55 20.07

 HUB 6.55 1.06 6.18 525.15 1.02 516.69 498.44 21.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.26 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.49 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.51 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.9008 192.3607 280.2319 1106.4363 0.3072 -0.1726 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5946 6.1838 517.1191 499.1565 20.9522 34.4670 33.0000 -1.4670

 

NASA/TM—2013-218094 M–33
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 286.6301 65.4522 279.0570 1109.2524 0.2584 0.1513 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5930 6.2988 519.7624 498.5129 410.5396 0.0246 0.3844

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.8433 0.0000 278.8433 1109.6051 0.2513 0.3075 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3101 520.1039 498.6570 0.0000 0.0600 0.0373 0.1829

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 6.5884 1.0623 526.2628 9.7797 231.2794 1.7929

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 61721.898 0.460 90.501 264374.500 0.510813E-02

 

Melt Ratio at Stator LE, Throat, TE

0.10791E-01 0.17112E-01 0.41805E-01

 trTOT = 1.1452 Tt4 = 526.2628 T1 = 459.5564

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 418367.50 613.4403 82.7803 1.5191 0.8361 15.5991 1.1452 37.3740

NASA/TM—2013-218094 M–34
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.653 EfDer = 0.953 SH = 0.811165E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.855 2268.543 4.829 461.382 1.000 1.000 0.980

 W Kg/sec = 12.661 Wdry = 27.833 WH2O = 0.023 lbm/sec H2O = 0.363g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.982 2405.254 1.381 0.249 53.375 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60013.164 21849.686 3.550 831.557 234.217 619.754 2.646 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.21 -0.06 173.21 0.17 0.43 433.01

 MEAN 17.06 0.00 -0.02 173.21 -0.06 173.21 0.17 0.36

 HUB 12.51 0.00 -0.02 173.21 -0.06 173.21 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 67.02 50.47 16.55 408.41 443.67 4.74 458.97 454.39 29.06

 MEAN 62.85 47.20 15.65 337.74 379.61 4.74 458.97 454.39 29.06

 HUB 55.04 38.62 16.42 247.66 302.27 4.74 458.97 454.39 29.06

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 366.02 282.12 233.19 1054.60 0.35 7.29 6.52 16.04

 MEAN 18.04 370.07 285.16 235.87 1051.91 0.35 7.43 6.80 12.53

 HUB 15.00 400.12 320.49 239.55 1048.61 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 408.41 265.19 126.29 0.25 5821.35 0.92 0.87

 MEAN 357.06 246.58 71.89 0.23 5144.19 0.92 0.87 0.87 1.77

 HUB 296.95 240.71 23.54 0.23 4808.08 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.04 479.88 1.04 469.13 468.58 26.80

 MEAN 5.39 1.12 4.96 477.73 1.04 466.74 467.35 29.36

 HUB 5.35 1.11 4.85 476.66 1.03 463.81 467.07 32.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.42 28.44 24.20 4.24 0.93 0.58 1.80

 MEAN 50.40 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 53.22 -5.61 -9.30 3.69 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.953 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 380.7440 284.6075 252.9123 1051.5505 0.3621 -0.0360 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.4005 4.9388 466.4642 467.8342 30.6253 48.3746 35.4000 -12.9746

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 252.1879 61.6929 244.5255 1058.8588 0.2382 0.5165 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3896 5.1836 472.9864 466.9227 554.9116 0.0338 0.6078

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 251.0828 0.0000 251.0828 1058.8729 0.2371 0.4836 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1621 473.0299 467.4573 0.0000 0.0600 0.0871 0.4694

NASA/TM—2013-218094 M–35
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8130 5.3652 1.1111 478.0822 16.7057 167.1285 1.2956

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 104191.086 0.625 164.010 289802.156 0.138794E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.998 EfDer = 0.958 SH = 0.198572E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.855 2268.543 5.365 478.080 1.000 1.000 0.980

 W Kg/sec = 12.661 Wdry = 27.800 WH2O = 0.055 lbm/sec H2O = 0.942g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.272 2362.946 1.379 0.250 53.413 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56549.461 21839.578 2.750 590.487 214.725 468.502 2.182

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 229.83 -0.08 229.83 0.22 0.44 423.74

 MEAN 18.08 0.00 -0.02 229.83 -0.08 229.83 0.22 0.40

 HUB 15.21 0.00 -0.02 229.83 -0.08 229.83 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.54 46.36 14.18 406.82 467.33 5.19 473.86 469.24 39.65

 MEAN 57.30 42.30 15.00 357.89 425.40 5.19 473.86 469.24 39.65

 HUB 52.65 37.84 14.81 301.11 378.86 5.19 473.86 469.24 39.65

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 337.22 233.31 243.48 1071.04 0.31 2.33 2.04 9.02

 MEAN 18.01 336.93 230.63 245.62 1068.92 0.32 2.40 2.13 7.35

 HUB 15.22 357.07 256.88 248.01 1066.83 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 404.25 297.50 170.94 0.28 4765.73 0.92 0.88

 MEAN 356.54 276.02 125.91 0.26 4155.01 0.92 0.88 0.88 1.70

 HUB 301.37 251.97 44.48 0.24 3911.75 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.93 1.10 5.54 493.17 1.03 484.07 478.93 28.75

 MEAN 5.85 1.09 5.47 491.23 1.03 482.16 477.93 30.77

 HUB 5.82 1.09 5.39 490.46 1.03 480.27 477.80 32.88

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.78 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 43.20 27.14 23.50 3.64 0.95 0.52 1.63

 HUB 46.01 10.17 6.50 3.67 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 360.3117 231.2743 276.2910 1067.8672 0.3374 -0.1078 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8623 5.4243 481.2441 478.4952 32.0210 39.9316 30.6000 -9.3316

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 268.1864 56.8574 262.0900 1072.9822 0.2499 0.3629 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8569 5.6114 485.8709 477.5199 491.5697 0.0234 0.4591

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 277.8279 0.0000 277.8279 1072.4972 0.2590 0.3510 0.5911

NASA/TM—2013-218094 M–36
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5780 485.4493 477.8435 0.0000 0.0600 0.0646 0.2796

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8328 5.8404 1.0886 491.6170 13.5405 189.4598 1.4687

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 84719.750 0.518 133.360 263986.250 0.223364E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.792 EfDer = 0.975 SH = 0.257960E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.855 2268.543 5.840 491.616 1.000 1.000 0.980

 W Kg/sec = 12.661 Wdry = 27.783 WH2O = 0.072 lbm/sec H2O = 1.295g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.255 2330.192 1.378 0.250 53.432 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53461.438 21834.457 2.726 545.479 200.106 424.468 2.121

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 235.21 -0.08 235.21 0.22 0.43 408.11

 MEAN 17.74 0.00 -0.02 235.21 -0.08 235.21 0.22 0.39

 HUB 15.05 0.00 -0.02 235.21 -0.08 235.21 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.38 46.36 13.02 397.32 461.79 5.65 487.20 478.41 31.77

 MEAN 56.19 43.40 12.79 351.16 422.73 5.65 487.20 478.41 31.77

 HUB 51.72 38.84 12.88 297.94 379.66 5.65 487.20 478.41 31.77

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 330.23 216.93 248.98 1084.56 0.30 2.26 1.98 8.75

 MEAN 17.51 332.06 217.54 250.88 1082.76 0.31 2.34 2.07 6.78

 HUB 14.85 354.37 248.15 252.98 1080.99 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 392.17 304.47 175.24 0.28 4299.07 0.92 0.89

 MEAN 346.57 282.12 129.03 0.26 3809.82 0.92 0.89 0.89 1.64

 HUB 293.98 257.09 45.83 0.24 3686.31 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.38 1.09 5.99 505.20 1.03 496.49 486.58 24.45

 MEAN 6.32 1.08 5.93 503.65 1.02 494.85 485.87 25.82

 HUB 6.30 1.08 5.86 503.26 1.02 493.24 485.99 27.22

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.06 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 40.93 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.45 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 356.8520 218.9676 281.7740 1081.6567 0.3299 -0.1170 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3307 5.8778 493.8797 486.4553 26.8844 37.8509 31.5000 -6.3509

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 278.0768 60.6606 271.3798 1086.0106 0.2561 0.3048 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3276 6.0497 497.8684 485.5909 451.3937 0.0177 0.4286

 

NASA/TM—2013-218094 M–37
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 282.6786 0.0000 282.6786 1085.7709 0.2603 0.3316 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0280 497.6621 485.8881 0.0000 0.0600 0.0501 0.2519

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8557 6.3143 1.0811 504.0338 12.4208 196.2291 1.5212

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 77875.633 0.506 122.586 263263.188 0.290033E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.997 EfDer = 0.986 SH = 0.333324E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.855 2268.543 6.314 504.033 1.000 1.000 0.980

 W Kg/sec = 12.661 Wdry = 27.762 WH2O = 0.093 lbm/sec H2O = 1.763g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.925 2301.311 1.377 0.251 53.456 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50710.867 21827.939 2.738 513.330 187.502 395.845 2.111

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 237.08 -0.08 237.08 0.22 0.41 386.78

 MEAN 16.97 0.00 -0.02 237.08 -0.08 237.08 0.22 0.38

 HUB 14.32 0.00 -0.02 237.08 -0.08 237.08 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.13 46.36 11.77 381.29 449.05 6.11 499.56 486.49 27.06

 MEAN 54.80 43.80 11.00 335.97 411.26 6.11 499.56 486.49 27.06

 HUB 50.10 37.84 12.26 283.49 369.62 6.11 499.56 486.49 27.06

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 318.61 197.46 250.05 1096.58 0.29 2.16 1.89 8.34

 MEAN 16.57 320.57 198.46 251.76 1094.98 0.29 2.24 1.97 6.35

 HUB 13.89 341.75 229.06 253.63 1093.40 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 373.76 305.95 176.31 0.28 3729.58 0.92 0.90

 MEAN 328.11 283.18 129.65 0.26 3290.60 0.92 0.90 0.90 1.59

 HUB 274.98 257.75 45.92 0.24 3182.80 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.81 1.08 6.43 515.79 1.02 507.71 493.19 21.98

 MEAN 6.75 1.07 6.37 514.40 1.02 506.22 492.61 23.01

 HUB 6.74 1.07 6.30 514.06 1.02 504.77 492.75 24.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.30 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.25 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.09 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 340.5900 199.5740 275.9923 1094.1804 0.3113 -0.0937 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7643 6.3316 505.5214 493.1027 23.7177 35.8712 32.4000 -3.4712

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 277.8054 62.3036 270.7288 1097.5115 0.2531 0.2612 2.2705

 

NASA/TM—2013-218094 M–38
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7628 6.4727 508.6103 492.4225 432.2457 0.0136 0.4022

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 275.5558 0.0000 275.5558 1097.6057 0.2511 0.3128 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4669 508.7091 492.6562 0.0000 0.0600 0.0407 0.2469

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8703 6.7520 1.0693 514.7486 10.7183 213.0604 1.6516

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67368.047 0.482 106.046 270253.000 0.371887E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.353 EfDer = 0.994 SH = 0.423964E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.855 2268.543 6.752 514.747 1.000 1.000 0.980

 W Kg/sec = 12.661 Wdry = 27.737 WH2O = 0.118 lbm/sec H2O = 2.353g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.414 2277.233 1.376 0.252 53.486 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48347.055 21820.082 2.875 509.668 177.301 384.739 2.170

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 227.65 -0.08 227.65 0.21 0.39 364.06

 MEAN 15.91 0.00 -0.02 227.65 -0.08 227.65 0.21 0.35

 HUB 13.07 0.00 -0.02 227.65 -0.08 227.65 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.89 47.36 10.53 362.68 428.27 6.56 510.63 493.28 24.24

 MEAN 54.15 44.80 9.35 315.03 388.74 6.56 510.63 493.28 24.24

 HUB 48.67 38.84 9.83 258.74 344.70 6.56 510.63 493.28 24.24

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 303.07 184.37 240.53 1107.32 0.27 2.05 1.78 7.43

 MEAN 15.50 302.58 181.35 242.21 1105.67 0.27 2.13 1.86 5.75

 HUB 12.59 318.70 205.02 244.00 1104.05 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.15 295.00 170.78 0.27 3309.05 0.92 0.91

 MEAN 306.80 272.77 125.46 0.25 2811.66 0.92 0.91 0.91 1.58

 HUB 249.24 247.98 44.22 0.22 2582.19 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.22 1.07 6.86 525.15 1.02 517.85 498.99 20.44

 MEAN 7.15 1.06 6.79 523.58 1.02 516.32 498.33 21.39

 HUB 7.11 1.05 6.72 522.86 1.02 514.80 498.25 22.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.47 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.82 27.38 23.50 3.88 0.93 0.44 1.64

 HUB 40.04 10.27 6.50 3.77 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 331.6776 184.6705 275.5120 1104.3680 0.3003 -0.1752 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1514 6.7247 515.1352 498.9117 22.3070 33.8332 33.0000 -0.8332

 

NASA/TM—2013-218094 M–39
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 282.1103 64.4201 274.6566 1106.9442 0.2549 0.1364 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1501 6.8394 517.5477 498.3431 410.5396 0.0237 0.3739

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 274.4572 0.0000 274.4572 1107.2880 0.2479 0.2965 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8512 517.8788 498.4748 0.0000 0.0600 0.0368 0.1685

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8802 7.1452 1.0582 523.8531 9.1165 234.3813 1.8169

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57465.156 0.456 90.458 284263.063 0.464779E-02

 

Melt Ratio at Stator LE, Throat, TE

0.98646E-02 0.15579E-01 0.37936E-01

 trTOT = 1.1354 Tt4 = 523.8531 T1 = 461.3822

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 391619.66 616.4596 79.9816 1.4798 0.8375 15.6532 1.1354 37.3740

NASA/TM—2013-218094 M–40
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.166 EfDer = 0.965 SH = 0.106771E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.863 2148.455 5.592 471.057 1.000 1.000 0.980

 W Kg/sec = 14.483 Wdry = 31.829 WH2O = 0.034 lbm/sec H2O = 0.541g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.817 2254.434 1.380 0.249 53.383 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60521.504 24990.566 3.557 831.557 233.783 619.754 2.651

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.67 -0.06 174.67 0.17 0.40 405.86

 MEAN 17.06 0.00 -0.02 174.67 -0.06 174.67 0.17 0.35

 HUB 12.51 0.00 -0.02 174.67 -0.06 174.67 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.70 50.47 15.23 386.79 424.46 5.49 468.61 462.45 28.43

 MEAN 61.37 47.20 14.17 319.86 364.50 5.49 468.61 462.45 28.43

 HUB 53.33 38.62 14.71 234.55 292.49 5.49 468.61 462.45 28.43

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 350.87 259.23 236.45 1063.63 0.33 7.29 6.52 16.04

 MEAN 18.04 357.28 265.78 238.78 1061.36 0.34 7.43 6.80 12.53

 HUB 15.00 389.67 305.34 242.09 1058.47 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.79 268.66 127.55 0.25 5349.22 0.92 0.88

 MEAN 338.15 249.50 72.38 0.24 4794.59 0.92 0.88 0.88 1.67

 HUB 281.23 243.29 24.11 0.23 4580.92 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.78 487.14 1.03 477.27 474.64 27.08

 MEAN 6.16 1.10 5.70 485.47 1.03 475.23 473.76 29.17

 HUB 6.13 1.10 5.59 484.83 1.03 472.65 473.79 32.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.63 28.35 24.20 4.15 0.93 0.54 1.80

 MEAN 48.06 16.86 12.70 4.16 0.95 0.48 2.22

 HUB 51.59 -5.69 -9.30 3.61 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.965 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.6875 265.2610 256.0608 1060.9498 0.3475 -0.0413 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1699 5.6821 474.9241 474.2390 30.3650 46.0110 35.4000 -10.6110

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.5764 62.7664 248.7806 1067.1857 0.2404 0.4759 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1618 5.9221 480.5370 473.3848 554.9116 0.0268 0.5651

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.1837 0.0000 255.1837 1067.2202 0.2391 0.4546 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9038 480.5934 473.8968 0.0000 0.0600 0.0721 0.4380

NASA/TM—2013-218094 M–41
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8311 6.1400 1.0979 485.8065 14.7546 174.3226 1.3513

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92124.273 0.616 165.878 326349.719 0.169134E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =13.135 EfDer = 0.973 SH = 0.231060E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.863 2148.455 6.140 485.805 1.000 1.000 0.980

 W Kg/sec = 14.483 Wdry = 31.789 WH2O = 0.074 lbm/sec H2O = 1.234g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.826 2219.998 1.378 0.250 53.423 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57469.355 24978.322 2.729 590.487 216.398 468.502 2.165

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.57 -0.08 233.57 0.22 0.42 398.11

 MEAN 18.08 0.00 -0.02 233.57 -0.08 233.57 0.22 0.39 

 HUB 15.21 0.00 -0.02 233.57 -0.08 233.57 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.78 46.36 12.42 385.29 450.63 5.94 481.45 475.61 38.05 

 MEAN 55.44 42.30 13.14 338.95 411.70 5.94 481.45 475.61 38.05

 HUB 50.69 37.84 12.85 285.17 368.68 5.94 481.45 475.61 38.05

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 324.64 208.52 248.82 1077.64 0.30 2.33 2.04 9.02

 MEAN 18.01 326.65 209.48 250.63 1075.93 0.30 2.40 2.13 7.35

 HUB 15.22 348.69 240.32 252.65 1074.24 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 382.85 303.81 174.34 0.28 4259.53 0.92 0.89

 MEAN 337.66 281.51 128.18 0.26 3774.18 0.92 0.89 0.89 1.61

 HUB 285.41 256.65 45.10 0.24 3659.54 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.68 1.09 6.28 498.56 1.03 490.14 483.68 29.38

 MEAN 6.62 1.08 6.21 497.11 1.02 488.58 482.97 30.98

 HUB 6.60 1.08 6.14 496.76 1.02 487.05 483.09 32.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.96 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 39.89 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.57 10.12 6.50 3.62 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 351.6312 210.0683 281.9855 1074.8132 0.3272 -0.1212 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6277 6.1610 487.6048 483.5496 32.2627 36.6847 30.6000 -6.0847

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.8289 58.2657 268.5816 1079.0328 0.2547 0.2990 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6246 6.3367 491.4452 482.6993 491.5697 0.0172 0.4052

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.4936 0.0000 284.4936 1078.5435 0.2638 0.3059 0.5911

NASA/TM—2013-218094 M–42
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3037 491.0131 483.0205 0.0000 0.0600 0.0490 0.2207

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8533 6.6112 1.0768 497.4730 11.6714 202.0251 1.5661

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73110.016 0.499 131.641 298506.781 0.256096E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.704 EfDer = 0.988 SH = 0.289333E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.863 2148.455 6.611 497.472 1.000 1.000 0.980

 W Kg/sec = 14.483 Wdry = 31.771 WH2O = 0.092 lbm/sec H2O = 1.623g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.382 2193.813 1.378 0.251 53.442 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54723.387 24972.564 2.681 545.479 203.452 424.468 2.086

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.77 -0.08 240.77 0.22 0.41 384.22

 MEAN 17.74 0.00 -0.02 240.77 -0.08 240.77 0.22 0.38

 HUB 15.05 0.00 -0.02 240.77 -0.08 240.77 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.39 46.36 11.03 376.29 446.79 6.39 492.85 483.47 32.02

 MEAN 54.10 43.40 10.70 332.58 410.65 6.39 492.85 483.47 32.02

 HUB 49.54 38.84 10.70 282.17 370.99 6.39 492.85 483.47 32.02

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 319.74 191.15 256.31 1089.00 0.29 2.26 1.98 8.75

 MEAN 17.51 323.71 195.69 257.86 1087.60 0.30 2.34 2.07 6.78

 HUB 14.85 347.77 231.41 259.60 1086.23 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 371.41 313.35 180.26 0.29 3788.36 0.92 0.90

 MEAN 328.23 289.93 132.54 0.27 3427.27 0.92 0.90 0.90 1.55

 HUB 278.42 263.82 47.01 0.24 3437.72 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.12 1.08 6.71 508.79 1.02 500.64 490.27 25.93

 MEAN 7.07 1.07 6.66 507.71 1.02 499.36 489.81 27.02

 HUB 7.07 1.07 6.60 507.75 1.02 498.11 490.16 28.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.72 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 37.19 27.20 23.50 3.70 0.94 0.44 1.62

 HUB 41.71 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 350.3304 196.9705 289.7137 1086.4182 0.3225 -0.1316 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0840 6.5990 498.3061 490.4164 28.1691 34.2110 31.5000 -2.7110

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 287.0500 62.6180 280.1369 1089.9109 0.2634 0.2289 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0825 6.7542 501.5195 489.6862 451.3937 0.0135 0.3697

 

NASA/TM—2013-218094 M–43
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.6534 0.0000 291.6534 1089.6683 0.2677 0.2767 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7332 501.3070 489.9644 0.0000 0.0600 0.0391 0.1806

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8721 7.0714 1.0696 508.0828 10.6129 211.3988 1.6388

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66610.625 0.483 119.938 298781.500 0.319456E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.672 EfDer = 0.997 SH = 0.358773E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.863 2148.455 7.071 508.082 1.000 1.000 0.980

 W Kg/sec = 14.483 Wdry = 31.748 WH2O = 0.114 lbm/sec H2O = 2.106g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.554 2170.786 1.377 0.251 53.465 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52287.801 24965.691 2.669 513.330 192.314 395.845 2.058

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.46 -0.08 244.46 0.22 0.40 364.84

 MEAN 16.97 0.00 -0.02 244.46 -0.08 244.46 0.22 0.37

 HUB 14.32 0.00 -0.02 244.46 -0.08 244.46 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.91 46.36 9.55 361.10 436.14 6.83 503.33 490.40 28.15

 MEAN 52.47 43.80 8.67 318.18 401.31 6.83 503.33 490.40 28.15

 HUB 47.69 37.84 9.85 268.48 363.16 6.83 503.33 490.40 28.15

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 310.65 171.12 259.27 1099.04 0.28 2.16 1.89 8.34

 MEAN 16.57 314.74 176.44 260.64 1097.83 0.29 2.24 1.97 6.35

 HUB 13.89 337.68 212.85 262.14 1096.65 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 353.98 317.26 182.86 0.29 3232.38 0.92 0.91

 MEAN 310.74 293.20 134.30 0.27 2925.69 0.92 0.91 0.91 1.49

 HUB 260.42 266.42 47.57 0.24 2957.75 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.53 1.06 7.13 517.72 1.02 510.05 495.95 23.83

 MEAN 7.48 1.06 7.08 516.81 1.02 508.93 495.59 24.66

 HUB 7.49 1.06 7.02 516.90 1.02 507.83 495.96 25.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.43 35.19 31.50 3.69 0.93 0.41 1.40

 MEAN 34.10 27.26 23.50 3.76 0.93 0.40 1.62

 HUB 39.08 10.28 6.50 3.78 0.93 0.42 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 336.4166 177.4300 285.8229 1096.9575 0.3067 -0.1062 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4966 7.0307 508.1457 496.1091 25.4461 31.8307 32.4000 0.5693

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.7728 64.7633 281.4168 1099.5052 0.2626 0.1770 2.2705

 

NASA/TM—2013-218094 M–44
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4957 7.1504 510.5136 495.5692 432.2457 0.0121 0.3390

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.3589 0.0000 286.3589 1099.6133 0.2604 0.2475 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1460 510.6240 495.7659 0.0000 0.0600 0.0367 0.1668

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8788 7.4852 1.0585 517.1412 9.0614 232.2558 1.8004

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57000.020 0.455 102.634 307734.594 0.393299E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.818 EfDer = 1.000 SH = 0.438789E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.863 2148.455 7.485 517.140 1.000 1.000 0.980

 W Kg/sec = 14.483 Wdry = 31.723 WH2O = 0.140 lbm/sec H2O = 2.682g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.480 2151.690 1.376 0.252 53.491 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50199.961 24957.754 2.779 509.668 183.385 384.739 2.098

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.38 -0.08 236.38 0.21 0.38 343.99

 MEAN 15.91 0.00 -0.02 236.38 -0.08 236.38 0.21 0.35

 HUB 13.07 0.00 -0.02 236.38 -0.08 236.38 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.47 47.36 8.11 343.48 417.02 7.25 512.71 496.19 25.71

 MEAN 51.62 44.80 6.82 298.35 380.71 7.25 512.71 496.19 25.71

 HUB 46.04 38.84 7.20 245.05 340.53 7.25 512.71 496.19 25.71

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 296.61 157.84 251.12 1108.06 0.27 2.05 1.78 7.43

 MEAN 15.50 298.67 159.57 252.47 1106.81 0.27 2.13 1.86 5.75

 HUB 12.59 317.00 189.77 253.93 1105.59 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 336.35 308.11 178.51 0.28 2833.15 0.92 0.91 

 MEAN 290.56 284.43 130.99 0.26 2474.24 0.92 0.91 0.91 1.47

 HUB 236.05 258.11 46.28 0.23 2390.24 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.90 1.06 7.52 525.56 1.02 518.58 500.84 22.31

 MEAN 7.85 1.05 7.47 524.50 1.01 517.42 500.42 23.09

 HUB 7.84 1.05 7.41 524.25 1.01 516.27 500.56 23.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.15 35.41 31.50 3.91 0.93 0.40 1.40

 MEAN 32.29 27.42 23.50 3.92 0.93 0.38 1.64

 HUB 36.77 10.33 6.50 3.83 0.93 0.38 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 330.0902 162.4953 287.3235 1105.3966 0.2986 -0.1941 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8540 7.3906 516.1259 501.0118 24.0957 29.4903 33.0000 3.5097

 

NASA/TM—2013-218094 M–45
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.2907 67.4299 287.4888 1107.2361 0.2667 0.0311 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8516 7.4789 517.8488 500.5839 410.5396 0.0261 0.3079

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.2354 0.0000 287.2354 1107.6143 0.2593 0.2218 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4934 518.2098 500.6347 0.0000 0.0600 0.0408 0.0677

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8778 7.8458 1.0482 524.7513 7.6298 258.4245 2.0033

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 48111.930 0.425 86.630 324572.344 0.468350E-02

 

Melt Ratio at Stator LE, Throat, TE

0.46533E-01 0.56821E-01 0.90234E-01

 trTOT = 1.1140 Tt4 = 524.7513 T1 = 471.0566

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 336956.88 606.7212 79.8175 1.4030 0.8525 14.1656 1.1140 37.3740

NASA/TM—2013-218094 M–46
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.342 EfDer = 0.994 SH = 0.135055E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.140 1969.919 6.513 481.855 1.000 1.000 0.980

 W Kg/sec = 18.245 Wdry = 40.085 WH2O = 0.054 lbm/sec H2O = 0.777g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.322 2043.816 1.380 0.249 53.392 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 67166.758 31478.881 3.251 831.557 255.818 619.754 2.423

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 193.85 -0.07 193.85 0.18 0.38 367.94

 MEAN 17.06 0.00 -0.02 193.85 -0.07 193.85 0.18 0.33

 HUB 12.51 0.00 -0.02 193.85 -0.07 193.85 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.34 50.47 10.87 354.65 404.23 6.37 478.85 471.04 26.62

 MEAN 56.54 47.20 9.34 293.28 351.61 6.37 478.85 471.04 26.62

 HUB 47.98 38.62 9.36 215.06 289.58 6.37 478.85 471.04 26.62

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 339.55 212.15 265.11 1071.76 0.32 7.29 6.52 16.04

 MEAN 18.04 352.07 229.55 266.94 1070.27 0.33 7.43 6.80 12.53

 HUB 15.00 392.61 285.02 270.01 1068.00 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.65 300.98 142.49 0.28 4378.07 0.92 0.91

 MEAN 310.05 278.82 80.51 0.26 4141.25 0.92 0.91 0.91 1.42

 HUB 257.86 271.37 27.16 0.25 4276.09 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.60 493.91 1.03 484.68 480.31 27.36

 MEAN 7.04 1.08 6.54 493.26 1.02 483.33 480.10 28.67

 HUB 7.05 1.08 6.43 493.63 1.02 481.28 480.82 30.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.67 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.69 16.78 12.70 4.08 0.93 0.36 2.22

 HUB 46.55 -5.74 -9.30 3.56 0.93 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 366.8634 229.1008 286.5337 1069.6538 0.3430 -0.0590 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0478 6.5045 482.8311 480.6245 29.9705 38.6444 35.4000 -3.2444

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 289.3788 70.7909 280.5865 1074.1375 0.2694 0.3405 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0453 6.7036 486.8987 479.9705 554.9116 0.0148 0.4402

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 287.2808 0.0000 287.2808 1074.2238 0.2674 0.3519 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6957 486.9954 480.4182 0.0000 0.0600 0.0402 0.3256

NASA/TM—2013-218094 M–47
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8737 7.0318 1.0797 493.5953 11.7434 199.6584 1.5477

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73404.313 0.584 166.505 405351.500 0.197496E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.510 EfDer = 0.999 SH = 0.254525E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.140 1969.919 7.032 493.593 1.000 1.000 0.980

 W Kg/sec = 18.245 Wdry = 40.038 WH2O = 0.102 lbm/sec H2O = 1.523g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.856 2019.394 1.378 0.250 53.431 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64615.262 31464.045 2.461 590.487 239.977 468.502 1.952

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.61 -0.09 262.61 0.24 0.41 362.13

 MEAN 18.08 0.00 -0.02 262.61 -0.09 262.61 0.24 0.38

 HUB 15.21 0.00 -0.02 262.61 -0.09 262.61 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.38 46.36 7.02 353.27 440.26 6.75 488.09 481.88 36.10

 MEAN 49.81 42.30 7.51 310.78 406.95 6.75 488.09 481.88 36.10

 HUB 44.89 37.84 7.05 261.47 370.65 6.75 488.09 481.88 36.10

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.45 152.72 282.86 1081.70 0.30 2.33 2.04 9.02

 MEAN 18.01 328.00 164.15 283.97 1080.84 0.30 2.40 2.13 7.35

 HUB 15.22 354.54 210.54 285.26 1080.00 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.04 345.45 198.32 0.32 3120.39 0.92 0.91

 MEAN 309.61 319.06 145.46 0.30 2957.93 0.92 0.91 0.91 1.38

 HUB 261.70 289.81 51.15 0.27 3206.50 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.45 1.06 7.01 502.15 1.02 493.91 487.31 30.82

 MEAN 7.42 1.06 6.97 501.71 1.02 493.12 487.17 31.63

 HUB 7.46 1.06 6.93 502.39 1.02 492.36 487.88 32.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.37 35.04 31.50 3.54 0.93 0.34 1.40

 MEAN 30.03 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.43 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.9833 164.6087 320.1437 1079.3026 0.3335 -0.1625 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4387 6.8953 491.7464 487.8701 33.3301 27.2109 30.6000 3.3891

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 314.3321 66.6406 307.1867 1081.9917 0.2905 0.1032 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4365 7.0197 494.2019 487.3002 491.5697 0.0145 0.2598

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 325.5053 0.0000 325.5053 1081.3575 0.3010 0.1534 0.5911

NASA/TM—2013-218094 M–48
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9786 493.6318 487.6304 0.0000 0.0600 0.0405 0.0164

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8722 7.4242 1.0558 502.0818 8.4898 249.2169 1.9319

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 53224.297 0.432 120.730 373808.156 0.276669E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.607 EfDer = 0.995 SH = 0.303793E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.140 1969.919 7.424 502.081 1.000 1.000 0.980

 W Kg/sec = 18.245 Wdry = 40.018 WH2O = 0.122 lbm/sec H2O = 1.882g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.193 2002.254 1.377 0.251 53.447 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62410.500 31457.908 2.379 545.479 229.316 424.468 1.851

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 274.59 -0.09 274.59 0.25 0.41 350.67

 MEAN 17.74 0.00 -0.02 274.59 -0.09 274.59 0.25 0.38

 HUB 15.05 0.00 -0.02 274.59 -0.09 274.59 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.49 46.36 5.13 345.02 441.02 7.11 496.07 487.75 32.88

 MEAN 48.01 43.40 4.61 304.94 410.42 7.11 496.07 487.75 32.88

 HUB 43.31 38.84 4.47 258.72 377.34 7.11 496.07 487.75 32.88

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 324.02 131.59 296.09 1089.19 0.30 2.26 1.98 8.75

 MEAN 17.51 331.50 147.69 296.79 1088.70 0.30 2.34 2.07 6.78

 HUB 14.85 359.04 200.76 297.67 1088.23 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 340.55 362.40 208.96 0.33 2608.75 0.92 0.91

 MEAN 300.95 334.02 153.26 0.31 2587.19 0.92 0.91 0.91 1.32

 HUB 255.28 302.62 54.52 0.28 2982.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.78 1.05 7.33 509.23 1.01 500.86 492.16 29.15

 MEAN 7.78 1.05 7.30 509.17 1.01 500.41 492.23 29.57

 HUB 7.83 1.06 7.27 510.25 1.02 499.98 493.15 29.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.96 35.21 31.50 3.71 0.93 0.28 1.40

 MEAN 26.46 27.31 23.50 3.81 0.92 0.30 1.62

 HUB 34.00 10.38 6.50 3.88 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.8340 148.6575 334.2686 1087.0143 0.3365 -0.1752 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7929 7.2141 498.8888 492.9915 31.2416 23.9759 31.5000 7.5241

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 333.8533 72.8279 325.8130 1088.9530 0.3066 0.0081 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7880 7.3040 500.6711 492.5599 451.3937 0.0199 0.2178

 

NASA/TM—2013-218094 M–49
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 339.6186 0.0000 339.6186 1088.6095 0.3120 0.0984 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2711 500.3623 492.8079 0.0000 0.0600 0.0553 -0.0580

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8445 7.7704 1.0466 509.5464 7.4664 269.3801 2.0882

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46882.770 0.404 106.346 376528.656 0.327613E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 2.032 EfDer = 0.977 SH = 0.356869E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.140 1969.919 7.770 509.545 1.000 1.000 0.980

 W Kg/sec = 18.245 Wdry = 39.996 WH2O = 0.143 lbm/sec H2O = 2.275g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.263 1987.534 1.377 0.251 53.464 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 60634.242 31451.291 2.325 513.330 220.797 395.845 1.793

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 283.48 -0.10 283.48 0.26 0.40 334.05

 MEAN 16.97 0.00 -0.02 283.48 -0.10 283.48 0.26 0.37

 HUB 14.32 0.00 -0.02 283.48 -0.10 283.48 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.44 46.36 3.08 331.09 435.95 7.42 503.15 492.79 30.61

 MEAN 45.83 43.80 2.03 291.74 406.85 7.42 503.15 492.79 30.61

 HUB 40.98 37.84 3.14 246.17 375.51 7.42 503.15 492.79 30.61

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.60 108.28 304.95 1095.54 0.30 2.16 1.89 8.34

 MEAN 16.57 330.46 126.40 305.33 1095.30 0.30 2.24 1.97 6.35

 HUB 13.89 356.10 182.24 305.94 1095.08 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.56 373.86 216.28 0.34 2046.22 0.92 0.89

 MEAN 284.92 344.03 158.52 0.31 2096.63 0.92 0.89 0.89 1.27

 HUB 238.78 311.12 56.54 0.28 2532.75 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.05 1.04 7.59 515.14 1.01 506.81 496.20 28.16

 MEAN 8.06 1.04 7.57 515.28 1.01 506.59 496.36 28.34

 HUB 8.12 1.05 7.56 516.47 1.01 506.38 497.29 28.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.55 35.35 31.50 3.85 0.93 0.23 1.40

 MEAN 22.49 27.44 23.50 3.94 0.91 0.25 1.62

 HUB 30.78 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.8789 127.1128 335.6135 1093.9755 0.3281 -0.1431 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0726 7.5019 505.3895 497.0214 29.5944 20.7441 32.4000 11.6559

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 341.9265 76.6841 333.2166 1094.9951 0.3123 -0.0544 2.2705

 

NASA/TM—2013-218094 M–50
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0638 7.5449 506.3347 496.7977 432.2457 0.0276 0.1813

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 339.6524 0.0000 339.6524 1095.1234 0.3101 0.0450 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5276 506.4584 496.8986 0.0000 0.0600 0.0785 -0.0887

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7792 8.0380 1.0344 515.6290 6.0840 309.2015 2.3969

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38266.465 0.363 86.801 390163.125 0.381880E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.354 EfDer = 0.944 SH = 0.413676E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 40.140 1969.919 8.038 515.628 1.000 1.000 0.980

 W Kg/sec = 18.245 Wdry = 39.974 WH2O = 0.166 lbm/sec H2O = 2.699g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.190 1975.777 1.376 0.252 53.482 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59250.277 31444.191 2.373 509.668 214.791 384.739 1.791 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 279.00 -0.10 279.00 0.25 0.38 315.86

 MEAN 15.91 0.00 -0.02 279.00 -0.10 279.00 0.25 0.36

 HUB 13.07 0.00 -0.02 279.00 -0.10 279.00 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.47 47.36 1.11 314.94 420.82 7.69 509.45 496.80 29.00

 MEAN 44.45 44.80 -0.35 273.56 390.80 7.69 509.45 496.80 29.00

 HUB 38.86 38.84 0.02 224.68 358.28 7.69 509.45 496.80 29.00

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.85 92.98 300.81 1101.37 0.29 2.05 1.78 7.43

 MEAN 15.50 320.18 108.68 301.17 1101.13 0.29 2.13 1.86 5.75

 HUB 12.59 341.68 160.24 301.78 1100.89 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 308.40 369.99 215.43 0.34 1669.77 0.92 0.86

 MEAN 266.42 339.98 157.74 0.31 1685.76 0.92 0.86 0.86 1.24

 HUB 216.43 306.96 56.19 0.28 2018.69 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.26 1.03 7.82 520.18 1.01 512.31 499.55 27.28

 MEAN 8.27 1.03 7.80 520.23 1.01 512.09 499.65 27.46

 HUB 8.31 1.03 7.78 521.14 1.01 511.87 500.37 27.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 17.18 35.61 31.50 4.11 0.93 0.20 1.40

 MEAN 19.84 27.64 23.50 4.14 0.90 0.21 1.64

 HUB 27.97 10.55 6.50 4.05 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.944 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.3752 110.6694 344.0121 1099.0164 0.3288 -0.2471 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2720 7.6848 510.1505 500.4758 29.2310 17.8331 33.0000 15.1669

 

NASA/TM—2013-218094 M–51
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 357.2191 81.5713 347.7809 1099.2708 0.3250 -0.2639 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2472 7.6747 510.3874 500.4036 410.5396 0.0717 0.1491

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 347.5238 0.0000 347.5238 1099.8485 0.3160 0.0109 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6913 510.9273 500.3711 0.0000 0.0600 0.1017 -0.2295

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6927 8.2328 1.0242 520.5114 4.8885 359.6833 2.7882

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30800.725 0.324 69.866 413488.031 0.437633E-02

 

Melt Ratio at Stator LE, Throat, TE

0.16851E-01 0.19118E-01 0.28124E-01

 trTOT = 1.0802 Tt4 = 520.5114 T1 = 481.8552

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 242578.56 550.2485 87.3220 1.2641 0.8262 9.3417 1.0802 37.3740

NASA/TM—2013-218094 M–52
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.734 EfDer = 0.999 SH = 0.186977E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.560 1802.713 7.939 496.977 1.000 1.000 0.980

 W Kg/sec = 22.527 Wdry = 49.467 WH2O = 0.093 lbm/sec H2O = 1.270g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 89.822 1841.680 1.379 0.250 53.409 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70259.188 38858.402 3.159 831.557 263.238 619.754 2.354

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.78 -0.07 202.78 0.19 0.35 331.55

 MEAN 17.06 0.00 -0.02 202.78 -0.07 202.78 0.19 0.31

 HUB 12.51 0.00 -0.02 202.78 -0.07 202.78 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.01 50.47 7.54 324.54 382.74 7.75 493.69 482.59 24.27

 MEAN 52.93 47.20 5.73 268.38 336.43 7.75 493.69 482.59 24.27

 HUB 44.15 38.62 5.53 196.80 282.63 7.75 493.69 482.59 24.27

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.66 173.75 280.15 1085.49 0.30 7.29 6.52 16.04

 MEAN 18.04 344.39 198.63 281.34 1084.62 0.32 7.43 6.80 12.53

 HUB 15.00 387.86 264.27 283.89 1082.89 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.54 318.16 150.80 0.29 3585.87 0.92 0.91

 MEAN 283.74 293.93 85.11 0.27 3583.70 0.92 0.91 0.91 1.28

 HUB 235.97 285.30 28.29 0.26 3964.89 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.91 506.00 1.02 497.31 489.69 26.23

 MEAN 8.43 1.06 7.87 505.99 1.02 496.51 489.86 26.91

 HUB 8.48 1.07 7.77 506.95 1.02 494.92 490.94 28.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.81 28.29 24.20 4.09 0.93 0.29 1.80

 MEAN 35.22 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.95 -5.69 -9.30 3.61 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.3868 198.2447 302.1581 1083.8682 0.3334 -0.0732 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4406 7.8243 495.8839 490.4179 28.1529 33.2687 35.4000 2.1313

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.1950 75.1493 297.8613 1087.0133 0.2826 0.2325 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4385 7.9898 498.7771 489.9331 554.9116 0.0136 0.3525

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 304.8922 0.0000 304.8922 1087.1208 0.2805 0.2569 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9826 498.8901 490.3451 0.0000 0.0600 0.0382 0.2205

NASA/TM—2013-218094 M–53
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8727 8.4239 1.0611 506.3093 9.3345 221.6512 1.7182

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58463.090 0.555 163.735 489634.719 0.256622E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.306 EfDer = 0.988 SH = 0.317396E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.560 1802.713 8.424 506.307 1.000 1.000 0.980

 W Kg/sec = 22.527 Wdry = 49.402 WH2O = 0.157 lbm/sec H2O = 2.211g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 85.445 1824.638 1.377 0.251 53.451 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 68535.438 38838.367 2.356 590.487 250.601 468.502 1.870

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.55 -0.10 278.55 0.26 0.39 327.21

 MEAN 18.08 0.00 -0.02 278.55 -0.10 278.55 0.26 0.37

 HUB 15.21 0.00 -0.02 278.55 -0.10 278.55 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.26 46.36 2.90 323.29 426.81 8.05 500.13 491.69 33.21

 MEAN 45.61 42.30 3.31 284.40 398.15 8.05 500.13 491.69 33.21

 HUB 40.67 37.84 2.83 239.28 367.27 8.05 500.13 491.69 33.21

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.08 107.72 303.53 1092.07 0.29 2.33 2.04 9.02

 MEAN 18.01 329.32 127.05 303.83 1091.90 0.30 2.40 2.13 7.35

 HUB 15.22 355.76 184.24 304.33 1091.74 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.24 371.11 213.52 0.34 2201.58 0.92 0.90

 MEAN 283.33 341.66 156.27 0.31 2289.92 0.92 0.90 0.90 1.25

 HUB 239.48 309.30 55.24 0.28 2806.18 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.23 511.82 1.01 503.56 495.23 30.74

 MEAN 8.74 1.04 8.22 512.04 1.01 503.41 495.44 30.88

 HUB 8.82 1.05 8.20 513.34 1.01 503.26 496.44 31.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.54 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.69 27.22 23.50 3.72 0.92 0.24 1.63

 HUB 31.19 10.29 6.50 3.79 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.9027 127.4076 343.0045 1090.0734 0.3357 -0.1930 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7579 8.1108 501.7441 496.2296 32.7355 20.3773 30.6000 10.2227

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 338.7352 71.8143 331.0351 1091.7266 0.3103 -0.0391 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7496 8.1934 503.2683 495.8481 491.5697 0.0251 0.1645

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 351.3958 0.0000 351.3958 1090.9663 0.3221 0.0286 0.5911

NASA/TM—2013-218094 M–54
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1293 502.5735 496.1924 0.0000 0.0600 0.0697 -0.1559

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8031 8.7251 1.0358 512.4006 6.0935 300.7329 2.3313

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38282.043 0.371 107.215 454294.906 0.340171E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.060 EfDer = 0.949 SH = 0.366637E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.560 1802.713 8.725 512.400 1.000 1.000 0.980

 W Kg/sec = 22.527 Wdry = 49.378 WH2O = 0.182 lbm/sec H2O = 2.603g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.989 1813.760 1.377 0.251 53.467 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67237.391 38830.781 2.240 545.479 243.480 424.468 1.743 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 295.82 -0.10 295.82 0.27 0.40 317.66

 MEAN 17.74 0.00 -0.02 295.82 -0.10 295.82 0.27 0.37

 HUB 15.05 0.00 -0.02 295.82 -0.10 295.82 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.87 46.36 0.51 315.73 432.74 8.30 505.44 496.06 32.24

 MEAN 43.34 43.40 -0.06 279.06 406.74 8.30 505.44 496.06 32.24

 HUB 38.68 38.84 -0.16 236.76 378.97 8.30 505.44 496.06 32.24

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.59 82.58 323.21 1096.40 0.30 2.26 1.98 8.75

 MEAN 17.51 340.43 107.66 322.96 1096.68 0.31 2.34 2.07 6.78

 HUB 14.85 366.70 173.51 323.05 1096.95 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 311.64 396.15 229.07 0.36 1637.93 0.92 0.87

 MEAN 275.41 363.93 167.75 0.33 1886.48 0.92 0.87 0.87 1.19

 HUB 233.61 328.59 60.11 0.30 2578.09 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.95 1.03 8.40 516.50 1.01 507.65 498.76 30.91

 MEAN 8.98 1.03 8.41 517.12 1.01 507.90 499.15 30.66

 HUB 9.08 1.04 8.41 518.85 1.01 508.16 500.35 30.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.33 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.44 27.45 23.50 3.95 0.90 0.19 1.62

 HUB 28.24 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.949 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.2576 108.3617 364.4909 1094.5944 0.3474 -0.2074 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9975 8.2881 505.9953 500.0504 32.6768 16.5570 31.5000 14.9430

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 366.3336 79.9132 357.5111 1095.4879 0.3344 -0.1444 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9812 8.3227 506.8222 499.8265 451.3937 0.0373 0.1200

 

NASA/TM—2013-218094 M–55
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 373.5992 0.0000 373.5992 1095.0221 0.3412 -0.0361 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2625 506.3958 500.0617 0.0000 0.0600 0.1002 -0.2456

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6839 8.9438 1.0251 517.4873 5.0876 340.6479 2.6407

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 32011.021 0.330 89.652 460067.813 0.388910E-02

 

Melt Ratio at Stator LE, Throat, TE

0.59957E-03 0.59957E-03 0.59957E-03

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.132 EfDer = 0.891 SH = 0.414452E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.560 1802.713 8.944 517.486 1.000 1.000 0.980

 W Kg/sec = 22.527 Wdry = 49.354 WH2O = 0.205 lbm/sec H2O = 2.975g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.361 1804.824 1.376 0.252 53.483 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66490.844 38823.406 2.150 513.330 238.774 395.845 1.658

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 310.86 -0.11 310.86 0.28 0.40 303.34

 MEAN 16.97 0.00 -0.02 310.86 -0.11 310.86 0.28 0.37

 HUB 14.32 0.00 -0.02 310.86 -0.11 310.86 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.28 46.36 -2.08 302.99 434.17 8.47 509.81 499.66 31.55

 MEAN 40.67 43.80 -3.13 266.98 409.84 8.47 509.81 499.66 31.55

 HUB 35.94 37.84 -1.90 225.28 383.97 8.47 509.81 499.66 31.55

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 343.48 55.41 338.98 1099.65 0.31 2.16 1.89 8.34

 MEAN 16.57 348.60 83.97 338.33 1100.27 0.32 2.24 1.97 6.35

 HUB 13.89 372.03 155.06 338.17 1100.88 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 297.01 416.27 241.60 0.38 1048.23 0.92 0.82

 MEAN 260.73 381.73 176.76 0.35 1393.54 0.92 0.82 0.82 1.14

 HUB 218.51 344.07 63.45 0.31 2155.36 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.08 1.02 8.50 520.10 1.01 510.74 501.52 31.23

 MEAN 9.12 1.02 8.52 520.96 1.01 511.32 501.97 30.66

 HUB 9.22 1.03 8.53 522.87 1.01 511.88 503.19 30.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.28 35.48 31.50 3.98 0.93 0.09 1.40

 MEAN 13.94 27.58 23.50 4.08 0.89 0.13 1.62

 HUB 24.63 10.63 6.50 4.13 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.891 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.1612 84.4429 372.7152 1098.5358 0.3479 -0.1703 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1366 8.4146 509.7174 502.7592 32.2632 12.7655 32.4000 19.6345

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 382.2050 85.7174 372.4691 1098.5321 0.3479 -0.1994 2.2705

 

NASA/TM—2013-218094 M–56
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1126 8.3922 509.7138 502.7531 432.2457 0.0482 0.0837

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 380.6141 0.0000 380.6141 1098.6300 0.3464 -0.0876 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3514 509.8062 502.7459 0.0000 0.0600 0.1294 -0.2646

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4863 9.0618 1.0132 521.3029 3.8245 419.1606 3.2493

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 24097.242 0.273 67.488 479330.313 0.431394E-02

 

Melt Ratio at Stator LE, Throat, TE

0.37744E-01 0.41741E-01 0.54528E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.984 EfDer = 0.828 SH = 0.451319E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.560 1802.713 9.062 521.299 1.000 1.000 0.980

 W Kg/sec = 22.527 Wdry = 49.336 WH2O = 0.224 lbm/sec H2O = 3.259g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.597 1798.207 1.375 0.252 53.495 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66111.844 38817.711 2.154 509.668 236.587 384.739 1.626

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 311.31 -0.11 311.31 0.28 0.38 287.47

 MEAN 15.91 0.00 -0.02 311.31 -0.11 311.31 0.28 0.36

 HUB 13.07 0.00 -0.02 311.31 -0.11 311.31 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.80 47.36 -4.56 288.20 424.31 8.58 513.61 502.03 30.27

 MEAN 38.82 44.80 -5.98 250.34 399.55 8.58 513.61 502.03 30.27

 HUB 33.46 38.84 -5.38 205.61 373.14 8.58 513.61 502.03 30.27

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 342.08 37.38 340.03 1102.76 0.31 2.05 1.78 7.43

 MEAN 15.50 345.51 64.83 339.37 1103.46 0.31 2.13 1.86 5.75

 HUB 12.59 364.68 133.77 339.26 1104.12 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.23 419.01 244.84 0.38 672.61 0.92 0.76

 MEAN 243.80 383.67 178.98 0.35 1006.35 0.92 0.76 0.76 1.11

 HUB 198.06 345.30 64.29 0.31 1685.60 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.14 1.01 8.56 522.97 1.00 513.69 503.36 30.56

 MEAN 9.18 1.01 8.59 523.80 1.00 514.34 503.76 29.94

 HUB 9.27 1.02 8.60 525.50 1.01 514.95 504.79 29.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.27 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.81 27.81 23.50 4.31 0.87 0.09 1.64

 HUB 21.52 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.828 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 394.6511 66.0142 389.0907 1100.6558 0.3586 -0.2825 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1852 8.4168 511.7405 504.8223 32.3752 9.6293 33.0000 23.3707

 

NASA/TM—2013-218094 M–57
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 407.5116 93.0556 396.7447 1099.7764 0.3705 -0.4384 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1296 8.3166 510.9206 505.0247 410.5396 0.1108 0.0564

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 396.2725 0.0000 396.2725 1100.5399 0.3601 -0.0987 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3410 511.6303 504.8395 0.0000 0.0600 0.1443 -0.3985

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2666 9.1091 1.0052 524.0796 2.7927 528.7075 4.0985

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17614.361 0.221 49.332 510293.469 0.464989E-02

 

Melt Ratio at Stator LE, Throat, TE

0.12035E+00 0.12661E+00 0.14481E+00

 trTOT = 1.0545 Tt4 = 524.0796 T1 = 496.9769

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 170467.77 477.4229 89.8218 1.1474 0.7025 5.7342 1.0545 37.3740

NASA/TM—2013-218094 M–58
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 02-15-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.926 EfDer = 1.000 SH = 0.259203E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.987 1583.382 9.337 510.164 1.000 1.000 0.980

 W Kg/sec = 21.812 Wdry = 47.863 WH2O = 0.124 lbm/sec H2O = 2.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.925 1596.573 1.378 0.250 53.432 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59081.984 37614.871 3.785 831.557 219.685 619.754 2.821 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 170.52 -0.06 170.52 0.16 0.30 287.42

 MEAN 17.06 0.00 -0.02 170.52 -0.06 170.52 0.16 0.27

 HUB 12.51 0.00 -0.02 170.52 -0.06 170.52 0.16 0.22

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.12 50.47 8.65 285.06 332.22 9.18 507.85 492.44 23.03

 MEAN 54.13 47.20 6.93 235.73 290.99 9.18 507.85 492.44 23.03

 HUB 45.40 38.62 6.78 172.86 242.85 9.18 507.85 492.44 23.03

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 284.18 158.20 236.07 1100.08 0.26 7.29 6.52 16.04

 MEAN 18.04 296.16 177.75 236.89 1099.35 0.27 7.43 6.80 12.53

 HUB 15.00 332.12 231.15 238.48 1098.02 0.30 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 285.06 267.99 126.85 0.24 3264.95 0.92 0.91

 MEAN 249.21 247.43 71.46 0.23 3206.94 0.92 0.91 0.91 1.32

 HUB 207.26 239.67 23.89 0.22 3467.99 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.78 1.05 9.35 517.36 1.01 510.92 498.24 25.16

 MEAN 9.78 1.05 9.30 517.23 1.01 510.23 498.30 25.68

 HUB 9.81 1.05 9.22 517.81 1.01 509.01 499.02 26.64

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.83 28.25 24.20 4.05 0.93 0.33 1.80

 MEAN 36.88 16.79 12.70 4.09 0.93 0.29 2.22

 HUB 44.11 -5.72 -9.30 3.58 0.93 0.18 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 309.8773 177.4065 254.0687 1098.8041 0.2820 -0.0684 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7856 9.2679 509.8144 498.7571 26.6210 34.9251 35.4000 0.4749

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 259.1602 63.3985 251.2859 1101.2593 0.2353 0.2616 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7850 9.4202 512.1082 498.3720 554.9116 0.0111 0.3749

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.1295 0.0000 257.1295 1101.3135 0.2335 0.2824 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4141 512.1731 498.7340 0.0000 0.0600 0.0367 0.2494

NASA/TM—2013-218094 M–59
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 9.7722 1.0466 517.4351 7.2998 214.2408 1.6608

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45844.344 0.564 124.321 462566.313 0.343411E-02

 

Melt Ratio at Stator LE, Throat, TE

0.33204E-01 0.49243E-01 0.10520E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.410 EfDer = 0.995 SH = 0.400283E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.987 1583.382 9.772 517.423 1.000 1.000 0.980

 W Kg/sec = 21.812 Wdry = 47.795 WH2O = 0.192 lbm/sec H2O = 3.194g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.098 1585.316 1.376 0.252 53.478 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57917.383 37593.836 2.791 590.487 211.569 468.502 2.214

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 235.39 -0.08 235.39 0.21 0.33 284.29

 MEAN 18.08 0.00 -0.02 235.39 -0.08 235.39 0.21 0.31

 HUB 15.21 0.00 -0.02 235.39 -0.08 235.39 0.21 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 50.35 46.36 3.99 283.95 368.90 9.47 513.02 499.83 30.28

 MEAN 46.71 42.30 4.41 249.80 343.29 9.47 513.02 499.83 30.28

 HUB 41.77 37.84 3.93 210.17 315.62 9.47 513.02 499.83 30.28

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 276.46 101.62 257.11 1105.19 0.25 2.33 2.04 9.02

 MEAN 18.01 282.63 116.73 257.40 1104.96 0.26 2.40 2.13 7.35

 HUB 15.22 305.47 163.84 257.82 1104.74 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.16 314.16 180.54 0.28 2076.72 0.92 0.91

 MEAN 248.85 289.33 132.13 0.26 2103.73 0.92 0.91 0.91 1.28

 HUB 210.35 261.98 46.51 0.24 2495.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.06 1.03 9.64 521.97 1.01 515.90 502.60 28.32

 MEAN 10.07 1.03 9.62 522.03 1.01 515.69 502.70 28.49

 HUB 10.12 1.04 9.61 522.89 1.01 515.48 503.39 28.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 21.57 35.08 31.50 3.58 0.93 0.25 1.40

 MEAN 24.39 27.17 23.50 3.67 0.92 0.26 1.63

 HUB 32.44 10.23 6.50 3.73 0.92 0.30 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 312.4315 117.0555 289.6747 1103.7185 0.2831 -0.1822 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0777 9.5411 514.5419 503.2419 29.5627 22.0033 30.6000 8.5967

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 286.4012 60.7191 279.8908 1105.0374 0.2592 -0.0053 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0739 9.6209 515.7733 502.9241 491.5697 0.0184 0.1856

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.4303 0.0000 296.4303 1104.5154 0.2684 0.0568 0.5911

NASA/TM—2013-218094 M–60
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5716 515.2906 503.1220 0.0000 0.0600 0.0607 -0.1127

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8343 10.0545 1.0289 522.2661 4.8743 286.5204 2.2211

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30702.379 0.386 83.259 428762.063 0.416443E-02

 

Melt Ratio at Stator LE, Throat, TE

0.22387E+00 0.23950E+00 0.28440E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.959 EfDer = 0.964 SH = 0.432988E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.987 1583.382 10.054 522.258 1.000 1.000 0.980

 W Kg/sec = 21.812 Wdry = 47.780 WH2O = 0.208 lbm/sec H2O = 3.512g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.400 1577.967 1.376 0.252 53.489 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56990.090 37588.949 2.640 545.479 206.635 424.468 2.054

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.74 -0.09 250.74 0.23 0.34 276.36

 MEAN 17.74 0.00 -0.02 250.74 -0.09 250.74 0.23 0.32

 HUB 15.05 0.00 -0.02 250.74 -0.09 250.74 0.23 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.89 46.36 1.53 277.32 373.93 9.71 517.27 502.94 28.76

 MEAN 44.36 43.40 0.96 245.10 350.70 9.71 517.27 502.94 28.76

 HUB 39.68 38.84 0.84 207.96 325.81 9.71 517.27 502.94 28.76

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 285.44 79.75 274.07 1108.71 0.26 2.26 1.98 8.75

 MEAN 17.51 291.65 99.84 274.03 1108.80 0.26 2.34 2.07 6.78

 HUB 14.85 314.70 154.48 274.18 1108.90 0.28 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 273.73 335.77 193.97 0.30 1581.63 0.92 0.88

 MEAN 241.90 308.67 142.06 0.28 1749.41 0.92 0.88 0.88 1.22

 HUB 205.19 278.83 50.72 0.25 2295.25 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.27 1.02 9.82 525.71 1.01 519.25 505.02 27.44

 MEAN 10.29 1.02 9.82 526.08 1.01 519.33 505.26 27.37

 HUB 10.37 1.03 9.82 527.28 1.01 519.42 506.10 27.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.22 35.29 31.50 3.79 0.93 0.18 1.40

 MEAN 20.02 27.40 23.50 3.90 0.91 0.21 1.62

 HUB 29.40 10.48 6.50 3.98 0.91 0.27 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.964 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 324.1210 100.4966 308.1474 1107.3849 0.2927 -0.1963 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3068 9.7216 518.0162 505.8516 28.4799 18.0628 31.5000 13.4372

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 309.6278 67.5432 302.1710 1108.1560 0.2794 -0.1102 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2978 9.7622 518.7373 505.6476 451.3937 0.0283 0.1394

 

NASA/TM—2013-218094 M–61
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 315.0720 0.0000 315.0720 1107.8418 0.2844 -0.0102 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7156 518.4459 505.7366 0.0000 0.0600 0.0901 -0.2042

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7368 10.2671 1.0212 526.3192 4.0991 323.4248 2.5072

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25843.408 0.345 70.082 434643.813 0.443894E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.40382E+00 0.41969E+00 0.46465E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.138 EfDer = 0.912 SH = 0.455469E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.987 1583.382 10.267 526.309 1.000 1.000 0.980

 W Kg/sec = 21.812 Wdry = 47.769 WH2O = 0.219 lbm/sec H2O = 3.733g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.209 1571.879 1.375 0.252 53.496 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56390.766 37585.582 2.527 513.330 203.168 395.845 1.948

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 263.64 -0.09 263.64 0.24 0.34 264.19

 MEAN 16.97 0.00 -0.02 263.64 -0.09 263.64 0.24 0.32

 HUB 14.32 0.00 -0.02 263.64 -0.09 263.64 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 45.28 46.36 -1.08 266.13 374.67 9.88 520.80 505.32 27.15

 MEAN 41.66 43.80 -2.14 234.49 352.90 9.88 520.80 505.32 27.15

 HUB 36.90 37.84 -0.94 197.87 329.69 9.88 520.80 505.32 27.15

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 292.62 56.44 287.12 1111.44 0.26 2.16 1.89 8.34

 MEAN 16.57 297.62 79.35 286.84 1111.77 0.27 2.24 1.97 6.35

 HUB 13.89 318.40 138.24 286.82 1112.10 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 260.88 352.47 204.43 0.32 1067.42 0.92 0.83

 MEAN 229.01 323.54 149.66 0.29 1316.63 0.92 0.83 0.83 1.16

 HUB 191.93 291.81 53.69 0.26 1921.43 0.92 0.83

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.41 1.01 9.93 528.63 1.00 521.85 506.76 26.50

 MEAN 10.44 1.02 9.94 529.18 1.01 522.16 507.06 26.26

 HUB 10.52 1.02 9.95 530.50 1.01 522.47 507.91 25.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 11.12 35.45 31.50 3.95 0.93 0.11 1.40

 MEAN 15.46 27.55 23.50 4.05 0.89 0.15 1.62

 HUB 25.73 10.60 6.50 4.10 0.89 0.22 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.912 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 324.9496 79.7934 315.0004 1110.5967 0.2926 -0.1614 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4499 9.8571 521.0604 507.5642 27.1108 14.2147 32.4000 18.1853

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 322.4278 72.3111 314.2145 1110.7273 0.2903 -0.1669 2.2705

 

NASA/TM—2013-218094 M–62
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4355 9.8513 521.1821 507.5144 432.2457 0.0380 0.1020

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 320.5824 0.0000 320.5824 1110.8020 0.2886 -0.0656 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8183 521.2530 507.4550 0.0000 0.0600 0.1212 -0.2307

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5646 10.3924 1.0122 529.3992 3.1302 393.6498 3.0515

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 19747.289 0.290 53.551 453084.281 0.463055E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.58271E+00 0.59701E+00 0.63911E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-4.984 EfDer = 0.850 SH = 0.471634E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 47.987 1583.382 10.392 529.388 1.000 1.000 0.980

 W Kg/sec = 21.812 Wdry = 47.761 WH2O = 0.226 lbm/sec H2O = 3.890g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.574 1567.300 1.375 0.252 53.501 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56035.848 37583.160 2.532 509.668 201.326 384.739 1.911

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 263.87 -0.09 263.87 0.24 0.33 250.56

 MEAN 15.91 0.00 -0.02 263.87 -0.09 263.87 0.24 0.31

 HUB 13.07 0.00 -0.02 263.87 -0.09 263.87 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.82 47.36 -3.54 253.14 365.72 10.00 523.87 506.89 25.54

 MEAN 39.82 44.80 -4.98 219.88 343.53 10.00 523.87 506.89 25.54

 HUB 34.40 38.84 -4.44 180.60 319.80 10.00 523.87 506.89 25.54

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 290.49 41.01 287.58 1114.02 0.26 2.05 1.78 7.43

 MEAN 15.50 294.09 62.83 287.29 1114.40 0.26 2.13 1.86 5.75

 HUB 12.59 311.25 119.71 287.30 1114.77 0.28 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 247.89 354.27 206.88 0.32 737.33 0.92 0.78

 MEAN 214.14 324.70 151.31 0.29 975.21 0.92 0.78 0.78 1.13

 HUB 173.96 292.38 54.25 0.26 1508.38 0.92 0.78

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.48 1.01 10.01 530.99 1.00 524.30 507.95 25.32

 MEAN 10.51 1.01 10.02 531.51 1.00 524.66 508.21 25.06

 HUB 10.58 1.02 10.03 532.68 1.01 525.00 508.92 24.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.12 35.73 31.50 4.23 0.93 0.07 1.40

 MEAN 12.34 27.77 23.50 4.27 0.88 0.11 1.64

 HUB 22.62 10.69 6.50 4.19 0.88 0.18 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.850 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 333.9125 63.9853 327.7246 1112.5076 0.3001 -0.2695 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5138 9.8875 522.8798 508.8556 26.3342 11.0475 33.0000 21.9525

 

NASA/TM—2013-218094 M–63
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 341.5939 78.0033 332.5686 1112.0642 0.3072 -0.3870 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4785 9.8247 522.4607 508.9240 410.5396 0.0901 0.0732

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 332.6145 0.0000 332.6145 1112.5494 0.2990 -0.0833 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.8353 522.9161 508.7715 0.0000 0.0600 0.1400 -0.3660

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3679 10.4533 1.0059 531.6813 2.3357 488.6016 3.7876

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14741.917 0.240 39.977 482866.969 0.477473E-02

 

Melt Ratio at Stator LE, Throat, TE

0.75422E+00 0.76743E+00 0.80675E+00

 trTOT = 1.0422 Tt4 = 531.6813 T1 = 510.1644

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 136879.33 371.1910 74.9247 1.1195 0.7424 6.9260 1.0422 37.3740

NASA/TM—2013-218094 M–64
Appendix N: NPSS cycle analysis for the descent conditions 

10μm, ISA +18R 

************************************************************************************************************************************ 

Date:05/13/13 Time:07:06:30 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 463.30 Stator 1 exit: 470.73 Stator 2 inlet: 480.06 Stator 2 exit: 484.84 

 Stator 3 inlet: 494.48 Stator 3 exit: 498.82 Stator 4 inlet: 507.82 Stator 4 exit: 511.52 

 Stator 5 inlet: 518.91 Stator 5 exit: 522.14 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.76 

Fan Bypass Relative Humidity 1.24 

LPC Inlet Relative Humidity 1.13 

LPC Exit Relative Humidity 0.10 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 187.38 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 454.81 

Additional Water at LPC Exit 0.0014826 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 257.31 614.8 1.1256 692.01 8.6213 772.64 9.491 0.736 10.000 1698.5 1606.4 1116.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.31 4.267 457.74 -20.96 0.0000 832.56 2.854 407.97 2539.9 0.7800 1.40084 0.0000295 257.30 0.008 0.0000

FS1 Inlet.Fl_O 257.31 4.267 457.74 -20.96 0.0000 832.56 3.893 445.88 4168.2 0.3643 1.40084 0.0000295 257.30 0.008 0.0000

FS12 Splitter.Fl_02 230.57 4.265 457.74 -20.96 0.0000 746.40 3.840 444.21 3531.8 0.3898 1.40084 0.0000295 230.56 0.007 0.0000

FS2 Splitter.Fl_01 26.74 4.265 457.74 -20.96 0.0000 86.58 4.170 454.81 830.5 0.1792 1.40084 0.0000295 26.74 0.001 0.0000

FS14 Fan.Fl_O 230.57 4.813 475.56 -16.68 0.0000 674.05 4.039 452.29 2606.7 0.5067 1.40071 0.0000295 230.56 0.007 0.0000

FS23 LPC.Fl_O 26.74 6.647 531.58 -3.25 0.0000 59.86 6.354 524.79 412.6 0.2543 1.40005 0.0000295 26.74 0.001 0.0000

FS24 VaporIN.Fl_O 26.78 6.647 533.63 -11.30 0.0000 60.07 6.352 526.77 412.6 0.2554 1.39981 0.0015120 26.74 0.040 0.0015

FS25 Bleed2.Fl_O 24.11 6.647 533.63 -11.30 0.0000 54.06 6.410 528.14 412.6 0.2280 1.39981 0.0015120 24.07 0.036 0.0015

FS3 HPC.Fl_O 22.94 40.498 967.89 94.37 0.0000 11.37 35.639 934.20 49.7 0.4335 1.38244 0.0015120 22.90 0.035 0.0015

FS36 Bleed3.Fl_O 17.78 40.498 967.89 94.37 0.0000 8.81 37.709 948.95 49.3 0.3228 1.38244 0.0015120 17.75 0.027 0.0015

FS4 Burner.Fl_O 17.97 39.565 1698.47 82.11 0.0108 12.08 37.361 1674.31 74.6 0.2943 1.33234 0.0015120 17.75 0.027 0.0147

FS45 HPT.Fl_O 24.02 9.492 1120.65 -20.25 0.0081 54.66 8.598 1091.21 265.4 0.3827 1.36726 0.0015120 23.79 0.036 0.0114

FS49 LPT.Fl_O 24.30 3.259 878.24 -79.54 0.0080 142.56 3.069 863.73 860.2 0.2963 1.38236 0.0015120 24.07 0.036 0.0113

FS5 TEGV.Fl_O 24.30 3.259 878.32 -79.53 0.0080 142.56 3.069 863.80 860.2 0.2963 1.38236 0.0015120 24.07 0.036 0.0113

FS8 Core_Nozz.Fl_O 24.30 3.259 878.39 -79.53 0.0080 142.57 2.854 846.65 613.4 0.4422 1.38235 0.0015120 24.07 0.036 0.0113

FS17 FanDuctLkg.Fl_O 230.57 4.813 475.56 -16.68 0.0000 674.05 4.039 452.29 2606.7 0.5067 1.40071 0.0000295 230.56 0.007 0.0000

FS171 Bleed15.Fl_O 233.24 4.813 476.23 -16.62 0.0000 682.36 3.906 448.59 2481.9 0.5544 1.40070 0.0000465 233.23 0.011 0.0000

FS172 FanDuct.Fl_O 233.24 4.813 476.23 -16.62 0.0000 682.36 3.906 448.59 2481.9 0.5544 1.40070 0.0000465 233.23 0.011 0.0000

FS173 Byp_Nozz.Fl_O 233.24 4.813 476.23 -16.62 0.0000 682.36 2.854 410.06 2006.9 0.8971 1.40070 0.0000465 233.23 0.011 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.40 1.129 0.9053 2563.961 1.0389 0.9069 -1393.0 1639.98 54.90

LPC 86.58 1.559 0.8387 2563.961 1.1613 0.8485 -669.9 6.96 3.70

HPC 54.06 6.093 0.8186 8959.996 1.8138 0.8573 -3516.5 61.17 57.84

HPT 12.08 4.168 0.8742 220.524 1.3658 0.8516 3516.5 

LPT 54.66 2.912 0.8512 71.952 1.2742 0.8310 2062.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 867.24 1.126 0.9071 2539.514 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 73.72 1.520 0.7797 0.677 0.0000 1.1742 1.0739 1.0757 0.0003

HPC 49.17 5.853 0.8270 8721.128 10.9874 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.081 0.8742 1.325 4.0806 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.438 0.8575 0.809 2.4382 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–1
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2539.86 6179.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8871 752.52 41.53 9.492

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2820 752.52 41.53 3.259

TEGV 0.0000 0.2963 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.76 36.25 14.094

FanDuct 0.0000 0.5544 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.08 69.01 27.635

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.76 36.25 14.094

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 967.89 94.37 40.498

Splitter 8.6213 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.76 36.25 14.094

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9088.3 2032.2 3516.5 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6783 533.63 -11.30 6.647

LP_Shaft 2408.7 4498.2 2062.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7523 967.89 94.37 39.565

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4083 967.89 94.37 22.363

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.89 94.37 40.498

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.89 94.37 40.498

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.89 94.37 40.498

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.56 -16.68 4.813

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.56 -16.68 4.813

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.56 -16.68 4.813

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.56 -16.68 4.813

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1698.40 0.9995 0.0230 0.19223 0.01083 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.142 0.9801 1.0000 0.9800 613.40 0.442 614.9 464.3

Byp_Nozz 1.687 0.9800 1.0000 0.9800 2006.86 0.897 873.1 6329.6

NASA/TM—2013-218094 N–2
************************************************************************************************************************************ 

Date:05/13/13 Time:07:06:47 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.81 Stator 1 exit: 463.77 Stator 2 inlet: 472.50 Stator 2 exit: 476.96 

 Stator 3 inlet: 485.96 Stator 3 exit: 490.01 Stator 4 inlet: 498.42 Stator 4 exit: 501.85 

 Stator 5 inlet: 508.75 Stator 5 exit: 511.73 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.23 

Fan Bypass Relative Humidity 1.61 

LPC Inlet Relative Humidity 1.44 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 723.11 Fan/LPC Inlet Flow Velocity 180.82 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 448.84 

Additional Water at LPC Exit 0.0012504 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 18.00 250.36 604.5 1.0913 659.66 8.7106 723.11 9.212 0.763 10.000 1671.6 1580.1 1100.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 250.36 4.201 451.57 -22.43 0.0000 817.10 2.947 407.97 2557.3 0.7300 1.40089 0.0000285 250.35 0.007 0.0000

FS1 Inlet.Fl_O 250.36 4.201 451.57 -22.43 0.0000 817.10 3.848 440.36 4168.2 0.3563 1.40089 0.0000285 250.35 0.007 0.0000

FS12 Splitter.Fl_02 224.57 4.199 451.57 -22.43 0.0000 733.33 3.798 438.76 3531.8 0.3816 1.40089 0.0000285 224.57 0.006 0.0000

FS2 Splitter.Fl_01 25.78 4.199 451.57 -22.43 0.0000 84.19 4.111 448.84 830.5 0.1740 1.40089 0.0000285 25.78 0.001 0.0000

FS14 Fan.Fl_O 224.57 4.708 468.18 -18.45 0.0000 665.97 3.974 446.00 2606.7 0.4981 1.40077 0.0000285 224.57 0.006 0.0000

FS23 LPC.Fl_O 25.78 6.408 520.70 -5.86 0.0000 59.24 6.133 514.19 412.6 0.2514 1.40020 0.0000285 25.78 0.001 0.0000

FS24 VaporIN.Fl_O 25.81 6.408 522.46 -12.64 0.0000 59.42 6.131 515.89 412.6 0.2523 1.40001 0.0012789 25.78 0.033 0.0013

FS25 Bleed2.Fl_O 23.23 6.408 522.46 -12.64 0.0000 53.47 6.185 517.20 412.6 0.2254 1.40001 0.0012789 23.20 0.030 0.0013

FS3 HPC.Fl_O 22.11 38.704 946.04 90.28 0.0000 11.34 34.094 913.28 49.7 0.4316 1.38377 0.0012789 22.08 0.028 0.0013

FS36 Bleed3.Fl_O 17.13 38.704 946.04 90.28 0.0000 8.79 36.056 927.61 49.3 0.3215 1.38377 0.0012789 17.11 0.022 0.0013

FS4 Burner.Fl_O 17.32 37.813 1671.63 78.19 0.0107 12.08 35.705 1647.78 74.6 0.2942 1.33374 0.0012789 17.11 0.022 0.0143

FS45 HPT.Fl_O 23.14 9.186 1104.24 -21.47 0.0080 54.03 8.343 1075.95 265.4 0.3772 1.36842 0.0012789 22.93 0.029 0.0110

FS49 LPT.Fl_O 23.42 3.310 875.72 -77.20 0.0079 135.10 3.137 862.85 860.2 0.2791 1.38259 0.0012789 23.20 0.030 0.0109

FS5 TEGV.Fl_O 23.42 3.310 875.79 -77.20 0.0079 135.10 3.137 862.92 860.2 0.2791 1.38259 0.0012789 23.20 0.030 0.0109

FS8 Core_Nozz.Fl_O 23.42 3.310 875.86 -77.20 0.0079 135.11 2.947 848.12 613.4 0.4131 1.38258 0.0012789 23.20 0.030 0.0109

FS17 FanDuctLkg.Fl_O 224.57 4.708 468.18 -18.45 0.0000 665.97 3.974 446.00 2606.7 0.4981 1.40077 0.0000285 224.57 0.006 0.0000

FS171 Bleed15.Fl_O 227.16 4.708 468.80 -18.38 0.0000 674.07 3.849 442.53 2481.9 0.5442 1.40076 0.0000427 227.15 0.010 0.0000

FS172 FanDuct.Fl_O 227.16 4.708 468.80 -18.38 0.0000 674.07 3.849 442.53 2481.9 0.5442 1.40076 0.0000427 227.15 0.010 0.0000

FS173 Byp_Nozz.Fl_O 227.16 4.708 468.80 -18.38 0.0000 674.07 2.947 409.96 2006.9 0.8461 1.40076 0.0000427 227.15 0.010 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 733.33 1.121 0.9045 2500.478 1.0368 0.9060 -1265.0 2240.58 54.74

LPC 84.19 1.526 0.8394 2500.478 1.1531 0.8487 -604.5 6.76 3.34

HPC 53.47 6.040 0.8178 8941.099 1.8108 0.8565 -3301.0 61.07 57.68

HPT 12.08 4.116 0.8729 219.483 1.3626 0.8503 3301.0 

LPT 54.03 2.775 0.8456 70.211 1.2589 0.8258 1869.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 852.05 1.118 0.9063 2476.637 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.97 1.492 0.7767 0.660 0.0000 1.1861 1.0697 1.0806 0.0003 

HPC 48.63 5.802 0.8262 8702.736 11.0009 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.030 0.8729 1.319 4.0301 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.335 0.8519 0.790 2.3352 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–3
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2557.30 5626.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8550 735.85 38.82 9.186

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2718 735.85 38.82 3.310

TEGV 0.0000 0.2791 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 714.62 33.67 13.513

FanDuct 0.0000 0.5442 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 845.67 65.58 26.432

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 714.62 33.67 13.513

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 946.04 90.28 38.704

Splitter 8.7106 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 714.62 33.67 13.513

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8973.7 1932.0 3301.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5814 522.46 -12.64 6.408

LP_Shaft 2333.1 4208.5 1869.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6527 946.04 90.28 37.813

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3212 946.04 90.28 21.438

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 946.04 90.28 38.704

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 946.04 90.28 38.704

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 946.04 90.28 38.704

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 468.18 -18.45 4.708

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 468.18 -18.45 4.708

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 468.18 -18.45 4.708

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 468.18 -18.45 4.708

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1671.57 0.9995 0.0230 0.18324 0.01071 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.123 0.9801 1.0000 0.9800 613.40 0.413 574.8 418.3

Byp_Nozz 1.598 0.9800 1.0000 0.9800 2006.86 0.846 823.3 5812.9

NASA/TM—2013-218094 N–4
************************************************************************************************************************************ 

Date:05/13/13 Time:07:07:03 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 454.80 Stator 1 exit: 461.58 Stator 2 inlet: 470.09 Stator 2 exit: 474.44 

 Stator 3 inlet: 483.21 Stator 3 exit: 487.14 Stator 4 inlet: 495.33 Stator 4 exit: 498.66 

 Stator 5 inlet: 505.38 Stator 5 exit: 508.27 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.40 

Fan Bypass Relative Humidity 1.75 

LPC Inlet Relative Humidity 1.56 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 707.26 Fan/LPC Inlet Flow Velocity 178.30 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 447.03 

Additional Water at LPC Exit 0.0011211 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 18.00 257.11 619.2 1.0843 671.35 8.7472 707.26 9.095 0.772 10.000 1661.3 1570.1 1093.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.11 4.339 449.68 -22.87 0.0000 810.76 3.088 407.97 2561.9 0.7140 1.40090 0.0000272 257.10 0.007 0.0000

FS1 Inlet.Fl_O 257.11 4.339 449.68 -22.87 0.0000 810.76 3.981 438.71 4168.2 0.3531 1.40090 0.0000272 257.10 0.007 0.0000

FS12 Splitter.Fl_02 230.73 4.337 449.68 -22.87 0.0000 727.95 3.929 437.14 3531.8 0.3782 1.40090 0.0000272 230.72 0.006 0.0000

FS2 Splitter.Fl_01 26.38 4.337 449.68 -22.87 0.0000 83.22 4.249 447.03 830.5 0.1720 1.40090 0.0000272 26.38 0.001 0.0000

FS14 Fan.Fl_O 230.73 4.850 465.85 -19.00 0.0000 662.53 4.103 444.08 2606.7 0.4946 1.40079 0.0000272 230.72 0.006 0.0000

FS23 LPC.Fl_O 26.38 6.563 517.05 -6.72 0.0000 58.97 6.284 510.66 412.6 0.2502 1.40025 0.0000272 26.38 0.001 0.0000

FS24 VaporIN.Fl_O 26.41 6.563 518.64 -12.81 0.0000 59.13 6.282 512.19 412.6 0.2510 1.40008 0.0011483 26.38 0.030 0.0011

FS25 Bleed2.Fl_O 23.77 6.563 518.64 -12.81 0.0000 53.21 6.338 513.48 412.6 0.2242 1.40008 0.0011483 23.74 0.027 0.0011

FS3 HPC.Fl_O 22.61 39.464 938.25 89.09 0.0000 11.33 34.774 905.81 49.7 0.4311 1.38425 0.0011483 22.59 0.026 0.0011

FS36 Bleed3.Fl_O 17.53 39.464 938.25 89.09 0.0000 8.78 36.770 919.99 49.3 0.3211 1.38425 0.0011483 17.51 0.020 0.0011

FS4 Burner.Fl_O 17.71 38.555 1661.28 77.08 0.0107 12.08 36.406 1637.53 74.6 0.2942 1.33430 0.0011483 17.51 0.020 0.0141

FS45 HPT.Fl_O 23.67 9.406 1097.90 -21.59 0.0079 53.81 8.551 1070.00 265.4 0.3754 1.36889 0.0011483 23.46 0.027 0.0109

FS49 LPT.Fl_O 23.95 3.450 874.50 -76.00 0.0079 132.48 3.278 862.18 860.2 0.2732 1.38271 0.0011483 23.74 0.027 0.0108

FS5 TEGV.Fl_O 23.95 3.450 874.58 -76.00 0.0079 132.48 3.278 862.25 860.2 0.2732 1.38270 0.0011483 23.74 0.027 0.0108

FS8 Core_Nozz.Fl_O 23.95 3.450 874.65 -76.00 0.0079 132.49 3.088 848.21 613.4 0.4032 1.38270 0.0011483 23.74 0.027 0.0108

FS17 FanDuctLkg.Fl_O 230.73 4.850 465.85 -19.00 0.0000 662.53 4.103 444.08 2606.7 0.4946 1.40079 0.0000272 230.72 0.006 0.0000

FS171 Bleed15.Fl_O 233.37 4.850 466.45 -18.93 0.0000 670.55 3.977 440.69 2481.9 0.5400 1.40078 0.0000399 233.36 0.009 0.0000

FS172 FanDuct.Fl_O 233.37 4.850 466.45 -18.93 0.0000 670.55 3.977 440.69 2481.9 0.5400 1.40078 0.0000399 233.36 0.009 0.0000

FS173 Byp_Nozz.Fl_O 233.37 4.850 466.45 -18.93 0.0000 670.55 3.088 409.92 2006.9 0.8293 1.40078 0.0000399 233.36 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 727.95 1.118 0.9041 2474.843 1.0360 0.9056 -1264.8 2632.78 54.65

LPC 83.22 1.513 0.8396 2474.843 1.1498 0.8487 -602.7 6.68 3.27

HPC 53.21 6.013 0.8173 8932.634 1.8090 0.8561 -3343.3 61.11 57.70

HPT 12.08 4.099 0.8723 219.152 1.3615 0.8497 3343.3 

LPT 53.81 2.726 0.8435 69.546 1.2534 0.8239 1867.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 845.80 1.116 0.9060 2451.245 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 69.86 1.480 0.7755 0.654 0.0000 1.1912 1.0688 1.0827 0.0003

HPC 48.40 5.777 0.8258 8694.496 11.0014 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.013 0.8723 1.317 4.0130 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.298 0.8498 0.782 2.2984 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–5
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.92 5651.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8746 729.98 38.14 9.406

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2781 729.98 38.14 3.450

TEGV 0.0000 0.2732 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 708.95 33.05 13.802

FanDuct 0.0000 0.5400 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 838.78 64.63 26.962 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 708.95 33.05 13.802

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 938.25 89.09 39.464

Splitter 8.7472 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 708.95 33.05 13.802

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8932.4 1965.8 3343.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6407 518.64 -12.81 6.563

LP_Shaft 2304.4 4256.6 1867.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7136 938.25 89.09 38.555

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3745 938.25 89.09 21.882

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 938.25 89.09 39.464

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 938.25 89.09 39.464

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 938.25 89.09 39.464

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 465.85 -19.00 4.850

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 465.85 -19.00 4.850

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 465.85 -19.00 4.850

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 465.85 -19.00 4.850

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1661.22 0.9995 0.0230 0.18649 0.01065 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.403 561.1 417.7

Byp_Nozz 1.570 0.9800 1.0000 0.9800 2006.86 0.829 807.0 5853.3

NASA/TM—2013-218094 N–6
************************************************************************************************************************************ 

Date:05/13/13 Time:07:07:18 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.45 Stator 1 exit: 462.82 Stator 2 inlet: 470.81 Stator 2 exit: 474.87 

 Stator 3 inlet: 483.09 Stator 3 exit: 486.75 Stator 4 inlet: 494.44 Stator 4 exit: 497.52 

 Stator 5 inlet: 503.81 Stator 5 exit: 506.47 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.00 

Fan Bypass Relative Humidity 2.26 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.22 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 667.90 Fan/LPC Inlet Flow Velocity 172.72 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 414.42 Fan/LPC Inlet Static Temperature 449.12 

Additional Water at LPC Exit 0.0010079 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 18.00 278.63 674.3 1.0687 720.58 8.8272 667.90 8.760 0.795 10.000 1654.1 1562.9 1091.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 278.63 4.831 451.61 -22.45 0.0000 790.90 3.578 414.42 2577.9 0.6690 1.40088 0.0000348 278.62 0.010 0.0000

FS1 Inlet.Fl_O 278.63 4.831 451.61 -22.45 0.0000 790.90 4.453 441.20 4168.2 0.3430 1.40088 0.0000348 278.62 0.010 0.0000

FS12 Splitter.Fl_02 250.28 4.829 451.61 -22.45 0.0000 710.78 4.398 439.70 3531.8 0.3676 1.40088 0.0000348 250.27 0.009 0.0000

FS2 Splitter.Fl_01 28.35 4.829 451.61 -22.45 0.0000 80.52 4.736 449.12 830.5 0.1662 1.40088 0.0000348 28.35 0.001 0.0000

FS14 Fan.Fl_O 250.28 5.362 466.82 -18.81 0.0000 650.77 4.572 446.01 2606.7 0.4825 1.40078 0.0000348 250.27 0.009 0.0000

FS23 LPC.Fl_O 28.35 7.127 514.90 -7.28 0.0000 58.25 6.832 508.70 412.6 0.2469 1.40028 0.0000348 28.35 0.001 0.0000

FS24 VaporIN.Fl_O 28.38 7.127 516.34 -12.75 0.0000 58.39 6.830 510.08 412.6 0.2476 1.40012 0.0010427 28.35 0.030 0.0010

FS25 Bleed2.Fl_O 25.54 7.127 516.34 -12.75 0.0000 52.55 6.889 511.33 412.6 0.2212 1.40012 0.0010427 25.52 0.027 0.0010

FS3 HPC.Fl_O 24.30 42.320 931.18 87.94 0.0000 11.31 37.308 899.09 49.7 0.4301 1.38467 0.0010427 24.28 0.025 0.0010

FS36 Bleed3.Fl_O 18.84 42.320 931.18 87.94 0.0000 8.76 39.440 913.11 49.3 0.3205 1.38467 0.0010427 18.82 0.020 0.0010

FS4 Burner.Fl_O 19.04 41.345 1654.14 75.96 0.0106 12.08 39.040 1630.46 74.6 0.2941 1.33467 0.0010427 18.82 0.020 0.0140

FS45 HPT.Fl_O 25.44 10.196 1095.08 -21.51 0.0079 53.29 9.289 1067.87 265.4 0.3710 1.36909 0.0010427 25.22 0.026 0.0107

FS49 LPT.Fl_O 25.74 3.942 883.50 -72.98 0.0078 125.26 3.767 872.47 860.2 0.2570 1.38222 0.0010427 25.52 0.027 0.0106

FS5 TEGV.Fl_O 25.74 3.942 883.57 -72.98 0.0078 125.27 3.767 872.54 860.2 0.2570 1.38222 0.0010427 25.52 0.027 0.0106

FS8 Core_Nozz.Fl_O 25.74 3.942 883.64 -72.98 0.0078 125.27 3.578 860.25 613.4 0.3768 1.38222 0.0010427 25.52 0.027 0.0106

FS17 FanDuctLkg.Fl_O 250.28 5.362 466.82 -18.81 0.0000 650.77 4.572 446.01 2606.7 0.4825 1.40078 0.0000348 250.27 0.009 0.0000

FS171 Bleed15.Fl_O 253.12 5.362 467.38 -18.74 0.0000 658.54 4.441 442.84 2481.9 0.5258 1.40077 0.0000461 253.11 0.012 0.0000

FS172 FanDuct.Fl_O 253.12 5.362 467.38 -18.74 0.0000 658.54 4.441 442.84 2481.9 0.5258 1.40077 0.0000461 253.11 0.012 0.0000

FS173 Byp_Nozz.Fl_O 253.12 5.362 467.38 -18.74 0.0000 658.54 3.578 416.28 2006.9 0.7824 1.40077 0.0000461 253.11 0.012 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.78 1.110 0.9033 2398.017 1.0337 0.9047 -1290.9 5592.06 54.18

LPC 80.52 1.476 0.8406 2398.017 1.1402 0.8491 -608.6 6.41 3.05

HPC 52.55 5.938 0.8161 8910.844 1.8034 0.8549 -3550.9 61.40 57.91

HPT 12.08 4.055 0.8718 218.602 1.3584 0.8493 3550.9 

LPT 53.29 2.586 0.8389 67.618 1.2372 0.8199 1899.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.85 1.108 0.9051 2375.152 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.54 1.446 0.7719 0.633 0.0000 1.2101 1.0675 1.0890 0.0003

HPC 47.79 5.705 0.8245 8673.287 10.9923 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.971 0.8718 1.314 3.9705 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.193 0.8452 0.761 2.1932 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–7
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2577.91 5784.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9400 725.24 37.60 10.196

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2989 725.24 37.60 3.942

TEGV 0.0000 0.2570 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.45 32.56 14.870

FanDuct 0.0000 0.5258 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 832.81 63.78 28.947

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.45 32.56 14.870

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 931.18 87.94 42.320

Splitter 8.8272 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.45 32.56 14.870

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8890.8 2097.7 3550.9 WB17Y Bleed> 0.1000 1.0000 1.0000 2.8382 516.34 -12.75 7.127

LP_Shaft 2237.6 4458.5 1899.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.9166 931.18 87.94 41.345

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5521 931.18 87.94 23.528

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 931.18 87.94 42.320

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 931.18 87.94 42.320

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 931.18 87.94 42.320

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 466.82 -18.81 5.362

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 466.82 -18.81 5.362

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 466.82 -18.81 5.362

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 466.82 -18.81 5.362

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1654.07 0.9995 0.0230 0.20016 0.01064 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.377 527.9 422.4

Byp_Nozz 1.499 0.9800 1.0000 0.9800 2006.86 0.782 767.2 6036.0

NASA/TM—2013-218094 N–8
************************************************************************************************************************************ 

Date:05/13/13 Time:07:07:44 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 15/ 43/ 2/12 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.08 Stator 1 exit: 470.61 Stator 2 inlet: 477.45 Stator 2 exit: 480.75 

 Stator 3 inlet: 487.89 Stator 3 exit: 490.80 Stator 4 inlet: 497.51 Stator 4 exit: 499.91 

 Stator 5 inlet: 505.31 Stator 5 exit: 507.35 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.96 

Fan Bypass Relative Humidity 3.11 

LPC Inlet Relative Humidity 2.83 

LPC Exit Relative Humidity 0.47 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 617.99 Fan/LPC Inlet Flow Velocity 174.69 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 429.58 Fan/LPC Inlet Static Temperature 458.87 

Additional Water at LPC Exit 0.0010284 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 18.00 305.17 734.1 1.0714 786.52 8.3887 617.99 8.201 0.828 10.000 1658.5 1566.7 1096.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 305.17 5.595 461.42 -20.30 0.0000 756.00 4.358 429.58 2596.8 0.6080 1.40081 0.0000681 305.15 0.021 0.0001

FS1 Inlet.Fl_O 305.17 5.595 461.42 -20.30 0.0000 756.00 5.199 451.81 4168.2 0.3257 1.40081 0.0000681 305.15 0.021 0.0001

FS12 Splitter.Fl_02 272.66 5.592 461.42 -20.30 0.0000 675.82 5.147 450.58 3531.8 0.3464 1.40081 0.0000681 272.64 0.019 0.0001

FS2 Splitter.Fl_01 32.50 5.592 461.42 -20.30 0.0000 80.56 5.485 458.87 830.5 0.1663 1.40081 0.0000681 32.50 0.002 0.0001

FS14 Fan.Fl_O 272.66 6.141 475.29 -16.97 0.0000 624.63 5.322 456.22 2606.7 0.4567 1.40070 0.0000681 272.64 0.019 0.0001

FS23 LPC.Fl_O 32.50 7.833 516.04 -7.20 0.0000 60.83 7.477 509.22 412.6 0.2587 1.40026 0.0000681 32.50 0.002 0.0001

FS24 VaporIN.Fl_O 32.54 7.833 517.50 -12.78 0.0000 60.98 7.475 510.62 412.6 0.2595 1.40010 0.0010965 32.50 0.036 0.0011

FS25 Bleed2.Fl_O 27.66 7.833 517.50 -12.78 0.0000 51.83 7.578 512.63 412.6 0.2180 1.40010 0.0010965 27.63 0.030 0.0011

FS3 HPC.Fl_O 26.32 45.884 929.98 87.34 0.0000 11.29 40.476 898.09 49.7 0.4290 1.38473 0.0010965 26.29 0.029 0.0011

FS36 Bleed3.Fl_O 20.39 45.884 929.98 87.34 0.0000 8.75 42.775 912.02 49.3 0.3197 1.38473 0.0010965 20.37 0.022 0.0011

FS4 Burner.Fl_O 20.61 44.827 1658.51 75.27 0.0107 12.08 42.328 1634.78 74.6 0.2942 1.33439 0.0010965 20.37 0.022 0.0142

FS45 HPT.Fl_O 27.55 11.207 1100.65 -21.61 0.0080 52.63 10.237 1074.10 265.4 0.3656 1.36868 0.0010965 27.30 0.030 0.0109

FS49 LPT.Fl_O 27.87 4.717 906.68 -68.72 0.0079 114.81 4.543 897.30 860.2 0.2342 1.38084 0.0010965 27.63 0.030 0.0108

FS5 TEGV.Fl_O 27.87 4.717 906.75 -68.72 0.0079 114.82 4.543 897.37 860.2 0.2342 1.38084 0.0010965 27.63 0.030 0.0108

FS8 Core_Nozz.Fl_O 27.87 4.717 906.82 -68.72 0.0079 114.82 4.358 887.22 613.4 0.3403 1.38083 0.0010965 27.63 0.030 0.0108

FS17 FanDuctLkg.Fl_O 272.66 6.141 475.29 -16.97 0.0000 624.63 5.322 456.22 2606.7 0.4567 1.40070 0.0000681 272.64 0.019 0.0001

FS171 Bleed15.Fl_O 277.54 6.141 476.04 -16.90 0.0000 636.31 5.174 453.27 2481.9 0.5006 1.40069 0.0000862 277.52 0.024 0.0001

FS172 FanDuct.Fl_O 277.54 6.141 476.04 -16.90 0.0000 636.31 5.174 453.27 2481.9 0.5006 1.40069 0.0000862 277.52 0.024 0.0001

FS173 Byp_Nozz.Fl_O 277.54 6.141 476.04 -16.90 0.0000 636.31 4.358 431.55 2006.9 0.7172 1.40069 0.0000862 277.52 0.024 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 675.82 1.098 0.9022 2251.763 1.0301 0.9035 -1282.9 -9545.82 52.70

LPC 80.56 1.401 0.8545 2251.763 1.1184 0.8613 -602.2 5.95 2.63

HPC 51.83 5.858 0.8146 8887.267 1.7971 0.8535 -3822.9 61.67 58.09

HPT 12.08 4.000 0.8720 217.982 1.3542 0.8497 3822.9 

LPT 52.63 2.376 0.8307 64.018 1.2114 0.8129 1885.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 785.23 1.096 0.9041 2230.293 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 60.40 1.383 0.7655 0.595 0.0000 1.3338 1.0471 1.1162 0.0003

HPC 47.14 5.629 0.8231 8650.338 10.9851 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.917 0.8720 1.310 3.9168 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.035 0.8369 0.720 2.0347 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–9
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.78 5861.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0178 725.21 37.28 11.207

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3236 725.21 37.28 4.717

TEGV 0.0000 0.2342 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.54 32.27 16.204

FanDuct 0.0000 0.5006 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 832.17 63.31 31.424

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.54 32.27 16.204

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 929.98 87.34 45.884

Splitter 8.3887 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 704.54 32.27 16.204

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8877.3 2261.7 3822.9 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8805 517.50 -12.78 7.833

LP_Shaft 2123.9 4661.9 1885.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1578 929.98 87.34 44.827

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7632 929.98 87.34 25.596

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 929.98 87.34 45.884

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 929.98 87.34 45.884

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 929.98 87.34 45.884

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.29 -16.97 6.141

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.29 -16.97 6.141

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.29 -16.97 6.141

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.29 -16.97 6.141

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1658.44 0.9995 0.0230 0.21848 0.01072 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 484.0 419.3

Byp_Nozz 1.409 0.9800 1.0000 0.9800 2006.86 0.717 716.0 6176.4

NASA/TM—2013-218094 N–10
************************************************************************************************************************************ 

Date:05/13/13 Time:07:08:15 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 23/ 51/ 2/20 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.14 Stator 1 exit: 477.22 Stator 2 inlet: 481.84 Stator 2 exit: 483.66 

 Stator 3 inlet: 488.81 Stator 3 exit: 490.22 Stator 4 inlet: 495.16 Stator 4 exit: 496.17 

 Stator 5 inlet: 499.77 Stator 5 exit: 500.50 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.82 

Fan Bypass Relative Humidity 3.94 

LPC Inlet Relative Humidity 3.82 

LPC Exit Relative Humidity 1.19 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 571.13 Fan/LPC Inlet Flow Velocity 194.31 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.36 

Ambient Static Temperature 445.14 Fan/LPC Inlet Static Temperature 469.18 

Additional Water at LPC Exit 0.0009281 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 18.00 330.61 753.5 1.1140 839.45 7.0610 571.13 7.339 0.859 10.000 1668.8 1574.6 1107.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 330.61 6.516 472.33 -18.03 0.0000 711.54 5.297 445.14 2595.6 0.5520 1.40072 0.0001274 330.57 0.042 0.0001

FS1 Inlet.Fl_O 330.61 6.516 472.33 -18.03 0.0000 711.54 6.111 463.73 4168.2 0.3041 1.40072 0.0001274 330.57 0.042 0.0001

FS12 Splitter.Fl_02 289.60 6.513 472.33 -18.03 0.0000 623.58 6.077 463.07 3531.8 0.3159 1.40072 0.0001274 289.56 0.037 0.0001

FS2 Splitter.Fl_01 41.01 6.513 472.33 -18.03 0.0000 88.31 6.363 469.18 830.5 0.1829 1.40072 0.0001274 41.01 0.005 0.0001

FS14 Fan.Fl_O 289.60 7.058 484.50 -15.11 0.0000 582.75 6.259 468.12 2606.7 0.4178 1.40061 0.0001274 289.56 0.037 0.0001

FS23 LPC.Fl_O 41.01 8.214 511.73 -8.58 0.0000 72.88 7.665 501.70 412.6 0.3161 1.40031 0.0001274 41.01 0.005 0.0001

FS24 VaporIN.Fl_O 41.05 8.214 513.06 -13.61 0.0000 73.05 7.662 502.95 412.6 0.3170 1.40016 0.0010555 41.01 0.043 0.0011

FS25 Bleed2.Fl_O 28.74 8.214 513.06 -13.61 0.0000 51.13 7.954 508.36 412.6 0.2149 1.40016 0.0010555 28.71 0.030 0.0011

FS3 HPC.Fl_O 27.34 47.823 920.81 85.31 0.0000 11.20 42.292 889.82 49.7 0.4246 1.38527 0.0010555 27.31 0.029 0.0011

FS36 Bleed3.Fl_O 21.19 47.823 920.81 85.31 0.0000 8.68 44.640 903.32 49.3 0.3168 1.38527 0.0010555 21.17 0.022 0.0011

FS4 Burner.Fl_O 21.42 46.722 1668.79 72.94 0.0110 12.09 44.115 1644.95 74.6 0.2943 1.33370 0.0010555 21.17 0.022 0.0145

FS45 HPT.Fl_O 28.63 12.036 1111.68 -22.65 0.0082 51.18 11.057 1086.57 265.4 0.3540 1.36781 0.0010555 28.37 0.030 0.0111

FS49 LPT.Fl_O 28.97 5.627 938.91 -64.51 0.0081 101.80 5.465 931.39 860.2 0.2063 1.37879 0.0010555 28.71 0.030 0.0110

FS5 TEGV.Fl_O 28.97 5.627 938.98 -64.51 0.0081 101.80 5.465 931.47 860.2 0.2063 1.37879 0.0010555 28.71 0.030 0.0110

FS8 Core_Nozz.Fl_O 28.97 5.627 939.05 -64.51 0.0081 101.81 5.297 923.58 613.4 0.2971 1.37878 0.0010555 28.71 0.030 0.0110

FS17 FanDuctLkg.Fl_O 289.60 7.058 484.50 -15.11 0.0000 582.75 6.259 468.12 2606.7 0.4178 1.40061 0.0001274 289.56 0.037 0.0001

FS171 Bleed15.Fl_O 301.92 7.058 485.66 -15.05 0.0000 608.26 6.064 465.02 2481.9 0.4707 1.40060 0.0001652 301.87 0.050 0.0002

FS172 FanDuct.Fl_O 301.92 7.058 485.66 -15.05 0.0000 608.26 6.064 465.02 2481.9 0.4707 1.40060 0.0001652 301.87 0.050 0.0002

FS173 Byp_Nozz.Fl_O 301.92 7.058 485.66 -15.05 0.0000 608.26 5.297 447.36 2006.9 0.6536 1.40060 0.0001652 301.87 0.050 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.58 1.084 0.9033 2046.616 1.0258 0.9044 -1195.3 -2784.52 49.87

LPC 88.31 1.261 0.8225 2046.616 1.0834 0.8283 -548.3 6.38 2.41

HPC 51.13 5.822 0.8139 8865.532 1.7948 0.8528 -3924.5 60.78 57.16

HPT 12.09 3.882 0.8734 215.845 1.3455 0.8519 3924.5 

LPT 51.18 2.139 0.8214 58.576 1.1811 0.8051 1743.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.54 1.082 0.9051 2027.101 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.54 1.312 0.7608 0.541 0.0000 1.6496 0.8378 1.0812 0.0003

HPC 46.50 5.595 0.8223 8629.182 11.0483 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.802 0.8734 1.297 3.8020 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.857 0.8275 0.659 1.8567 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–11
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2595.59 5868.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0575 718.34 35.85 12.036

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3362 718.34 35.85 5.627

TEGV 0.0000 0.2063 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.91 30.90 16.928

FanDuct 0.0000 0.4707 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 824.09 61.57 32.772

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.91 30.90 16.928

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 920.81 85.31 47.823

Splitter 7.0610 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.91 30.90 16.928

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8817.5 2337.7 3924.5 WB17Y Bleed> 0.3000 1.0000 1.0000 12.3156 513.06 -13.61 8.214

LP_Shaft 1953.0 4688.8 1743.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2811 920.81 85.31 46.722

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8711 920.81 85.31 26.882

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 920.81 85.31 47.823

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 920.81 85.31 47.823

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 920.81 85.31 47.823

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 484.50 -15.11 7.058

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 484.50 -15.11 7.058

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 484.50 -15.11 7.058

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 484.50 -15.11 7.058

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1668.72 0.9995 0.0230 0.23318 0.01102 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.297 430.8 387.9 

Byp_Nozz 1.333 0.9800 1.0000 0.9800 2006.86 0.654 664.4 6234.5

NASA/TM—2013-218094 N–12
************************************************************************************************************************************ 

Date:05/13/13 Time:07:08:46 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 26/ 54/ 2/23 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 486.29 Stator 1 exit: 489.25 Stator 2 inlet: 492.01 Stator 2 exit: 492.78 

 Stator 3 inlet: 496.12 Stator 3 exit: 496.46 Stator 4 inlet: 499.72 Stator 4 exit: 499.76 

 Stator 5 inlet: 501.62 Stator 5 exit: 501.46 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.85 

Fan Bypass Relative Humidity 4.91 

LPC Inlet Relative Humidity 5.02 

LPC Exit Relative Humidity 2.61 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 518.26 Fan/LPC Inlet Flow Velocity 204.13 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.74 

Ambient Static Temperature 465.18 Fan/LPC Inlet Static Temperature 484.08 

Additional Water at LPC Exit 0.0009833 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 18.00 368.24 837.7 1.1161 934.98 6.2459 518.26 6.460 0.890 10.000 1701.9 1603.8 1138.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 368.24 7.943 487.56 -15.16 0.0000 660.53 6.740 465.18 2616.6 0.4900 1.40057 0.0002627 368.14 0.097 0.0003

FS1 Inlet.Fl_O 368.24 7.943 487.56 -15.16 0.0000 660.53 7.522 480.02 4168.2 0.2800 1.40057 0.0002627 368.14 0.097 0.0003

FS12 Splitter.Fl_02 317.42 7.939 487.56 -15.16 0.0000 569.66 7.502 479.72 3531.8 0.2855 1.40057 0.0002627 317.33 0.083 0.0003

FS2 Splitter.Fl_01 50.82 7.939 487.56 -15.16 0.0000 91.21 7.743 484.08 830.5 0.1892 1.40057 0.0002627 50.81 0.013 0.0003

FS14 Fan.Fl_O 317.42 8.514 498.42 -12.55 0.0000 537.10 7.713 484.55 2606.7 0.3781 1.40045 0.0002627 317.33 0.083 0.0003

FS23 LPC.Fl_O 50.82 9.087 515.32 -8.50 0.0000 81.92 8.301 502.16 412.6 0.3618 1.40024 0.0002627 50.81 0.013 0.0003

FS24 VaporIN.Fl_O 50.87 9.087 516.72 -13.83 0.0000 82.11 8.297 503.45 412.6 0.3629 1.40009 0.0012460 50.81 0.063 0.0012

FS25 Bleed2.Fl_O 30.52 9.087 516.72 -13.83 0.0000 49.27 8.821 512.34 412.6 0.2066 1.40009 0.0012460 30.48 0.038 0.0012

FS3 HPC.Fl_O 29.04 51.310 920.26 84.09 0.0000 11.08 45.517 890.05 49.7 0.4191 1.38528 0.0012460 29.01 0.036 0.0012

FS36 Bleed3.Fl_O 22.51 51.310 920.26 84.09 0.0000 8.59 47.970 903.18 49.3 0.3131 1.38528 0.0012460 22.48 0.028 0.0012

FS4 Burner.Fl_O 22.77 50.129 1701.92 71.14 0.0116 12.09 47.330 1677.69 74.6 0.2947 1.33172 0.0012460 22.48 0.028 0.0153

FS45 HPT.Fl_O 30.42 13.561 1142.72 -23.26 0.0086 48.94 12.562 1119.52 265.4 0.3364 1.36550 0.0012460 30.13 0.038 0.0118

FS49 LPT.Fl_O 30.78 7.048 989.02 -60.45 0.0085 88.63 6.895 983.12 860.2 0.1787 1.37544 0.0012460 30.48 0.038 0.0117

FS5 TEGV.Fl_O 30.78 7.048 989.09 -60.45 0.0085 88.63 6.895 983.19 860.2 0.1787 1.37544 0.0012460 30.48 0.038 0.0117

FS8 Core_Nozz.Fl_O 30.78 7.048 989.16 -60.45 0.0085 88.64 6.740 977.17 613.5 0.2555 1.37543 0.0012460 30.48 0.038 0.0117

FS17 FanDuctLkg.Fl_O 317.42 8.514 498.42 -12.55 0.0000 537.10 7.713 484.55 2606.7 0.3781 1.40045 0.0002627 317.33 0.083 0.0003

FS171 Bleed15.Fl_O 337.77 8.514 499.53 -12.63 0.0000 572.16 7.478 481.33 2481.9 0.4345 1.40043 0.0003219 337.66 0.109 0.0003

FS172 FanDuct.Fl_O 337.77 8.514 499.53 -12.63 0.0000 572.16 7.478 481.33 2481.9 0.4345 1.40043 0.0003219 337.66 0.109 0.0003

FS173 Byp_Nozz.Fl_O 337.77 8.514 499.53 -12.63 0.0000 572.16 6.740 467.24 2006.9 0.5873 1.40043 0.0003219 337.66 0.109 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 569.66 1.072 0.9055 1850.759 1.0223 0.9064 -1170.2 -1884.98 46.41

LPC 91.21 1.145 0.6913 1850.759 1.0569 0.6972 -478.8 6.96 2.20

HPC 49.27 5.646 0.8099 8805.262 1.7810 0.8491 -4126.3 60.59 56.76

HPT 12.09 3.697 0.8755 213.036 1.3307 0.8552 4126.2 

LPT 48.94 1.924 0.8145 53.082 1.1521 0.8002 1649.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 661.89 1.071 0.9073 1833.113 0.0439 0.8607 1.0235 0.9980 0.9905

LPC 47.10 1.248 0.7559 0.489 0.0000 1.9364 0.5839 0.9146 0.0003

HPC 44.81 5.427 0.8183 8570.520 11.0857 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.622 0.8755 1.280 3.6218 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.695 0.8205 0.597 1.6951 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–13
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2616.64 5931.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.1232 719.87 35.13 13.561

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3571 719.87 35.13 7.048

TEGV 0.0000 0.1787 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 699.65 30.23 18.376

FanDuct 0.0000 0.4345 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 824.52 60.59 35.266

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 699.65 30.23 18.376

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 920.26 84.09 51.310

Splitter 6.2459 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 699.65 30.23 18.376

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8788.7 2465.8 4126.2 WB17Y Bleed> 0.4000 1.0000 1.0000 20.3481 516.72 -13.83 9.087

LP_Shaft 1794.4 4826.8 1649.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4850 920.26 84.09 50.129

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 3.0495 920.26 84.09 29.212

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 920.26 84.09 51.310

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 920.26 84.09 51.310

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 920.26 84.09 51.310

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 498.42 -12.55 8.514

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 498.42 -12.55 8.514

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 498.42 -12.55 8.514

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 498.42 -12.55 8.514

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1701.86 0.9995 0.0230 0.25972 0.01155 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.046 0.9801 1.0000 0.9800 613.40 0.256 380.6 364.1

Byp_Nozz 1.263 0.9800 1.0000 0.9800 2006.86 0.587 610.1 6405.2

NASA/TM—2013-218094 N–14
************************************************************************************************************************************ 

Date:05/13/13 Time:07:09:18 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 30/ 58/ 2/27 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 500.30 Stator 1 exit: 502.66 Stator 2 inlet: 504.99 Stator 2 exit: 505.72 

 Stator 3 inlet: 508.44 Stator 3 exit: 508.85 Stator 4 inlet: 511.46 Stator 4 exit: 511.64 

 Stator 5 inlet: 513.24 Stator 5 exit: 513.26 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.53 

Fan Bypass Relative Humidity 5.96 

LPC Inlet Relative Humidity 5.71 

LPC Exit Relative Humidity 3.38 

HPC Relative Humidity 0.04 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 479.99 Fan/LPC Inlet Flow Velocity 173.25 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.18 

Ambient Static Temperature 481.63 Fan/LPC Inlet Static Temperature 498.31 

Additional Water at LPC Exit 0.0012964 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 18.00 386.83 648.6 1.3675 886.97 6.7923 479.99 5.294 0.902 10.000 1654.1 1558.1 1128.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 386.83 9.342 500.81 -13.05 0.0000 597.95 8.149 481.63 2541.8 0.4460 1.40040 0.0004484 386.65 0.173 0.0004

FS1 Inlet.Fl_O 386.83 9.342 500.81 -13.05 0.0000 597.95 8.941 494.56 4168.2 0.2512 1.40040 0.0004484 386.65 0.173 0.0004

FS12 Splitter.Fl_02 337.18 9.337 500.81 -13.05 0.0000 521.48 8.911 494.16 3531.8 0.2592 1.40040 0.0004484 337.03 0.151 0.0004

FS2 Splitter.Fl_01 49.64 9.337 500.81 -13.05 0.0000 76.77 9.175 498.31 830.5 0.1583 1.40040 0.0004484 49.62 0.022 0.0004

FS14 Fan.Fl_O 337.18 9.816 508.83 -11.13 0.0000 500.02 9.029 496.81 2606.7 0.3475 1.40030 0.0004484 337.03 0.151 0.0004

FS23 LPC.Fl_O 49.64 10.441 523.31 -7.65 0.0000 70.18 9.797 513.87 412.6 0.3030 1.40011 0.0004484 49.62 0.022 0.0004

FS24 VaporIN.Fl_O 49.71 10.441 525.12 -14.69 0.0000 70.39 9.792 515.58 412.6 0.3041 1.39991 0.0017448 49.62 0.087 0.0017

FS25 Bleed2.Fl_O 29.82 10.441 525.12 -14.69 0.0000 42.24 10.218 521.89 412.6 0.1760 1.39991 0.0017448 29.77 0.052 0.0017

FS3 HPC.Fl_O 28.38 49.459 890.59 73.96 0.0000 11.05 43.910 861.48 49.7 0.4175 1.38687 0.0017448 28.33 0.049 0.0017

FS36 Bleed3.Fl_O 21.99 49.459 890.59 73.96 0.0000 8.56 46.258 874.11 49.3 0.3120 1.38687 0.0017448 21.95 0.038 0.0017

FS4 Burner.Fl_O 22.24 48.320 1654.07 61.48 0.0112 12.08 45.628 1630.44 74.6 0.2941 1.33416 0.0017448 21.95 0.038 0.0154

FS45 HPT.Fl_O 29.72 14.283 1133.11 -23.80 0.0084 45.20 13.397 1113.81 265.4 0.3073 1.36622 0.0017448 29.42 0.051 0.0120

FS49 LPT.Fl_O 30.07 8.397 1008.63 -53.65 0.0083 73.39 8.273 1004.55 860.2 0.1472 1.37429 0.0017448 29.77 0.052 0.0118

FS5 TEGV.Fl_O 30.07 8.397 1008.70 -53.65 0.0083 73.39 8.273 1004.63 860.2 0.1472 1.37429 0.0017448 29.77 0.052 0.0118

FS8 Core_Nozz.Fl_O 30.07 8.397 1008.77 -53.65 0.0083 73.40 8.149 1000.57 613.4 0.2091 1.37428 0.0017448 29.77 0.052 0.0119

FS17 FanDuctLkg.Fl_O 337.18 9.816 508.83 -11.13 0.0000 500.02 9.029 496.81 2606.7 0.3475 1.40030 0.0004484 337.03 0.151 0.0004

FS171 Bleed15.Fl_O 357.07 9.816 509.73 -11.33 0.0000 529.98 8.815 494.30 2481.9 0.3949 1.40028 0.0005205 356.88 0.186 0.0005

FS172 FanDuct.Fl_O 357.07 9.816 509.73 -11.33 0.0000 529.98 8.815 494.30 2481.9 0.3949 1.40028 0.0005205 356.88 0.186 0.0005

FS173 Byp_Nozz.Fl_O 357.07 9.816 509.73 -11.33 0.0000 529.98 8.149 483.33 2006.9 0.5224 1.40028 0.0005205 356.88 0.186 0.0005

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 521.48 1.051 0.8987 1612.378 1.0160 0.8994 -917.2 -1524.62 44.72

LPC 76.77 1.118 0.7226 1612.378 1.0449 0.7270 -379.1 8.25 1.96

HPC 42.24 4.737 0.7956 8541.451 1.6960 0.8340 -3649.6 68.30 63.08

HPT 12.08 3.383 0.8669 211.319 1.3031 0.8470 3649.6 

LPT 45.20 1.701 0.8009 47.068 1.1199 0.7886 1296.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 605.90 1.050 0.9005 1597.004 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 39.77 1.185 0.7481 0.426 0.0000 1.9307 0.6395 0.9659 0.0003

HPC 38.41 4.561 0.8038 8313.741 10.7568 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.317 0.8669 1.270 3.3171 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.527 0.8069 0.529 1.5272 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–15
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2541.80 5770.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0975 708.95 29.64 14.283

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3489 708.95 29.64 8.397

TEGV 0.0000 0.1472 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 690.65 25.20 19.025

FanDuct 0.0000 0.3949 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 803.76 52.68 34.632

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 690.65 25.20 19.025

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 890.59 73.96 49.459

Splitter 6.7923 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 690.65 25.20 19.025

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8594.4 2230.3 3649.6 WB17Y Bleed> 0.4000 1.0000 1.0000 19.8826 525.12 -14.69 10.441

LP_Shaft 1584.4 4296.9 1296.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4053 890.59 73.96 48.320

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9797 890.59 73.96 28.851

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 890.59 73.96 49.459

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 890.59 73.96 49.459

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 890.59 73.96 49.459

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 508.83 -11.13 9.816

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 508.83 -11.13 9.816

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 508.83 -11.13 9.816

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 508.83 -11.13 9.816

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1654.01 0.9995 0.0230 0.24638 0.01122 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.030 0.9801 1.0000 0.9800 613.40 0.209 315.0 294.4

Byp_Nozz 1.204 0.9800 1.0000 0.9800 2006.86 0.522 551.9 6125.0

NASA/TM—2013-218094 N–16
10μm, ISA +36R 

************************************************************************************************************************************ 

Date:05/13/13 Time:07:26:11 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 483.77 Stator 1 exit: 491.58 Stator 2 inlet: 501.39 Stator 2 exit: 506.41 

 Stator 3 inlet: 516.53 Stator 3 exit: 521.10 Stator 4 inlet: 530.55 Stator 4 exit: 534.44 

 Stator 5 inlet: 542.19 Stator 5 exit: 545.58 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.97 

Fan Bypass Relative Humidity 1.40 

LPC Inlet Relative Humidity 1.30 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 192.08 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 474.85 

Additional Water at LPC Exit 0.0024853 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 252.23 628.1 1.1314 710.62 8.6079 789.49 9.522 0.736 10.000 1767.7 1672.6 1164.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.23 4.267 477.92 -16.44 0.0000 833.95 2.854 425.97 2544.2 0.7800 1.40068 0.0000851 252.21 0.021 0.0001

FS1 Inlet.Fl_O 252.23 4.267 477.92 -16.44 0.0000 833.95 3.891 465.49 4168.2 0.3651 1.40068 0.0000851 252.21 0.021 0.0001

FS12 Splitter.Fl_02 225.98 4.265 477.92 -16.44 0.0000 747.52 3.839 463.75 3531.8 0.3906 1.40068 0.0000851 225.96 0.019 0.0001

FS2 Splitter.Fl_01 26.25 4.265 477.92 -16.44 0.0000 86.84 4.169 474.85 830.5 0.1798 1.40068 0.0000851 26.25 0.002 0.0001

FS14 Fan.Fl_O 225.98 4.821 496.75 -11.93 0.0000 674.16 4.045 472.44 2606.7 0.5068 1.40049 0.0000851 225.96 0.019 0.0001

FS23 LPC.Fl_O 26.25 6.667 555.57 2.19 0.0000 59.90 6.373 548.48 412.6 0.2545 1.39967 0.0000851 26.25 0.002 0.0001

FS24 VaporIN.Fl_O 26.32 6.667 558.88 -11.31 0.0000 60.22 6.369 551.65 412.6 0.2562 1.39927 0.0025704 26.25 0.067 0.0026

FS25 Bleed2.Fl_O 23.69 6.667 558.88 -11.31 0.0000 54.20 6.428 553.10 412.6 0.2288 1.39927 0.0025704 23.63 0.061 0.0026

FS3 HPC.Fl_O 22.54 40.628 1012.12 99.39 0.0000 11.39 35.730 976.89 49.7 0.4351 1.37957 0.0025704 22.48 0.058 0.0026

FS36 Bleed3.Fl_O 17.47 40.628 1012.12 99.39 0.0000 8.83 37.818 992.33 49.3 0.3238 1.37957 0.0025704 17.42 0.045 0.0026

FS4 Burner.Fl_O 17.66 39.693 1767.67 86.54 0.0113 12.07 37.481 1742.72 74.6 0.2947 1.32864 0.0025704 17.42 0.045 0.0163

FS45 HPT.Fl_O 23.61 9.526 1168.62 -20.65 0.0085 54.66 8.628 1138.08 265.4 0.3835 1.36376 0.0025704 23.35 0.060 0.0129

FS49 LPT.Fl_O 23.88 3.263 915.06 -83.10 0.0084 142.89 3.071 899.92 860.2 0.2975 1.37985 0.0025704 23.63 0.061 0.0127

FS5 TEGV.Fl_O 23.88 3.263 915.13 -83.10 0.0084 142.90 3.071 899.99 860.2 0.2975 1.37985 0.0025704 23.63 0.061 0.0128

FS8 Core_Nozz.Fl_O 23.88 3.263 915.20 -83.10 0.0084 142.90 2.854 882.05 613.4 0.4442 1.37984 0.0025704 23.63 0.061 0.0128

FS17 FanDuctLkg.Fl_O 225.98 4.821 496.75 -11.93 0.0000 674.16 4.045 472.44 2606.7 0.5068 1.40049 0.0000851 225.96 0.019 0.0001

FS171 Bleed15.Fl_O 228.61 4.821 497.47 -11.92 0.0000 682.50 3.911 468.59 2481.9 0.5547 1.40048 0.0001136 228.59 0.026 0.0001

FS172 FanDuct.Fl_O 228.61 4.821 497.47 -11.92 0.0000 682.50 3.911 468.59 2481.9 0.5547 1.40048 0.0001136 228.59 0.026 0.0001

FS173 Byp_Nozz.Fl_O 228.61 4.821 497.47 -11.92 0.0000 682.50 2.854 428.18 2006.9 0.8986 1.40048 0.0001136 228.59 0.026 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 747.52 1.130 0.9057 2573.075 1.0394 0.9073 -1443.6 1576.92 54.76

LPC 86.84 1.563 0.8383 2573.075 1.1625 0.8482 -691.9 6.99 3.76

HPC 54.20 6.094 0.8185 8964.236 1.8110 0.8571 -3620.0 61.50 58.17

HPT 12.07 4.167 0.8776 221.323 1.3643 0.8557 3620.0 

LPT 54.66 2.920 0.8565 72.252 1.2754 0.8369 2135.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 868.55 1.127 0.9075 2548.541 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 74.12 1.524 0.7801 0.680 0.0000 1.1716 1.0745 1.0746 0.0003

HPC 49.29 5.854 0.8270 8725.256 10.9657 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.079 0.8776 1.330 4.0789 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.444 0.8628 0.813 2.4440 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–17
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2544.20 6189.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8716 787.61 44.04 9.526

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2771 787.61 44.04 3.263

TEGV 0.0000 0.2975 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 764.88 38.51 14.138

FanDuct 0.0000 0.5547 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 905.01 72.83 27.723

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 764.88 38.51 14.138

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1012.12 99.39 40.628

Splitter 8.6079 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 764.88 38.51 14.138

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9305.2 2043.2 3620.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6318 558.88 -11.31 6.667

LP_Shaft 2469.9 4540.9 2135.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7045 1012.12 99.39 39.693

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3665 1012.12 99.39 22.437

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1012.12 99.39 40.628

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1012.12 99.39 40.628

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1012.12 99.39 40.628

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 496.75 -11.93 4.821

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 496.75 -11.93 4.821

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 496.75 -11.93 4.821

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 496.75 -11.93 4.821

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1767.62 0.9995 0.0230 0.19739 0.01133 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.444 630.1 467.7

Byp_Nozz 1.689 0.9800 1.0000 0.9800 2006.86 0.899 893.6 6349.7

NASA/TM—2013-218094 N–18
************************************************************************************************************************************ 

Date:05/13/13 Time:07:26:26 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.99 Stator 1 exit: 484.31 Stator 2 inlet: 493.48 Stator 2 exit: 498.17 

 Stator 3 inlet: 507.62 Stator 3 exit: 511.87 Stator 4 inlet: 520.70 Stator 4 exit: 524.31 

 Stator 5 inlet: 531.55 Stator 5 exit: 534.68 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.46 

Fan Bypass Relative Humidity 1.80 

LPC Inlet Relative Humidity 1.64 

LPC Exit Relative Humidity 0.17 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 738.88 Fan/LPC Inlet Flow Velocity 185.26 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 468.62 

Additional Water at LPC Exit 0.0022286 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 36.00 245.39 616.1 1.0985 676.77 8.7010 738.88 9.236 0.764 10.000 1739.5 1645.1 1147.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 245.39 4.201 471.48 -17.97 0.0000 818.38 2.947 425.97 2561.4 0.7300 1.40073 0.0000824 245.37 0.020 0.0001

FS1 Inlet.Fl_O 245.39 4.201 471.48 -17.97 0.0000 818.38 3.847 459.73 4168.2 0.3570 1.40073 0.0000824 245.37 0.020 0.0001

FS12 Splitter.Fl_02 220.10 4.199 471.48 -17.97 0.0000 734.39 3.796 458.06 3531.8 0.3823 1.40073 0.0000824 220.08 0.018 0.0001

FS2 Splitter.Fl_01 25.30 4.199 471.48 -17.97 0.0000 84.40 4.111 468.62 830.5 0.1745 1.40073 0.0000824 25.29 0.002 0.0001

FS14 Fan.Fl_O 220.10 4.715 489.02 -13.76 0.0000 666.16 3.978 465.84 2606.7 0.4984 1.40057 0.0000824 220.08 0.018 0.0001

FS23 LPC.Fl_O 25.30 6.425 544.15 -0.54 0.0000 59.26 6.149 537.36 412.6 0.2515 1.39985 0.0000824 25.29 0.002 0.0001

FS24 VaporIN.Fl_O 25.35 6.425 547.17 -12.64 0.0000 59.56 6.145 540.26 412.6 0.2531 1.39949 0.0023110 25.29 0.058 0.0023

FS25 Bleed2.Fl_O 22.82 6.425 547.17 -12.64 0.0000 53.60 6.201 541.64 412.6 0.2261 1.39949 0.0023110 22.76 0.053 0.0023

FS3 HPC.Fl_O 21.71 38.805 989.28 95.17 0.0000 11.36 34.159 955.02 49.7 0.4332 1.38103 0.0023110 21.66 0.050 0.0023

FS36 Bleed3.Fl_O 16.83 38.805 989.28 95.17 0.0000 8.80 36.138 970.02 49.3 0.3226 1.38103 0.0023110 16.79 0.039 0.0023

FS4 Burner.Fl_O 17.01 37.911 1739.52 82.50 0.0112 12.08 35.797 1714.88 74.6 0.2946 1.33005 0.0023110 16.79 0.039 0.0159

FS45 HPT.Fl_O 22.74 9.214 1151.35 -21.86 0.0084 54.03 8.368 1122.01 265.4 0.3779 1.36497 0.0023110 22.50 0.052 0.0125

FS49 LPT.Fl_O 23.00 3.312 912.39 -80.52 0.0083 135.37 3.139 898.97 860.2 0.2801 1.38011 0.0023110 22.76 0.053 0.0124

FS5 TEGV.Fl_O 23.00 3.312 912.46 -80.52 0.0083 135.38 3.139 899.04 860.2 0.2801 1.38010 0.0023110 22.76 0.053 0.0124

FS8 Core_Nozz.Fl_O 23.00 3.312 912.53 -80.52 0.0083 135.38 2.947 883.58 613.4 0.4147 1.38010 0.0023110 22.76 0.053 0.0124

FS17 FanDuctLkg.Fl_O 220.10 4.715 489.02 -13.76 0.0000 666.16 3.978 465.84 2606.7 0.4984 1.40057 0.0000824 220.08 0.018 0.0001

FS171 Bleed15.Fl_O 222.63 4.715 489.68 -13.75 0.0000 674.29 3.853 462.22 2481.9 0.5446 1.40056 0.0001077 222.61 0.024 0.0001

FS172 FanDuct.Fl_O 222.63 4.715 489.68 -13.75 0.0000 674.29 3.853 462.22 2481.9 0.5446 1.40056 0.0001077 222.61 0.024 0.0001

FS173 Byp_Nozz.Fl_O 222.63 4.715 489.68 -13.75 0.0000 674.29 2.947 428.07 2006.9 0.8474 1.40056 0.0001077 222.61 0.024 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 734.39 1.123 0.9049 2508.802 1.0372 0.9065 -1309.5 2134.34 54.63

LPC 84.40 1.530 0.8388 2508.802 1.1542 0.8482 -623.8 6.79 3.36

HPC 53.60 6.039 0.8177 8944.896 1.8080 0.8564 -3395.8 61.41 58.03

HPT 12.08 4.114 0.8763 220.281 1.3611 0.8544 3395.8 

LPT 54.03 2.782 0.8508 70.493 1.2599 0.8316 1933.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 853.29 1.120 0.9067 2484.881 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 71.33 1.495 0.7771 0.663 0.0000 1.1832 1.0700 1.0794 0.0003

HPC 48.75 5.802 0.8262 8706.431 10.9784 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.028 0.8763 1.324 4.0281 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.340 0.8571 0.793 2.3402 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–19
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.41 5635.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8397 770.14 41.26 9.214

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2670 770.14 41.26 3.312

TEGV 0.0000 0.2801 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 747.98 35.87 13.549

FanDuct 0.0000 0.5446 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 884.70 69.29 26.500

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 747.98 35.87 13.549

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 989.28 95.17 38.805

Splitter 8.7010 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 747.98 35.87 13.549

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9187.4 1941.2 3395.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5352 547.17 -12.64 6.425

LP_Shaft 2391.9 4245.2 1933.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6052 989.28 95.17 37.911

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2796 989.28 95.17 21.496

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 989.28 95.17 38.805

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 989.28 95.17 38.805

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 989.28 95.17 38.805

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 489.02 -13.76 4.715

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 489.02 -13.76 4.715

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 489.02 -13.76 4.715

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 489.02 -13.76 4.715

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1739.46 0.9995 0.0230 0.18799 0.01120 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.415 588.7 420.9

Byp_Nozz 1.600 0.9800 1.0000 0.9800 2006.86 0.847 842.6 5830.6

NASA/TM—2013-218094 N–20
************************************************************************************************************************************ 

Date:05/13/13 Time:07:26:42 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 474.90 Stator 1 exit: 482.02 Stator 2 inlet: 490.95 Stator 2 exit: 495.51 

 Stator 3 inlet: 504.71 Stator 3 exit: 508.84 Stator 4 inlet: 517.43 Stator 4 exit: 520.93 

 Stator 5 inlet: 527.97 Stator 5 exit: 531.01 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.63 

Fan Bypass Relative Humidity 1.94 

LPC Inlet Relative Humidity 1.76 

LPC Exit Relative Humidity 0.19 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 722.68 Fan/LPC Inlet Flow Velocity 182.50 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 466.73 

Additional Water at LPC Exit 0.0020327 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 36.00 251.93 628.7 1.0937 687.60 8.7439 722.68 9.107 0.772 10.000 1728.0 1633.9 1140.1

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 251.93 4.339 469.50 -18.42 0.0000 811.77 3.088 425.97 2565.2 0.7140 1.40075 0.0000786 251.91 0.020 0.0001

FS1 Inlet.Fl_O 251.93 4.339 469.50 -18.42 0.0000 811.77 3.980 458.02 4168.2 0.3536 1.40075 0.0000786 251.91 0.020 0.0001

FS12 Splitter.Fl_02 226.07 4.337 469.50 -18.42 0.0000 728.83 3.928 456.38 3531.8 0.3788 1.40075 0.0000786 226.06 0.018 0.0001

FS2 Splitter.Fl_01 25.86 4.337 469.50 -18.42 0.0000 83.35 4.248 466.73 830.5 0.1723 1.40075 0.0000786 25.85 0.002 0.0001

FS14 Fan.Fl_O 226.07 4.856 486.54 -14.34 0.0000 662.72 4.107 463.79 2606.7 0.4948 1.40060 0.0000786 226.06 0.018 0.0001

FS23 LPC.Fl_O 25.86 6.578 540.27 -1.45 0.0000 58.96 6.298 533.60 412.6 0.2501 1.39991 0.0000786 25.85 0.002 0.0001

FS24 VaporIN.Fl_O 25.91 6.578 543.04 -12.48 0.0000 59.23 6.294 536.26 412.6 0.2516 1.39958 0.0021113 25.85 0.055 0.0021

FS25 Bleed2.Fl_O 23.32 6.578 543.04 -12.48 0.0000 53.31 6.350 537.62 412.6 0.2247 1.39958 0.0021113 23.27 0.049 0.0021

FS3 HPC.Fl_O 22.19 39.517 980.74 94.17 0.0000 11.35 34.796 946.82 49.7 0.4326 1.38157 0.0021113 22.14 0.047 0.0021

FS36 Bleed3.Fl_O 17.19 39.517 980.74 94.17 0.0000 8.79 36.806 961.67 49.3 0.3222 1.38157 0.0021113 17.16 0.036 0.0021

FS4 Burner.Fl_O 17.39 38.607 1728.02 81.59 0.0111 12.08 36.454 1703.50 74.6 0.2946 1.33065 0.0021113 17.16 0.036 0.0156

FS45 HPT.Fl_O 23.24 9.427 1144.30 -21.65 0.0083 53.80 8.569 1115.40 265.4 0.3759 1.36548 0.0021113 23.00 0.049 0.0122

FS49 LPT.Fl_O 23.51 3.452 910.93 -78.87 0.0082 132.64 3.279 898.11 860.2 0.2739 1.38025 0.0021113 23.27 0.049 0.0121

FS5 TEGV.Fl_O 23.51 3.452 911.00 -78.87 0.0082 132.64 3.279 898.18 860.2 0.2739 1.38025 0.0021113 23.27 0.049 0.0121

FS8 Core_Nozz.Fl_O 23.51 3.452 911.07 -78.87 0.0082 132.65 3.088 883.55 613.4 0.4043 1.38024 0.0021113 23.27 0.049 0.0121

FS17 FanDuctLkg.Fl_O 226.07 4.856 486.54 -14.34 0.0000 662.72 4.107 463.79 2606.7 0.4948 1.40060 0.0000786 226.06 0.018 0.0001

FS171 Bleed15.Fl_O 228.66 4.856 487.19 -14.32 0.0000 670.75 3.981 460.27 2481.9 0.5403 1.40059 0.0001016 228.64 0.023 0.0001

FS172 FanDuct.Fl_O 228.66 4.856 487.19 -14.32 0.0000 670.75 3.981 460.27 2481.9 0.5403 1.40059 0.0001016 228.64 0.023 0.0001

FS173 Byp_Nozz.Fl_O 228.66 4.856 487.19 -14.32 0.0000 670.75 3.088 428.03 2006.9 0.8304 1.40059 0.0001016 228.64 0.023 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 728.83 1.120 0.9045 2481.637 1.0363 0.9060 -1306.4 2512.84 54.57

LPC 83.35 1.517 0.8389 2481.637 1.1507 0.8481 -620.8 6.70 3.29

HPC 53.31 6.008 0.8172 8935.248 1.8060 0.8559 -3433.3 61.49 58.07

HPT 12.08 4.095 0.8757 219.940 1.3600 0.8537 3433.3 

LPT 53.80 2.731 0.8485 69.798 1.2541 0.8295 1927.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 846.83 1.117 0.9063 2457.975 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.16 1.483 0.7758 0.655 0.0000 1.1881 1.0689 1.0813 0.0003

HPC 48.48 5.772 0.8257 8697.040 10.9773 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.010 0.8757 1.322 4.0097 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.302 0.8548 0.785 2.3019 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–21
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2565.23 5658.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8581 763.74 40.84 9.427

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2728 763.74 40.84 3.452

TEGV 0.0000 0.2739 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 741.80 35.51 13.824

FanDuct 0.0000 0.5403 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 877.17 68.57 27.000

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 741.80 35.51 13.824

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 980.74 94.17 39.517

Splitter 8.7439 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 741.80 35.51 13.824

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9142.8 1972.3 3433.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5908 543.04 -12.48 6.578

LP_Shaft 2361.1 4287.0 1927.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6623 980.74 94.17 38.607

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3296 980.74 94.17 21.916

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 980.74 94.17 39.517

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 980.74 94.17 39.517

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 980.74 94.17 39.517

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.54 -14.34 4.856

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.54 -14.34 4.856

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.54 -14.34 4.856

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.54 -14.34 4.856

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1727.96 0.9995 0.0230 0.19100 0.01113 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.118 0.9801 1.0000 0.9800 613.40 0.404 573.9 419.3

Byp_Nozz 1.572 0.9800 1.0000 0.9800 2006.86 0.830 825.7 5868.1

NASA/TM—2013-218094 N–22
************************************************************************************************************************************ 

Date:05/13/13 Time:07:26:57 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.29 Stator 1 exit: 482.95 Stator 2 inlet: 491.29 Stator 2 exit: 495.54 

 Stator 3 inlet: 504.12 Stator 3 exit: 507.94 Stator 4 inlet: 515.96 Stator 4 exit: 519.18 

 Stator 5 inlet: 525.74 Stator 5 exit: 528.52 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.24 

Fan Bypass Relative Humidity 2.48 

LPC Inlet Relative Humidity 2.22 

LPC Exit Relative Humidity 0.28 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 682.24 Fan/LPC Inlet Flow Velocity 176.05 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 432.42 Fan/LPC Inlet Static Temperature 468.63 

Additional Water at LPC Exit 0.0018496 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 36.00 272.75 675.2 1.0861 733.31 8.8476 682.24 8.731 0.795 10.000 1716.8 1623.0 1134.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 272.75 4.831 471.21 -18.12 0.0000 790.84 3.578 432.42 2577.9 0.6690 1.40074 0.0000968 272.72 0.026 0.0001

FS1 Inlet.Fl_O 272.75 4.831 471.21 -18.12 0.0000 790.84 4.453 460.36 4168.2 0.3430 1.40074 0.0000968 272.72 0.026 0.0001

FS12 Splitter.Fl_02 245.05 4.829 471.21 -18.12 0.0000 710.89 4.398 458.78 3531.8 0.3677 1.40074 0.0000968 245.03 0.024 0.0001

FS2 Splitter.Fl_01 27.70 4.829 471.21 -18.12 0.0000 80.35 4.737 468.63 830.5 0.1658 1.40074 0.0000968 27.69 0.003 0.0001

FS14 Fan.Fl_O 245.05 5.363 487.11 -14.31 0.0000 650.78 4.573 465.39 2606.7 0.4826 1.40059 0.0000968 245.03 0.024 0.0001

FS23 LPC.Fl_O 27.70 7.130 537.35 -2.26 0.0000 58.11 6.835 530.91 412.6 0.2463 1.39995 0.0000968 27.69 0.003 0.0001

FS24 VaporIN.Fl_O 27.75 7.130 539.88 -12.30 0.0000 58.35 6.832 533.35 412.6 0.2475 1.39966 0.0019464 27.69 0.054 0.0019

FS25 Bleed2.Fl_O 24.97 7.130 539.88 -12.30 0.0000 52.52 6.891 534.66 412.6 0.2212 1.39966 0.0019464 24.93 0.049 0.0019

FS3 HPC.Fl_O 23.76 42.182 971.40 92.78 0.0000 11.33 37.160 937.89 49.7 0.4317 1.38216 0.0019464 23.72 0.046 0.0019

FS36 Bleed3.Fl_O 18.42 42.182 971.40 92.78 0.0000 8.78 39.298 952.55 49.3 0.3216 1.38216 0.0019464 18.38 0.036 0.0019

FS4 Burner.Fl_O 18.62 41.210 1716.81 80.27 0.0111 12.08 38.912 1692.45 74.6 0.2945 1.33124 0.0019464 18.38 0.036 0.0154

FS45 HPT.Fl_O 24.89 10.178 1139.03 -21.42 0.0083 53.25 9.274 1110.94 265.4 0.3712 1.36587 0.0019464 24.63 0.048 0.0120

FS49 LPT.Fl_O 25.18 3.940 919.16 -75.23 0.0082 125.00 3.766 907.78 860.2 0.2568 1.37981 0.0019464 24.93 0.049 0.0119

FS5 TEGV.Fl_O 25.18 3.940 919.23 -75.23 0.0082 125.01 3.766 907.85 860.2 0.2568 1.37981 0.0019464 24.93 0.049 0.0119

FS8 Core_Nozz.Fl_O 25.18 3.940 919.30 -75.23 0.0082 125.01 3.578 895.18 613.5 0.3762 1.37980 0.0019464 24.93 0.049 0.0119

FS17 FanDuctLkg.Fl_O 245.05 5.363 487.11 -14.31 0.0000 650.78 4.573 465.39 2606.7 0.4826 1.40059 0.0000968 245.03 0.024 0.0001

FS171 Bleed15.Fl_O 247.83 5.363 487.70 -14.28 0.0000 658.55 4.442 462.10 2481.9 0.5258 1.40058 0.0001175 247.80 0.029 0.0001

FS172 FanDuct.Fl_O 247.83 5.363 487.70 -14.28 0.0000 658.55 4.442 462.10 2481.9 0.5258 1.40058 0.0001175 247.80 0.029 0.0001

FS173 Byp_Nozz.Fl_O 247.83 5.363 487.70 -14.28 0.0000 658.55 3.578 434.38 2006.9 0.7826 1.40058 0.0001175 247.80 0.029 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.89 1.111 0.9034 2399.012 1.0337 0.9048 -1320.9 5509.81 54.17

LPC 80.35 1.477 0.8398 2399.012 1.1404 0.8483 -621.5 6.42 3.06

HPC 52.52 5.916 0.8157 8909.373 1.7993 0.8544 -3622.8 61.89 58.39

HPT 12.08 4.049 0.8750 219.376 1.3567 0.8530 3622.8 

LPT 53.25 2.583 0.8433 67.753 1.2370 0.8248 1942.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.99 1.108 0.9052 2376.137 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.58 1.446 0.7720 0.634 0.0000 1.2067 1.0675 1.0878 0.0003

HPC 47.77 5.685 0.8241 8671.855 10.9625 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.964 0.8750 1.318 3.9644 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.191 0.8496 0.762 2.1907 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–23
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2577.87 5783.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9190 757.41 40.24 10.178

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2922 757.41 40.24 3.940

TEGV 0.0000 0.2568 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 735.78 34.99 14.841

FanDuct 0.0000 0.5258 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 869.24 67.56 28.862

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 735.78 34.99 14.841

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 971.40 92.78 42.182

Splitter 8.8476 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 735.78 34.99 14.841

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9089.7 2093.3 3622.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7748 539.88 -12.30 7.130

LP_Shaft 2286.6 4461.6 1942.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8515 971.40 92.78 41.210

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4951 971.40 92.78 23.460

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 971.40 92.78 42.182

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 971.40 92.78 42.182

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 971.40 92.78 42.182

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 487.11 -14.31 5.363

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 487.11 -14.31 5.363

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 487.11 -14.31 5.363

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 487.11 -14.31 5.363

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1716.76 0.9995 0.0230 0.20370 0.01108 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.101 0.9801 1.0000 0.9800 613.40 0.376 537.4 420.6

Byp_Nozz 1.499 0.9800 1.0000 0.9800 2006.86 0.783 783.9 6038.1

NASA/TM—2013-218094 N–24
************************************************************************************************************************************ 

Date:05/13/13 Time:07:27:15 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 15/ 29/ 1/13 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.57 Stator 1 exit: 490.29 Stator 2 inlet: 497.36 Stator 2 exit: 500.79 

 Stator 3 inlet: 508.16 Stator 3 exit: 511.17 Stator 4 inlet: 518.10 Stator 4 exit: 520.59 

 Stator 5 inlet: 526.17 Stator 5 exit: 528.27 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.19 

Fan Bypass Relative Humidity 3.36 

LPC Inlet Relative Humidity 3.05 

LPC Exit Relative Humidity 0.57 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 630.80 Fan/LPC Inlet Flow Velocity 176.82 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 447.58 Fan/LPC Inlet Static Temperature 478.13 

Additional Water at LPC Exit 0.0018320 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 36.00 298.22 718.6 1.1019 791.89 8.4428 630.80 8.114 0.827 10.000 1714.5 1620.4 1136.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 298.22 5.595 480.74 -16.28 0.0000 754.13 4.358 447.58 2590.5 0.6080 1.40064 0.0001750 298.17 0.052 0.0002

FS1 Inlet.Fl_O 298.22 5.595 480.74 -16.28 0.0000 754.13 5.201 470.79 4168.2 0.3248 1.40064 0.0001750 298.17 0.052 0.0002

FS12 Splitter.Fl_02 266.64 5.592 480.74 -16.28 0.0000 674.60 5.148 469.49 3531.8 0.3457 1.40064 0.0001750 266.60 0.047 0.0002

FS2 Splitter.Fl_01 31.58 5.592 480.74 -16.28 0.0000 79.90 5.487 478.13 830.5 0.1649 1.40064 0.0001750 31.58 0.006 0.0002

FS14 Fan.Fl_O 266.64 6.134 495.01 -12.86 0.0000 624.13 5.317 475.19 2606.7 0.4563 1.40050 0.0001750 266.60 0.047 0.0002

FS23 LPC.Fl_O 31.58 7.815 537.27 -2.73 0.0000 60.45 7.464 530.27 412.6 0.2570 1.39994 0.0001750 31.58 0.006 0.0002

FS24 VaporIN.Fl_O 31.64 7.815 539.78 -12.67 0.0000 60.70 7.461 532.67 412.6 0.2583 1.39965 0.0020069 31.58 0.063 0.0020

FS25 Bleed2.Fl_O 26.89 7.815 539.78 -12.67 0.0000 51.59 7.563 534.74 412.6 0.2170 1.39965 0.0020069 26.84 0.054 0.0020

FS3 HPC.Fl_O 25.59 45.396 966.66 91.26 0.0000 11.31 40.015 933.44 49.7 0.4307 1.38243 0.0020069 25.54 0.051 0.0020

FS36 Bleed3.Fl_O 19.83 45.396 966.66 91.26 0.0000 8.76 42.305 947.96 49.3 0.3209 1.38243 0.0020069 19.79 0.040 0.0020

FS4 Burner.Fl_O 20.05 44.351 1714.49 78.73 0.0111 12.08 41.878 1690.16 74.6 0.2945 1.33132 0.0020069 19.79 0.040 0.0155

FS45 HPT.Fl_O 26.80 11.115 1140.52 -21.80 0.0083 52.54 10.156 1113.25 265.4 0.3654 1.36575 0.0020069 26.53 0.053 0.0121

FS49 LPT.Fl_O 27.11 4.711 941.00 -70.55 0.0082 113.93 4.540 931.46 860.2 0.2325 1.37848 0.0020069 26.84 0.054 0.0120

FS5 TEGV.Fl_O 27.11 4.711 941.07 -70.55 0.0082 113.93 4.540 931.53 860.2 0.2325 1.37848 0.0020069 26.84 0.054 0.0120

FS8 Core_Nozz.Fl_O 27.11 4.711 941.14 -70.55 0.0082 113.94 4.358 921.23 613.4 0.3376 1.37847 0.0020069 26.84 0.054 0.0120

FS17 FanDuctLkg.Fl_O 266.64 6.134 495.01 -12.86 0.0000 624.13 5.317 475.19 2606.7 0.4563 1.40050 0.0001750 266.60 0.047 0.0002

FS171 Bleed15.Fl_O 271.39 6.134 495.80 -12.86 0.0000 635.74 5.170 472.15 2481.9 0.5000 1.40048 0.0002070 271.33 0.056 0.0002

FS172 FanDuct.Fl_O 271.39 6.134 495.80 -12.86 0.0000 635.74 5.170 472.15 2481.9 0.5000 1.40048 0.0002070 271.33 0.056 0.0002

FS173 Byp_Nozz.Fl_O 271.39 6.134 495.80 -12.86 0.0000 635.74 4.358 449.63 2006.9 0.7159 1.40048 0.0002070 271.33 0.056 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 674.60 1.097 0.9017 2242.889 1.0297 0.9030 -1291.2 -8700.18 52.77

LPC 79.90 1.397 0.8538 2242.889 1.1176 0.8605 -605.9 5.97 2.61

HPC 51.59 5.809 0.8137 8878.896 1.7908 0.8526 -3858.9 62.39 58.77

HPT 12.08 3.990 0.8747 218.753 1.3522 0.8529 3858.9 

LPT 52.54 2.359 0.8343 63.939 1.2096 0.8170 1897.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 783.82 1.095 0.9035 2221.503 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 60.10 1.380 0.7653 0.592 0.0000 1.3295 1.0471 1.1156 0.0003

HPC 46.92 5.582 0.8222 8642.190 10.9446 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.907 0.8746 1.315 3.9072 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.022 0.8405 0.719 2.0225 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–25
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2590.54 5846.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9897 754.94 39.30 11.115

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3147 754.94 39.30 4.711

TEGV 0.0000 0.2325 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 733.54 34.10 16.083

FanDuct 0.0000 0.5000 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.58 66.32 31.115

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 733.54 34.10 16.083

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 966.66 91.26 45.396

Splitter 8.4428 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 733.54 34.10 16.083

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9057.8 2237.6 3858.9 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7460 539.78 -12.67 7.815

LP_Shaft 2159.3 4614.3 1897.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.0708 966.66 91.26 44.351

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.6870 966.66 91.26 25.340

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.66 91.26 45.396

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.66 91.26 45.396

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.66 91.26 45.396

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 495.01 -12.86 6.134

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 495.01 -12.86 6.134

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 495.01 -12.86 6.134

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 495.01 -12.86 6.134

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1714.43 0.9995 0.0230 0.21997 0.01111 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.081 0.9801 1.0000 0.9800 613.40 0.338 489.0 412.1

Byp_Nozz 1.407 0.9800 1.0000 0.9800 2006.86 0.716 729.5 6153.4

NASA/TM—2013-218094 N–26
************************************************************************************************************************************ 

Date:05/13/13 Time:07:27:45 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 50/ 2/19 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 492.34 Stator 1 exit: 496.52 Stator 2 inlet: 501.28 Stator 2 exit: 503.16 

 Stator 3 inlet: 508.43 Stator 3 exit: 509.89 Stator 4 inlet: 514.95 Stator 4 exit: 516.00 

 Stator 5 inlet: 519.70 Stator 5 exit: 520.47 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.02 

Fan Bypass Relative Humidity 4.20 

LPC Inlet Relative Humidity 4.03 

LPC Exit Relative Humidity 1.36 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 582.56 Fan/LPC Inlet Flow Velocity 195.14 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 463.14 Fan/LPC Inlet Static Temperature 488.24 

Additional Water at LPC Exit 0.0016385 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 36.00 322.38 718.6 1.1634 836.02 7.1400 582.56 7.201 0.857 10.000 1718.4 1622.2 1143.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 322.38 6.516 491.41 -14.47 0.0000 707.72 5.297 463.14 2581.9 0.5520 1.40052 0.0003043 322.28 0.098 0.0003

FS1 Inlet.Fl_O 322.38 6.516 491.41 -14.47 0.0000 707.72 6.116 482.58 4168.2 0.3023 1.40052 0.0003043 322.28 0.098 0.0003

FS12 Splitter.Fl_02 282.78 6.513 491.41 -14.47 0.0000 621.08 6.081 481.87 3531.8 0.3145 1.40052 0.0003043 282.69 0.086 0.0003

FS2 Splitter.Fl_01 39.60 6.513 491.41 -14.47 0.0000 86.99 6.367 488.24 830.5 0.1801 1.40052 0.0003043 39.59 0.012 0.0003

FS14 Fan.Fl_O 282.78 7.042 503.71 -11.52 0.0000 581.59 6.248 486.77 2606.7 0.4169 1.40038 0.0003043 282.69 0.086 0.0003

FS23 LPC.Fl_O 39.60 8.195 531.87 -4.77 0.0000 71.92 7.662 521.75 412.6 0.3114 1.40001 0.0003043 39.59 0.012 0.0003

FS24 VaporIN.Fl_O 39.67 8.195 534.13 -13.66 0.0000 72.19 7.657 523.87 412.6 0.3129 1.39975 0.0019428 39.59 0.077 0.0019

FS25 Bleed2.Fl_O 27.77 8.195 534.13 -13.66 0.0000 50.53 7.942 529.36 412.6 0.2123 1.39975 0.0019428 27.72 0.054 0.0019

FS3 HPC.Fl_O 26.42 46.925 953.42 88.34 0.0000 11.22 41.467 921.25 49.7 0.4262 1.38323 0.0019428 26.37 0.051 0.0019

FS36 Bleed3.Fl_O 20.48 46.925 953.42 88.34 0.0000 8.69 43.785 935.28 49.3 0.3179 1.38323 0.0019428 20.44 0.040 0.0019

FS4 Burner.Fl_O 20.71 45.844 1718.39 75.56 0.0114 12.08 43.287 1694.00 74.6 0.2947 1.33097 0.0019428 20.44 0.040 0.0157

FS45 HPT.Fl_O 27.68 11.875 1148.20 -22.96 0.0085 50.96 10.918 1122.64 265.4 0.3526 1.36514 0.0019428 27.39 0.053 0.0123

FS49 LPT.Fl_O 28.00 5.616 972.42 -65.77 0.0084 100.33 5.459 964.90 860.2 0.2034 1.37646 0.0019428 27.72 0.054 0.0122

FS5 TEGV.Fl_O 28.00 5.616 972.49 -65.77 0.0084 100.33 5.459 964.97 860.2 0.2034 1.37646 0.0019428 27.72 0.054 0.0122

FS8 Core_Nozz.Fl_O 28.00 5.616 972.56 -65.77 0.0084 100.33 5.297 957.10 613.4 0.2927 1.37645 0.0019428 27.72 0.054 0.0122

FS17 FanDuctLkg.Fl_O 282.78 7.042 503.71 -11.52 0.0000 581.59 6.248 486.77 2606.7 0.4169 1.40038 0.0003043 282.69 0.086 0.0003

FS171 Bleed15.Fl_O 294.68 7.042 504.94 -11.61 0.0000 606.81 6.055 483.62 2481.9 0.4692 1.40036 0.0003704 294.57 0.109 0.0004

FS172 FanDuct.Fl_O 294.68 7.042 504.94 -11.61 0.0000 606.81 6.055 483.62 2481.9 0.4692 1.40036 0.0003704 294.57 0.109 0.0004

FS173 Byp_Nozz.Fl_O 294.68 7.042 504.94 -11.61 0.0000 606.81 5.297 465.46 2006.9 0.6508 1.40036 0.0003704 294.57 0.109 0.0004

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 621.08 1.081 0.9019 2028.608 1.0250 0.9030 -1180.0 -2623.37 49.99

LPC 86.99 1.258 0.8246 2028.608 1.0823 0.8302 -543.8 6.42 2.41

HPC 50.53 5.726 0.8120 8845.140 1.7850 0.8510 -3910.4 61.84 58.11

HPT 12.08 3.860 0.8755 216.532 1.3427 0.8545 3910.3 

LPT 50.96 2.114 0.8239 58.273 1.1779 0.8081 1723.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 721.64 1.079 0.9038 2009.265 0.0424 0.8607 1.0235 0.9980 0.9905

LPC 52.94 1.306 0.7604 0.536 0.0000 1.6433 0.8452 1.0844 0.0003

HPC 45.96 5.503 0.8204 8609.335 10.9922 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.781 0.8755 1.301 3.7812 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.838 0.8300 0.656 1.8382 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–27
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2581.91 5837.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0219 745.39 37.34 11.875

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3249 745.39 37.34 5.616

TEGV 0.0000 0.2034 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 724.38 32.24 16.716

FanDuct 0.0000 0.4692 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 854.08 63.86 32.208

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 724.38 32.24 16.716

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 953.42 88.34 46.925

Splitter 7.1400 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 724.38 32.24 16.716

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8976.0 2288.0 3910.3 WB17Y Bleed> 0.3000 1.0000 1.0000 11.9010 534.13 -13.66 8.195

LP_Shaft 1974.6 4585.0 1723.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1707 953.42 88.34 45.844

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7744 953.42 88.34 26.414

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 953.42 88.34 46.925

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 953.42 88.34 46.925

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 953.42 88.34 46.925

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 503.71 -11.52 7.042

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 503.71 -11.52 7.042

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 503.71 -11.52 7.042

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 503.71 -11.52 7.042

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1718.34 0.9995 0.0230 0.23223 0.01136 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.060 0.9801 1.0000 0.9800 613.40 0.293 431.7 375.7

Byp_Nozz 1.329 0.9800 1.0000 0.9800 2006.86 0.651 674.8 6180.1

NASA/TM—2013-218094 N–28
************************************************************************************************************************************ 

Date:05/13/13 Time:07:28:17 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 29/ 57/ 2/26 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 505.27 Stator 1 exit: 508.26 Stator 2 inlet: 511.07 Stator 2 exit: 511.88 

 Stator 3 inlet: 515.27 Stator 3 exit: 515.65 Stator 4 inlet: 518.94 Stator 4 exit: 519.02 

 Stator 5 inlet: 520.94 Stator 5 exit: 520.82 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.01 

Fan Bypass Relative Humidity 5.18 

LPC Inlet Relative Humidity 5.20 

LPC Exit Relative Humidity 2.82 

HPC Relative Humidity 0.03 

Drop Diameter 0.0000100 Inlet Length 40.00 

Ambient Flow Velocity 528.20 Fan/LPC Inlet Flow Velocity 202.80 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 483.18 Fan/LPC Inlet Static Temperature 502.99 

Additional Water at LPC Exit 0.0016391 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 36.00 357.84 772.0 1.1870 916.37 6.3566 528.20 6.264 0.888 10.000 1742.0 1642.4 1169.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 357.84 7.943 506.41 -12.46 0.0000 654.18 6.740 483.18 2591.9 0.4900 1.40031 0.0005787 357.63 0.207 0.0006

FS1 Inlet.Fl_O 357.84 7.943 506.41 -12.46 0.0000 654.18 7.530 498.74 4168.2 0.2771 1.40031 0.0005787 357.63 0.207 0.0006

FS12 Splitter.Fl_02 309.20 7.939 506.41 -12.46 0.0000 565.54 7.509 498.40 3531.8 0.2833 1.40031 0.0005787 309.02 0.179 0.0006

FS2 Splitter.Fl_01 48.64 7.939 506.41 -12.46 0.0000 88.97 7.753 502.99 830.5 0.1844 1.40031 0.0005787 48.61 0.028 0.0006

FS14 Fan.Fl_O 309.20 8.483 517.12 -9.89 0.0000 534.86 7.693 502.86 2606.7 0.3763 1.40017 0.0005787 309.02 0.179 0.0006

FS23 LPC.Fl_O 48.64 9.069 534.49 -5.72 0.0000 80.02 8.324 521.56 412.6 0.3520 1.39993 0.0005787 48.61 0.028 0.0006

FS24 VaporIN.Fl_O 48.72 9.069 536.74 -14.61 0.0000 80.32 8.317 523.64 412.6 0.3538 1.39967 0.0022178 48.61 0.108 0.0022

FS25 Bleed2.Fl_O 29.23 9.069 536.74 -14.61 0.0000 48.19 8.814 532.40 412.6 0.2020 1.39967 0.0022178 29.17 0.065 0.0022

FS3 HPC.Fl_O 27.82 49.753 947.33 85.28 0.0000 11.10 44.103 916.15 49.7 0.4207 1.38355 0.0022178 27.75 0.062 0.0022

FS36 Bleed3.Fl_O 21.56 49.753 947.33 85.28 0.0000 8.61 46.497 929.71 49.3 0.3142 1.38355 0.0022178 21.51 0.048 0.0022

FS4 Burner.Fl_O 21.81 48.608 1742.04 72.01 0.0118 12.09 45.894 1717.37 74.6 0.2949 1.32952 0.0022178 21.51 0.048 0.0166

FS45 HPT.Fl_O 29.15 13.295 1174.54 -24.25 0.0088 48.48 12.335 1151.28 265.4 0.3332 1.36317 0.0022178 28.83 0.064 0.0130

FS49 LPT.Fl_O 29.49 7.032 1020.75 -61.62 0.0087 86.45 6.887 1014.99 860.2 0.1743 1.37316 0.0022178 29.17 0.065 0.0129

FS5 TEGV.Fl_O 29.49 7.032 1020.82 -61.62 0.0087 86.46 6.887 1015.06 860.2 0.1743 1.37315 0.0022178 29.17 0.065 0.0129

FS8 Core_Nozz.Fl_O 29.49 7.032 1020.89 -61.62 0.0087 86.46 6.740 1009.20 613.4 0.2491 1.37315 0.0022178 29.17 0.065 0.0129

FS17 FanDuctLkg.Fl_O 309.20 8.483 517.12 -9.89 0.0000 534.86 7.693 502.86 2606.7 0.3763 1.40017 0.0005787 309.02 0.179 0.0006

FS171 Bleed15.Fl_O 328.68 8.483 518.28 -10.17 0.0000 569.22 7.463 499.64 2481.9 0.4317 1.40015 0.0006757 328.46 0.222 0.0007

FS172 FanDuct.Fl_O 328.68 8.483 518.28 -10.17 0.0000 569.22 7.463 499.64 2481.9 0.4317 1.40015 0.0006757 328.46 0.222 0.0007

FS173 Byp_Nozz.Fl_O 328.68 8.483 518.28 -10.17 0.0000 569.22 6.740 485.31 2006.9 0.5826 1.40015 0.0006757 328.46 0.222 0.0007

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 565.54 1.068 0.9037 1818.644 1.0211 0.9046 -1124.1 -1837.84 46.55

LPC 88.97 1.142 0.6988 1818.644 1.0554 0.7044 -463.8 7.11 2.05

HPC 48.19 5.486 0.8076 8765.766 1.7650 0.8467 -4031.4 62.22 58.20

HPT 12.09 3.656 0.8769 213.647 1.3264 0.8570 4031.4 

LPT 48.48 1.891 0.8158 52.435 1.1473 0.8020 1587.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 657.10 1.067 0.9056 1801.304 0.0437 0.8607 1.0235 0.9980 0.9905

LPC 46.11 1.239 0.7548 0.480 0.0000 1.9294 0.5948 0.9257 0.0003

HPC 43.83 5.275 0.8160 8532.076 11.0030 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.582 0.8769 1.284 3.5824 12.6299 0.9723 1.0000 0.0003

LPT 0.74 1.670 0.8218 0.590 1.6699 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–29
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2591.91 5874.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0758 743.58 35.33 13.295

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3420 743.58 35.33 7.032

TEGV 0.0000 0.1743 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 723.00 30.34 18.019

FanDuct 0.0000 0.4317 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 850.02 61.31 34.293

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 723.00 30.34 18.019

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 947.33 85.28 49.753

Splitter 6.3566 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 723.00 30.34 18.019

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8917.2 2374.4 4031.4 WB17Y Bleed> 0.4000 1.0000 1.0000 19.4886 536.74 -14.61 9.069

LP_Shaft 1797.0 4640.9 1587.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3378 947.33 85.28 48.608

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9207 947.33 85.28 28.409

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 947.33 85.28 49.753

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 947.33 85.28 49.753

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 947.33 85.28 49.753

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 517.12 -9.89 8.483

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 517.12 -9.89 8.483

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 517.12 -9.89 8.483

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 517.12 -9.89 8.483

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1741.99 0.9995 0.0230 0.25455 0.01183 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.043 0.9801 1.0000 0.9800 613.40 0.249 376.8 345.3

Byp_Nozz 1.259 0.9800 1.0000 0.9800 2006.86 0.583 616.8 6301.3

NASA/TM—2013-218094 N–30
25μm, ISA +18R 

************************************************************************************************************************************ 

Date:05/13/13 Time:09:35:49 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 463.25 Stator 1 exit: 470.65 Stator 2 inlet: 479.96 Stator 2 exit: 484.71 

 Stator 3 inlet: 494.33 Stator 3 exit: 498.66 Stator 4 inlet: 507.66 Stator 4 exit: 511.34 

 Stator 5 inlet: 518.73 Stator 5 exit: 521.95 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.76 

Fan Bypass Relative Humidity 1.24 

LPC Inlet Relative Humidity 1.13 

LPC Exit Relative Humidity 0.10 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 187.85 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 454.80 

Additional Water at LPC Exit 0.0002383 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 257.27 609.3 1.1329 690.29 8.5968 772.64 9.489 0.736 10.000 1694.0 1602.0 1113.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.27 4.267 457.74 -20.96 0.0000 832.43 2.854 407.97 2539.5 0.7800 1.40084 0.0000295 257.26 0.008 0.0000

FS1 Inlet.Fl_O 257.27 4.267 457.74 -20.96 0.0000 832.43 3.893 445.88 4168.2 0.3642 1.40084 0.0000295 257.26 0.008 0.0000

FS12 Splitter.Fl_02 230.46 4.265 457.74 -20.96 0.0000 746.07 3.841 444.22 3531.8 0.3896 1.40084 0.0000295 230.46 0.007 0.0000

FS2 Splitter.Fl_01 26.81 4.265 457.74 -20.96 0.0000 86.78 4.170 454.80 830.5 0.1796 1.40084 0.0000295 26.81 0.001 0.0000

FS14 Fan.Fl_O 230.46 4.811 475.50 -16.70 0.0000 674.00 4.038 452.24 2606.7 0.5066 1.40071 0.0000295 230.46 0.007 0.0000

FS23 LPC.Fl_O 26.81 6.640 531.29 -3.32 0.0000 60.05 6.346 524.46 412.6 0.2551 1.40005 0.0000295 26.81 0.001 0.0000

FS24 VaporIN.Fl_O 26.81 6.640 531.65 -4.61 0.0000 60.08 6.346 524.80 412.6 0.2553 1.40001 0.0002677 26.81 0.007 0.0003

FS25 Bleed2.Fl_O 24.13 6.640 531.65 -4.61 0.0000 54.08 6.404 526.17 412.6 0.2280 1.40001 0.0002677 24.13 0.006 0.0003

FS3 HPC.Fl_O 22.96 40.489 964.75 100.64 0.0000 11.37 35.638 931.20 49.7 0.4331 1.38282 0.0002677 22.96 0.006 0.0003

FS36 Bleed3.Fl_O 17.80 40.489 964.75 100.64 0.0000 8.81 37.704 945.89 49.3 0.3225 1.38282 0.0002677 17.79 0.005 0.0003

FS4 Burner.Fl_O 17.99 39.556 1694.00 88.37 0.0108 12.08 37.354 1669.90 74.6 0.2941 1.33277 0.0002677 17.79 0.005 0.0134

FS45 HPT.Fl_O 24.04 9.490 1117.39 -13.58 0.0080 54.65 8.597 1088.04 265.4 0.3824 1.36768 0.0002677 23.84 0.006 0.0101

FS49 LPT.Fl_O 24.32 3.259 875.68 -72.60 0.0079 142.53 3.069 861.21 860.2 0.2961 1.38271 0.0002677 24.13 0.006 0.0100

FS5 TEGV.Fl_O 24.32 3.259 875.75 -72.60 0.0079 142.54 3.069 861.29 860.2 0.2961 1.38270 0.0002677 24.13 0.006 0.0100

FS8 Core_Nozz.Fl_O 24.32 3.259 875.82 -72.60 0.0079 142.54 2.854 844.20 613.4 0.4418 1.38270 0.0002677 24.13 0.006 0.0100

FS17 FanDuctLkg.Fl_O 230.46 4.811 475.50 -16.70 0.0000 674.00 4.038 452.24 2606.7 0.5066 1.40071 0.0000295 230.46 0.007 0.0000

FS171 Bleed15.Fl_O 233.14 4.811 476.14 -16.56 0.0000 682.31 3.904 448.52 2481.9 0.5544 1.40070 0.0000322 233.14 0.008 0.0000

FS172 FanDuct.Fl_O 233.14 4.811 476.14 -16.56 0.0000 682.31 3.904 448.52 2481.9 0.5544 1.40070 0.0000322 233.14 0.008 0.0000

FS173 Byp_Nozz.Fl_O 233.14 4.811 476.14 -16.56 0.0000 682.31 2.854 410.04 2006.9 0.8967 1.40070 0.0000322 233.14 0.008 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.07 1.128 0.9051 2561.318 1.0388 0.9068 -1387.4 1659.17 54.93

LPC 86.78 1.557 0.8401 2561.318 1.1607 0.8498 -668.8 6.95 3.68

HPC 54.08 6.098 0.8186 8960.575 1.8147 0.8574 -3506.7 61.09 57.76

HPT 12.08 4.168 0.8739 220.416 1.3661 0.8513 3506.7 

LPT 54.65 2.912 0.8507 71.982 1.2742 0.8305 2056.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 866.85 1.125 0.9070 2536.896 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 73.61 1.519 0.7796 0.677 0.0000 1.1790 1.0734 1.0776 0.0003

HPC 49.18 5.857 0.8271 8721.692 10.9923 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.081 0.8739 1.325 4.0806 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.438 0.8570 0.810 2.4380 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–31
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2539.48 6178.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8881 749.94 48.02 9.490

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2824 749.94 48.02 3.259

TEGV 0.0000 0.2961 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 728.23 42.75 14.087

FanDuct 0.0000 0.5544 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 862.20 75.38 27.626

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 728.23 42.75 14.087

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 964.75 100.64 40.489

Splitter 8.5968 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 728.23 42.75 14.087

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9072.0 2030.2 3506.7 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6814 531.65 -4.61 6.640

LP_Shaft 2406.2 4488.1 2056.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7555 964.75 100.64 39.556

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4111 964.75 100.64 22.358

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.75 100.64 40.489

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.75 100.64 40.489

 WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.75 100.64 40.489

 WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.50 -16.70 4.811

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.50 -16.70 4.811

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.50 -16.70 4.811

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.50 -16.70 4.811

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1693.94 0.9995 0.0230 0.19175 0.01078 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.142 0.9801 1.0000 0.9800 613.40 0.442 613.3 463.7

Byp_Nozz 1.686 0.9800 1.0000 0.9800 2006.86 0.897 872.7 6323.8

NASA/TM—2013-218094 N–32
************************************************************************************************************************************ 

Date:05/13/13 Time:09:36:06 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.76 Stator 1 exit: 463.70 Stator 2 inlet: 472.41 Stator 2 exit: 476.85 

 Stator 3 inlet: 485.85 Stator 3 exit: 489.87 Stator 4 inlet: 498.28 Stator 4 exit: 501.69 

 Stator 5 inlet: 508.59 Stator 5 exit: 511.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.23 

Fan Bypass Relative Humidity 1.61 

LPC Inlet Relative Humidity 1.45 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 723.11 Fan/LPC Inlet Flow Velocity 181.19 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 448.83 

Additional Water at LPC Exit 0.0002037 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 18.00 250.31 599.9 1.0971 658.20 8.6897 723.11 9.210 0.763 10.000 1667.8 1576.4 1097.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 250.31 4.201 451.57 -22.43 0.0000 816.96 2.947 407.97 2556.9 0.7300 1.40089 0.0000285 250.31 0.007 0.0000

FS1 Inlet.Fl_O 250.31 4.201 451.57 -22.43 0.0000 816.96 3.848 440.36 4168.2 0.3563 1.40089 0.0000285 250.31 0.007 0.0000

FS12 Splitter.Fl_02 224.48 4.199 451.57 -22.43 0.0000 733.02 3.798 438.77 3531.8 0.3814 1.40089 0.0000285 224.47 0.006 0.0000

FS2 Splitter.Fl_01 25.83 4.199 451.57 -22.43 0.0000 84.35 4.111 448.83 830.5 0.1744 1.40089 0.0000285 25.83 0.001 0.0000

FS14 Fan.Fl_O 224.48 4.707 468.13 -18.46 0.0000 665.90 3.972 445.95 2606.7 0.4981 1.40077 0.0000285 224.47 0.006 0.0000

FS23 LPC.Fl_O 25.83 6.403 520.46 -5.92 0.0000 59.40 6.126 513.92 412.6 0.2521 1.40021 0.0000285 25.83 0.001 0.0000

FS24 VaporIN.Fl_O 25.84 6.403 520.77 -7.02 0.0000 59.43 6.125 514.22 412.6 0.2523 1.40018 0.0002323 25.83 0.006 0.0002

FS25 Bleed2.Fl_O 23.25 6.403 520.77 -7.02 0.0000 53.48 6.180 515.53 412.6 0.2253 1.40018 0.0002323 23.25 0.005 0.0002

FS3 HPC.Fl_O 22.13 38.693 943.36 95.55 0.0000 11.33 34.090 910.72 49.7 0.4313 1.38409 0.0002323 22.12 0.005 0.0002

FS36 Bleed3.Fl_O 17.15 38.693 943.36 95.55 0.0000 8.78 36.049 924.99 49.3 0.3213 1.38409 0.0002323 17.14 0.004 0.0002

FS4 Burner.Fl_O 17.33 37.802 1667.78 83.45 0.0107 12.08 35.696 1643.97 74.6 0.2941 1.33411 0.0002323 17.14 0.004 0.0132

FS45 HPT.Fl_O 23.17 9.183 1101.44 -15.86 0.0080 54.02 8.342 1073.22 265.4 0.3770 1.36878 0.0002323 22.98 0.005 0.0100

FS49 LPT.Fl_O 23.44 3.309 873.50 -71.37 0.0079 135.07 3.137 860.67 860.2 0.2789 1.38289 0.0002323 23.25 0.005 0.0099

FS5 TEGV.Fl_O 23.44 3.309 873.57 -71.37 0.0079 135.07 3.137 860.74 860.2 0.2789 1.38288 0.0002323 23.25 0.005 0.0099

FS8 Core_Nozz.Fl_O 23.44 3.309 873.65 -71.37 0.0079 135.08 2.947 845.99 613.4 0.4128 1.38288 0.0002323 23.25 0.005 0.0099

FS17 FanDuctLkg.Fl_O 224.48 4.707 468.13 -18.46 0.0000 665.90 3.972 445.95 2606.7 0.4981 1.40077 0.0000285 224.47 0.006 0.0000

FS171 Bleed15.Fl_O 227.06 4.707 468.73 -18.33 0.0000 674.00 3.848 442.47 2481.9 0.5441 1.40077 0.0000308 227.06 0.007 0.0000

FS172 FanDuct.Fl_O 227.06 4.707 468.73 -18.33 0.0000 674.00 3.848 442.47 2481.9 0.5441 1.40077 0.0000308 227.06 0.007 0.0000

FS173 Byp_Nozz.Fl_O 227.06 4.707 468.73 -18.33 0.0000 674.00 2.947 409.94 2006.9 0.8457 1.40077 0.0000308 227.06 0.007 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 733.02 1.121 0.9043 2498.137 1.0367 0.9059 -1260.4 2272.33 54.77

LPC 84.35 1.525 0.8404 2498.137 1.1526 0.8496 -603.6 6.76 3.33

HPC 53.48 6.043 0.8178 8941.494 1.8115 0.8566 -3292.8 61.00 57.62

HPT 12.08 4.116 0.8727 219.391 1.3628 0.8500 3292.8 

LPT 54.02 2.775 0.8452 70.235 1.2589 0.8254 1864.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 851.70 1.118 0.9062 2474.317 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 70.87 1.491 0.7766 0.660 0.0000 1.1901 1.0693 1.0822 0.0003

HPC 48.64 5.806 0.8263 8703.120 11.0050 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.030 0.8726 1.319 4.0300 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.335 0.8515 0.790 2.3350 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–33
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2556.86 5625.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8558 733.64 44.27 9.183

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2721 733.64 44.27 3.309

TEGV 0.0000 0.2789 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.46 39.14 13.507

FanDuct 0.0000 0.5441 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 843.21 70.94 26.423

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.46 39.14 13.507

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 943.36 95.55 38.693

Splitter 8.6897 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.46 39.14 13.507

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8959.6 1930.2 3292.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5838 520.77 -7.02 6.403

LP_Shaft 2330.9 4200.0 1864.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6552 943.36 95.55 37.802

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3233 943.36 95.55 21.432

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.36 95.55 38.693

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.36 95.55 38.693

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.36 95.55 38.693

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 468.13 -18.46 4.707

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 468.13 -18.46 4.707

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 468.13 -18.46 4.707

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 468.13 -18.46 4.707

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1667.71 0.9995 0.0230 0.18283 0.01066 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.123 0.9801 1.0000 0.9800 613.40 0.413 573.5 417.8

Byp_Nozz 1.597 0.9800 1.0000 0.9800 2006.86 0.846 823.0 5807.9

NASA/TM—2013-218094 N–34
************************************************************************************************************************************ 

Date:05/13/13 Time:09:36:22 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 454.76 Stator 1 exit: 461.53 Stator 2 inlet: 470.02 Stator 2 exit: 474.35 

 Stator 3 inlet: 483.10 Stator 3 exit: 487.02 Stator 4 inlet: 495.21 Stator 4 exit: 498.53 

 Stator 5 inlet: 505.24 Stator 5 exit: 508.12 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.40 

Fan Bypass Relative Humidity 1.75 

LPC Inlet Relative Humidity 1.56 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 707.26 Fan/LPC Inlet Flow Velocity 178.63 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 447.02 

Additional Water at LPC Exit 0.0001836 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 18.00 257.07 615.0 1.0895 670.02 8.7284 707.26 9.092 0.772 10.000 1657.8 1566.8 1091.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.07 4.339 449.68 -22.87 0.0000 810.63 3.088 407.97 2561.5 0.7140 1.40090 0.0000272 257.06 0.007 0.0000

FS1 Inlet.Fl_O 257.07 4.339 449.68 -22.87 0.0000 810.63 3.981 438.71 4168.2 0.3530 1.40090 0.0000272 257.06 0.007 0.0000

FS12 Splitter.Fl_02 230.64 4.337 449.68 -22.87 0.0000 727.67 3.930 437.15 3531.8 0.3780 1.40090 0.0000272 230.64 0.006 0.0000

FS2 Splitter.Fl_01 26.42 4.337 449.68 -22.87 0.0000 83.37 4.248 447.02 830.5 0.1723 1.40090 0.0000272 26.42 0.001 0.0000

FS14 Fan.Fl_O 230.64 4.849 465.80 -19.01 0.0000 662.47 4.102 444.04 2606.7 0.4945 1.40079 0.0000272 230.64 0.006 0.0000

FS23 LPC.Fl_O 26.42 6.558 516.85 -6.77 0.0000 59.11 6.277 510.42 412.6 0.2508 1.40025 0.0000272 26.42 0.001 0.0000

FS24 VaporIN.Fl_O 26.43 6.558 517.13 -7.76 0.0000 59.14 6.277 510.70 412.6 0.2509 1.40023 0.0002108 26.42 0.006 0.0002

FS25 Bleed2.Fl_O 23.79 6.558 517.13 -7.76 0.0000 53.22 6.333 511.98 412.6 0.2241 1.40023 0.0002108 23.78 0.005 0.0002

FS3 HPC.Fl_O 22.63 39.454 935.85 93.82 0.0000 11.32 34.770 903.51 49.7 0.4308 1.38453 0.0002108 22.63 0.005 0.0002

FS36 Bleed3.Fl_O 17.54 39.454 935.85 93.82 0.0000 8.78 36.763 917.65 49.3 0.3209 1.38453 0.0002108 17.54 0.004 0.0002

FS4 Burner.Fl_O 17.73 38.545 1657.84 81.79 0.0106 12.08 36.398 1634.13 74.6 0.2940 1.33463 0.0002108 17.54 0.004 0.0132

FS45 HPT.Fl_O 23.69 9.404 1095.40 -16.56 0.0079 53.81 8.550 1067.57 265.4 0.3752 1.36921 0.0002108 23.50 0.005 0.0099

FS49 LPT.Fl_O 23.97 3.450 872.52 -70.78 0.0078 132.45 3.278 860.23 860.2 0.2730 1.38297 0.0002108 23.78 0.005 0.0098

FS5 TEGV.Fl_O 23.97 3.450 872.59 -70.78 0.0078 132.46 3.278 860.30 860.2 0.2730 1.38296 0.0002108 23.78 0.005 0.0098

FS8 Core_Nozz.Fl_O 23.97 3.450 872.66 -70.78 0.0078 132.46 3.088 846.30 613.4 0.4029 1.38296 0.0002108 23.78 0.005 0.0098

FS17 FanDuctLkg.Fl_O 230.64 4.849 465.80 -19.01 0.0000 662.47 4.102 444.04 2606.7 0.4945 1.40079 0.0000272 230.64 0.006 0.0000

FS171 Bleed15.Fl_O 233.28 4.849 466.38 -18.88 0.0000 670.48 3.976 440.64 2481.9 0.5399 1.40078 0.0000293 233.28 0.007 0.0000

FS172 FanDuct.Fl_O 233.28 4.849 466.38 -18.88 0.0000 670.48 3.976 440.64 2481.9 0.5399 1.40078 0.0000293 233.28 0.007 0.0000

FS173 Byp_Nozz.Fl_O 233.28 4.849 466.38 -18.88 0.0000 670.48 3.088 409.90 2006.9 0.8290 1.40078 0.0000293 233.28 0.007 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 727.67 1.118 0.9040 2472.757 1.0359 0.9055 -1260.7 2671.86 54.68

LPC 83.37 1.512 0.8405 2472.757 1.1494 0.8495 -602.0 6.67 3.26

HPC 53.22 6.016 0.8174 8932.984 1.8097 0.8562 -3335.8 61.05 57.64

HPT 12.08 4.099 0.8721 219.069 1.3617 0.8494 3335.8 

LPT 53.81 2.726 0.8431 69.567 1.2534 0.8234 1862.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 845.48 1.115 0.9058 2449.180 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 69.77 1.479 0.7754 0.653 0.0000 1.1947 1.0683 1.0839 0.0003

HPC 48.41 5.780 0.8259 8694.837 11.0051 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.013 0.8721 1.317 4.0129 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.298 0.8494 0.783 2.2982 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–35
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.52 5650.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8753 728.01 43.03 9.404

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2783 728.01 43.03 3.450

TEGV 0.0000 0.2730 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 707.03 37.95 13.795

FanDuct 0.0000 0.5399 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 836.58 69.44 26.954

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 707.03 37.95 13.795

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 935.85 93.82 39.454

Splitter 8.7284 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 707.03 37.95 13.795

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8919.7 1964.2 3335.8 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6429 517.13 -7.76 6.558

LP_Shaft 2302.4 4249.0 1862.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7159 935.85 93.82 38.545

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3765 935.85 93.82 21.877

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.85 93.82 39.454

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.85 93.82 39.454

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.85 93.82 39.454

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 465.80 -19.01 4.849

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 465.80 -19.01 4.849

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 465.80 -19.01 4.849

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 465.80 -19.01 4.849

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1657.78 0.9995 0.0230 0.18612 0.01061 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.403 559.9 417.2

Byp_Nozz 1.570 0.9800 1.0000 0.9800 2006.86 0.829 806.6 5848.7

NASA/TM—2013-218094 N–36
************************************************************************************************************************************ 

Date:05/13/13 Time:09:36:36 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.41 Stator 1 exit: 462.77 Stator 2 inlet: 470.74 Stator 2 exit: 474.79 

 Stator 3 inlet: 483.00 Stator 3 exit: 486.65 Stator 4 inlet: 494.33 Stator 4 exit: 497.40 

 Stator 5 inlet: 503.68 Stator 5 exit: 506.34 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.00 

Fan Bypass Relative Humidity 2.26 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.22 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 667.90 Fan/LPC Inlet Flow Velocity 173.00 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 414.42 Fan/LPC Inlet Static Temperature 449.11 

Additional Water at LPC Exit 0.0001599 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 18.00 278.58 670.2 1.0732 719.20 8.8101 667.90 8.757 0.795 10.000 1650.9 1559.9 1088.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 278.58 4.831 451.61 -22.45 0.0000 790.76 3.578 414.42 2577.4 0.6690 1.40088 0.0000348 278.57 0.010 0.0000

FS1 Inlet.Fl_O 278.58 4.831 451.61 -22.45 0.0000 790.76 4.453 441.21 4168.2 0.3430 1.40088 0.0000348 278.57 0.010 0.0000

FS12 Splitter.Fl_02 250.18 4.829 451.61 -22.45 0.0000 710.51 4.398 439.71 3531.8 0.3674 1.40088 0.0000348 250.18 0.009 0.0000

FS2 Splitter.Fl_01 28.40 4.829 451.61 -22.45 0.0000 80.65 4.736 449.11 830.5 0.1665 1.40088 0.0000348 28.40 0.001 0.0000

FS14 Fan.Fl_O 250.18 5.360 466.78 -18.82 0.0000 650.69 4.571 445.98 2606.7 0.4824 1.40078 0.0000348 250.18 0.009 0.0000

FS23 LPC.Fl_O 28.40 7.123 514.73 -7.33 0.0000 58.37 6.826 508.50 412.6 0.2474 1.40028 0.0000348 28.40 0.001 0.0000

FS24 VaporIN.Fl_O 28.40 7.123 514.98 -8.19 0.0000 58.39 6.826 508.74 412.6 0.2475 1.40026 0.0001947 28.40 0.006 0.0002

FS25 Bleed2.Fl_O 25.56 7.123 514.98 -8.19 0.0000 52.55 6.884 509.99 412.6 0.2211 1.40026 0.0001947 25.56 0.005 0.0002

FS3 HPC.Fl_O 24.32 42.307 928.99 92.22 0.0000 11.31 37.302 896.99 49.7 0.4299 1.38493 0.0001947 24.32 0.005 0.0002

FS36 Bleed3.Fl_O 18.85 42.307 928.99 92.22 0.0000 8.76 39.431 910.97 49.3 0.3203 1.38493 0.0001947 18.85 0.004 0.0002

FS4 Burner.Fl_O 19.05 41.333 1650.94 80.22 0.0106 12.08 39.030 1627.32 74.6 0.2940 1.33498 0.0001947 18.85 0.004 0.0131

FS45 HPT.Fl_O 25.46 10.193 1092.77 -16.96 0.0079 53.29 9.287 1065.63 265.4 0.3708 1.36939 0.0001947 25.26 0.005 0.0099

FS49 LPT.Fl_O 25.76 3.942 881.65 -68.26 0.0078 125.23 3.767 870.65 860.2 0.2569 1.38247 0.0001947 25.56 0.005 0.0098

FS5 TEGV.Fl_O 25.76 3.942 881.72 -68.26 0.0078 125.23 3.767 870.72 860.2 0.2569 1.38246 0.0001947 25.56 0.005 0.0098

FS8 Core_Nozz.Fl_O 25.76 3.942 881.79 -68.26 0.0078 125.24 3.578 858.47 613.3 0.3765 1.38246 0.0001947 25.56 0.005 0.0098

FS17 FanDuctLkg.Fl_O 250.18 5.360 466.78 -18.82 0.0000 650.69 4.571 445.98 2606.7 0.4824 1.40078 0.0000348 250.18 0.009 0.0000

FS171 Bleed15.Fl_O 253.02 5.360 467.32 -18.70 0.0000 658.46 4.440 442.80 2481.9 0.5257 1.40078 0.0000366 253.02 0.009 0.0000

FS172 FanDuct.Fl_O 253.02 5.360 467.32 -18.70 0.0000 658.46 4.440 442.80 2481.9 0.5257 1.40078 0.0000366 253.02 0.009 0.0000

FS173 Byp_Nozz.Fl_O 253.02 5.360 467.32 -18.70 0.0000 658.46 3.578 416.27 2006.9 0.7821 1.40078 0.0000366 253.02 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.51 1.110 0.9032 2396.066 1.0336 0.9046 -1286.9 5760.24 54.20

LPC 80.65 1.475 0.8415 2396.066 1.1398 0.8500 -607.9 6.41 3.05

HPC 52.55 5.940 0.8161 8910.957 1.8039 0.8550 -3543.2 61.35 57.86

HPT 12.08 4.055 0.8716 218.528 1.3585 0.8490 3543.3 

LPT 53.29 2.586 0.8386 67.635 1.2372 0.8196 1894.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.54 1.108 0.9050 2373.220 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.45 1.445 0.7718 0.633 0.0000 1.2136 1.0675 1.0903 0.0003

HPC 47.79 5.707 0.8245 8673.396 10.9953 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.970 0.8716 1.313 3.9704 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.193 0.8448 0.761 2.1929 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–37
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2577.44 5783.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9407 723.45 42.01 10.193

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2991 723.45 42.01 3.942

TEGV 0.0000 0.2569 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.70 36.99 14.863

FanDuct 0.0000 0.5257 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 830.81 68.12 28.937

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.70 36.99 14.863

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 928.99 92.22 42.307

Splitter 8.8101 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.70 36.99 14.863

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8879.2 2095.9 3543.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.8402 514.98 -8.19 7.123

LP_Shaft 2235.8 4450.8 1894.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.9186 928.99 92.22 41.333

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5539 928.99 92.22 23.521

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.99 92.22 42.307

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.99 92.22 42.307

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.99 92.22 42.307

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1650.87 0.9995 0.0230 0.19978 0.01060 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.377 526.9 421.9

Byp_Nozz 1.498 0.9800 1.0000 0.9800 2006.86 0.782 766.9 6031.3

NASA/TM—2013-218094 N–38
************************************************************************************************************************************ 

Date:05/13/13 Time:09:36:53 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.05 Stator 1 exit: 470.56 Stator 2 inlet: 477.38 Stator 2 exit: 480.67 

 Stator 3 inlet: 487.80 Stator 3 exit: 490.69 Stator 4 inlet: 497.40 Stator 4 exit: 499.79 

 Stator 5 inlet: 505.19 Stator 5 exit: 507.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.96 

Fan Bypass Relative Humidity 3.12 

LPC Inlet Relative Humidity 2.83 

LPC Exit Relative Humidity 0.47 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 617.99 Fan/LPC Inlet Flow Velocity 174.95 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 429.58 Fan/LPC Inlet Static Temperature 458.87 

Additional Water at LPC Exit 0.0001731 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 18.00 305.10 729.6 1.0759 784.96 8.3732 617.99 8.197 0.828 10.000 1655.4 1563.6 1094.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 305.10 5.595 461.42 -20.30 0.0000 755.84 4.358 429.58 2596.2 0.6080 1.40081 0.0000681 305.08 0.021 0.0001

FS1 Inlet.Fl_O 305.10 5.595 461.42 -20.30 0.0000 755.84 5.199 451.82 4168.2 0.3256 1.40081 0.0000681 305.08 0.021 0.0001

FS12 Splitter.Fl_02 272.55 5.592 461.42 -20.30 0.0000 675.54 5.147 450.59 3531.8 0.3463 1.40081 0.0000681 272.54 0.019 0.0001

FS2 Splitter.Fl_01 32.55 5.592 461.42 -20.30 0.0000 80.68 5.485 458.87 830.5 0.1665 1.40081 0.0000681 32.55 0.002 0.0001

FS14 Fan.Fl_O 272.55 6.139 475.25 -16.98 0.0000 624.52 5.321 456.19 2606.7 0.4566 1.40070 0.0000681 272.54 0.019 0.0001

FS23 LPC.Fl_O 32.55 7.827 515.86 -7.25 0.0000 60.96 7.469 509.01 412.6 0.2593 1.40026 0.0000681 32.55 0.002 0.0001

FS24 VaporIN.Fl_O 32.56 7.827 516.13 -8.18 0.0000 60.98 7.469 509.27 412.6 0.2594 1.40023 0.0002412 32.55 0.008 0.0002

FS25 Bleed2.Fl_O 27.67 7.827 516.13 -8.18 0.0000 51.83 7.572 511.27 412.6 0.2179 1.40023 0.0002412 27.67 0.007 0.0002

FS3 HPC.Fl_O 26.33 45.865 927.80 91.66 0.0000 11.28 40.465 896.00 49.7 0.4288 1.38500 0.0002412 26.32 0.006 0.0002

FS36 Bleed3.Fl_O 20.41 45.865 927.80 91.66 0.0000 8.75 42.761 909.89 49.3 0.3196 1.38500 0.0002412 20.40 0.005 0.0002

FS4 Burner.Fl_O 20.62 44.809 1655.36 79.58 0.0107 12.08 42.312 1631.67 74.6 0.2941 1.33469 0.0002412 20.40 0.005 0.0133

FS45 HPT.Fl_O 27.57 11.203 1098.36 -17.02 0.0080 52.62 10.235 1071.87 265.4 0.3654 1.36897 0.0002412 27.34 0.007 0.0100

FS49 LPT.Fl_O 27.89 4.717 904.83 -63.97 0.0079 114.78 4.543 895.48 860.2 0.2340 1.38109 0.0002412 27.67 0.007 0.0099

FS5 TEGV.Fl_O 27.89 4.717 904.90 -63.97 0.0079 114.78 4.543 895.55 860.2 0.2340 1.38108 0.0002412 27.67 0.007 0.0099

FS8 Core_Nozz.Fl_O 27.89 4.717 904.98 -63.97 0.0079 114.79 4.358 885.44 613.4 0.3400 1.38108 0.0002412 27.67 0.007 0.0099

FS17 FanDuctLkg.Fl_O 272.55 6.139 475.25 -16.98 0.0000 624.52 5.321 456.19 2606.7 0.4566 1.40070 0.0000681 272.54 0.019 0.0001

FS171 Bleed15.Fl_O 277.44 6.139 475.97 -16.83 0.0000 636.19 5.173 453.22 2481.9 0.5005 1.40070 0.0000711 277.42 0.020 0.0001

FS172 FanDuct.Fl_O 277.44 6.139 475.97 -16.83 0.0000 636.19 5.173 453.22 2481.9 0.5005 1.40070 0.0000711 277.42 0.020 0.0001

FS173 Byp_Nozz.Fl_O 277.44 6.139 475.97 -16.83 0.0000 636.19 4.358 431.52 2006.9 0.7169 1.40070 0.0000711 277.42 0.020 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 675.54 1.098 0.9021 2249.745 1.0300 0.9034 -1278.8 -9339.51 52.72

LPC 80.68 1.399 0.8551 2249.745 1.1180 0.8618 -601.1 5.96 2.63

HPC 51.83 5.860 0.8147 8887.483 1.7976 0.8536 -3814.3 61.61 58.04

HPT 12.08 4.000 0.8718 217.906 1.3543 0.8495 3814.3 

LPT 52.62 2.375 0.8304 64.027 1.2114 0.8125 1879.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 784.91 1.096 0.9040 2228.294 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 60.33 1.382 0.7655 0.594 0.0000 1.3372 1.0459 1.1170 0.0003

HPC 47.14 5.631 0.8231 8650.549 10.9883 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.917 0.8718 1.310 3.9166 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.034 0.8365 0.720 2.0342 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–39
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.24 5860.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0184 723.42 41.74 11.203

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3238 723.42 41.74 4.717

TEGV 0.0000 0.2340 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.79 36.75 16.195

FanDuct 0.0000 0.5005 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 830.18 67.70 31.410

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.79 36.75 16.195

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 927.80 91.66 45.865

Splitter 8.3732 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.79 36.75 16.195

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8865.7 2259.6 3814.3 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8835 516.13 -8.18 7.827

LP_Shaft 2121.9 4653.1 1879.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1597 927.80 91.66 44.809

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7648 927.80 91.66 25.586

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.80 91.66 45.865

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.80 91.66 45.865

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.80 91.66 45.865

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1655.29 0.9995 0.0230 0.21804 0.01069 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 483.0 418.7

Byp_Nozz 1.409 0.9800 1.0000 0.9800 2006.86 0.717 715.7 6171.3

NASA/TM—2013-218094 N–40
************************************************************************************************************************************ 

Date:05/13/13 Time:09:37:15 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 36/ 1/20 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.11 Stator 1 exit: 477.18 Stator 2 inlet: 481.79 Stator 2 exit: 483.59 

 Stator 3 inlet: 488.73 Stator 3 exit: 490.13 Stator 4 inlet: 495.05 Stator 4 exit: 496.05 

 Stator 5 inlet: 499.65 Stator 5 exit: 500.37 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.82 

Fan Bypass Relative Humidity 3.94 

LPC Inlet Relative Humidity 3.82 

LPC Exit Relative Humidity 1.19 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 571.13 Fan/LPC Inlet Flow Velocity 194.52 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.36 

Ambient Static Temperature 445.14 Fan/LPC Inlet Static Temperature 469.17 

Additional Water at LPC Exit 0.0001671 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 18.00 330.55 749.0 1.1186 837.85 7.0509 571.13 7.335 0.859 10.000 1666.1 1572.0 1105.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 330.55 6.516 472.33 -18.03 0.0000 711.40 5.297 445.14 2595.1 0.5520 1.40072 0.0001274 330.51 0.042 0.0001

FS1 Inlet.Fl_O 330.55 6.516 472.33 -18.03 0.0000 711.40 6.111 463.74 4168.2 0.3040 1.40072 0.0001274 330.51 0.042 0.0001

FS12 Splitter.Fl_02 289.49 6.513 472.33 -18.03 0.0000 623.35 6.078 463.07 3531.8 0.3158 1.40072 0.0001274 289.45 0.037 0.0001

FS2 Splitter.Fl_01 41.06 6.513 472.33 -18.03 0.0000 88.41 6.362 469.17 830.5 0.1831 1.40072 0.0001274 41.05 0.005 0.0001

FS14 Fan.Fl_O 289.49 7.057 484.46 -15.12 0.0000 582.64 6.258 468.10 2606.7 0.4178 1.40061 0.0001274 289.45 0.037 0.0001

FS23 LPC.Fl_O 41.06 8.207 511.60 -8.61 0.0000 73.02 7.656 501.53 412.6 0.3167 1.40031 0.0001274 41.05 0.005 0.0001

FS24 VaporIN.Fl_O 41.06 8.207 511.87 -9.51 0.0000 73.05 7.655 501.78 412.6 0.3169 1.40028 0.0002944 41.05 0.012 0.0003

FS25 Bleed2.Fl_O 28.75 8.207 511.87 -9.51 0.0000 51.13 7.947 507.18 412.6 0.2148 1.40028 0.0002944 28.74 0.008 0.0003

FS3 HPC.Fl_O 27.35 47.796 918.91 89.17 0.0000 11.19 42.274 888.00 49.7 0.4244 1.38550 0.0002944 27.34 0.008 0.0003

FS36 Bleed3.Fl_O 21.20 47.796 918.91 89.17 0.0000 8.67 44.618 901.47 49.3 0.3166 1.38550 0.0002944 21.19 0.006 0.0003

FS4 Burner.Fl_O 21.43 46.696 1666.06 76.78 0.0110 12.09 44.092 1642.26 74.6 0.2942 1.33397 0.0002944 21.19 0.006 0.0137

FS45 HPT.Fl_O 28.64 12.031 1109.70 -18.56 0.0082 51.18 11.053 1084.65 265.4 0.3538 1.36807 0.0002944 28.40 0.008 0.0103

FS49 LPT.Fl_O 28.98 5.626 937.29 -60.29 0.0081 101.75 5.464 929.80 860.2 0.2061 1.37901 0.0002944 28.74 0.008 0.0102

FS5 TEGV.Fl_O 28.98 5.626 937.36 -60.29 0.0081 101.76 5.464 929.87 860.2 0.2061 1.37901 0.0002944 28.74 0.008 0.0102

FS8 Core_Nozz.Fl_O 28.98 5.626 937.44 -60.29 0.0081 101.76 5.297 922.01 613.4 0.2969 1.37900 0.0002944 28.74 0.008 0.0102

FS17 FanDuctLkg.Fl_O 289.49 7.057 484.46 -15.12 0.0000 582.64 6.258 468.10 2606.7 0.4178 1.40061 0.0001274 289.45 0.037 0.0001

FS171 Bleed15.Fl_O 301.81 7.057 485.58 -14.89 0.0000 608.14 6.064 464.96 2481.9 0.4705 1.40060 0.0001342 301.77 0.040 0.0001

FS172 FanDuct.Fl_O 301.81 7.057 485.58 -14.89 0.0000 608.14 6.064 464.96 2481.9 0.4705 1.40060 0.0001342 301.77 0.040 0.0001

FS173 Byp_Nozz.Fl_O 301.81 7.057 485.58 -14.89 0.0000 608.14 5.297 447.32 2006.9 0.6533 1.40060 0.0001342 301.77 0.040 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.35 1.084 0.9032 2044.928 1.0257 0.9043 -1191.7 -2768.59 49.88

LPC 88.41 1.260 0.8219 2044.928 1.0832 0.8277 -547.1 6.38 2.41

HPC 51.13 5.824 0.8139 8865.652 1.7952 0.8529 -3915.9 60.73 57.11

HPT 12.09 3.881 0.8732 215.773 1.3456 0.8517 3915.9 

LPT 51.18 2.138 0.8211 58.580 1.1810 0.8048 1738.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.27 1.082 0.9050 2025.429 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.48 1.311 0.7608 0.540 0.0000 1.6530 0.8357 1.0804 0.0003

HPC 46.51 5.597 0.8223 8629.300 11.0513 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.802 0.8732 1.297 3.8015 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.856 0.8272 0.659 1.8562 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–41
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2595.09 5867.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0578 716.78 39.83 12.031

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3363 716.78 39.83 5.626

TEGV 0.0000 0.2061 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.38 34.89 16.917

FanDuct 0.0000 0.4705 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 822.34 65.48 32.752

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.38 34.89 16.917

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 918.91 89.17 47.796

Splitter 7.0509 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.38 34.89 16.917

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8807.3 2335.2 3915.9 WB17Y Bleed> 0.3000 1.0000 1.0000 12.3194 511.87 -9.51 8.207

LP_Shaft 1951.4 4679.6 1738.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2821 918.91 89.17 46.696

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8719 918.91 89.17 26.867

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.91 89.17 47.796

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.91 89.17 47.796

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.91 89.17 47.796

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1666.00 0.9995 0.0230 0.23274 0.01098 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.297 430.0 387.3 

Byp_Nozz 1.332 0.9800 1.0000 0.9800 2006.86 0.653 664.1 6229.4

NASA/TM—2013-218094 N–42
************************************************************************************************************************************ 

Date:05/13/13 Time:09:37:48 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 28/ 56/ 2/25 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 486.26 Stator 1 exit: 489.21 Stator 2 inlet: 491.95 Stator 2 exit: 492.71 

 Stator 3 inlet: 496.04 Stator 3 exit: 496.37 Stator 4 inlet: 499.61 Stator 4 exit: 499.64 

 Stator 5 inlet: 501.49 Stator 5 exit: 501.32 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.85 

Fan Bypass Relative Humidity 4.91 

LPC Inlet Relative Humidity 5.02 

LPC Exit Relative Humidity 2.62 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 518.26 Fan/LPC Inlet Flow Velocity 204.30 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.74 

Ambient Static Temperature 465.18 Fan/LPC Inlet Static Temperature 484.08 

Additional Water at LPC Exit 0.0001863 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 18.00 368.15 832.5 1.1207 932.96 6.2384 518.26 6.454 0.890 10.000 1699.1 1601.1 1136.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 368.15 7.943 487.56 -15.16 0.0000 660.38 6.740 465.18 2616.0 0.4900 1.40057 0.0002627 368.06 0.097 0.0003

FS1 Inlet.Fl_O 368.15 7.943 487.56 -15.16 0.0000 660.38 7.522 480.02 4168.2 0.2799 1.40057 0.0002627 368.06 0.097 0.0003

FS12 Splitter.Fl_02 317.29 7.939 487.56 -15.16 0.0000 569.43 7.503 479.73 3531.8 0.2854 1.40057 0.0002627 317.21 0.083 0.0003

FS2 Splitter.Fl_01 50.86 7.939 487.56 -15.16 0.0000 91.28 7.743 484.08 830.5 0.1894 1.40057 0.0002627 50.85 0.013 0.0003

FS14 Fan.Fl_O 317.29 8.512 498.39 -12.56 0.0000 536.98 7.712 484.52 2606.7 0.3780 1.40045 0.0002627 317.21 0.083 0.0003

FS23 LPC.Fl_O 50.86 9.079 515.20 -8.53 0.0000 82.05 8.291 501.99 412.6 0.3625 1.40024 0.0002627 50.85 0.013 0.0003

FS24 VaporIN.Fl_O 50.87 9.079 515.49 -9.53 0.0000 82.09 8.290 502.26 412.6 0.3627 1.40021 0.0004491 50.85 0.023 0.0004

FS25 Bleed2.Fl_O 30.52 9.079 515.49 -9.53 0.0000 49.25 8.813 511.12 412.6 0.2065 1.40021 0.0004491 30.51 0.014 0.0004

FS3 HPC.Fl_O 29.04 51.266 918.25 88.12 0.0000 11.08 45.484 888.13 49.7 0.4188 1.38552 0.0004491 29.03 0.013 0.0004

FS36 Bleed3.Fl_O 22.51 51.266 918.25 88.12 0.0000 8.58 47.932 901.21 49.3 0.3129 1.38552 0.0004491 22.50 0.010 0.0004

FS4 Burner.Fl_O 22.77 50.085 1699.12 75.15 0.0115 12.09 47.290 1674.93 74.6 0.2946 1.33200 0.0004491 22.50 0.010 0.0145

FS45 HPT.Fl_O 30.42 13.553 1140.71 -18.98 0.0086 48.92 12.556 1117.56 265.4 0.3361 1.36576 0.0004491 30.15 0.014 0.0110

FS49 LPT.Fl_O 30.78 7.047 987.36 -56.04 0.0085 88.56 6.895 981.49 860.2 0.1785 1.37568 0.0004491 30.51 0.014 0.0108

FS5 TEGV.Fl_O 30.78 7.047 987.44 -56.04 0.0085 88.57 6.895 981.56 860.2 0.1785 1.37567 0.0004491 30.51 0.014 0.0108

FS8 Core_Nozz.Fl_O 30.78 7.047 987.51 -56.04 0.0085 88.57 6.740 975.55 613.4 0.2553 1.37567 0.0004491 30.51 0.014 0.0108

FS17 FanDuctLkg.Fl_O 317.29 8.512 498.39 -12.56 0.0000 536.98 7.712 484.52 2606.7 0.3780 1.40045 0.0002627 317.21 0.083 0.0003

FS171 Bleed15.Fl_O 337.64 8.512 499.42 -12.38 0.0000 572.01 7.477 481.24 2481.9 0.4343 1.40044 0.0002740 337.55 0.092 0.0003

FS172 FanDuct.Fl_O 337.64 8.512 499.42 -12.38 0.0000 572.01 7.477 481.24 2481.9 0.4343 1.40044 0.0002740 337.55 0.092 0.0003

FS173 Byp_Nozz.Fl_O 337.64 8.512 499.42 -12.38 0.0000 572.01 6.740 467.17 2006.9 0.5871 1.40044 0.0002740 337.55 0.092 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 569.43 1.072 0.9054 1848.947 1.0222 0.9063 -1166.4 -1882.29 46.42

LPC 91.28 1.144 0.6896 1848.947 1.0567 0.6954 -477.0 6.97 2.19

HPC 49.25 5.647 0.8099 8804.937 1.7813 0.8491 -4115.0 60.55 56.72

HPT 12.09 3.695 0.8753 212.950 1.3307 0.8549 4115.0 

LPT 48.92 1.923 0.8141 53.077 1.1520 0.7998 1643.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 661.62 1.070 0.9072 1831.317 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 47.04 1.247 0.7558 0.488 0.0000 1.9402 0.5807 0.9124 0.0003

HPC 44.80 5.428 0.8182 8570.203 11.0884 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.621 0.8753 1.280 3.6208 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.694 0.8202 0.597 1.6944 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–43
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2616.04 5930.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.1232 718.23 39.29 13.553

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3571 718.23 39.29 7.047

TEGV 0.0000 0.1785 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 698.05 34.41 18.360

FanDuct 0.0000 0.4343 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 822.69 64.69 35.235

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 698.05 34.41 18.360

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 918.25 88.12 51.266

Splitter 6.2384 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 698.05 34.41 18.360

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8777.9 2462.2 4115.0 WB17Y Bleed> 0.4000 1.0000 1.0000 20.3482 515.49 -9.53 9.079

LP_Shaft 1792.6 4815.1 1643.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4850 918.25 88.12 50.085

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 3.0495 918.25 88.12 29.189

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.25 88.12 51.266

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.25 88.12 51.266

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.25 88.12 51.266

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1699.06 0.9995 0.0230 0.25915 0.01152 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.046 0.9801 1.0000 0.9800 613.40 0.255 379.8 363.4

Byp_Nozz 1.263 0.9800 1.0000 0.9800 2006.86 0.587 609.8 6399.3

NASA/TM—2013-218094 N–44
************************************************************************************************************************************ 

Date:05/13/13 Time:09:38:20 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 30/ 58/ 2/27 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 500.27 Stator 1 exit: 502.63 Stator 2 inlet: 504.94 Stator 2 exit: 505.66 

 Stator 3 inlet: 508.36 Stator 3 exit: 508.76 Stator 4 inlet: 511.37 Stator 4 exit: 511.54 

 Stator 5 inlet: 513.13 Stator 5 exit: 513.14 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.53 

Fan Bypass Relative Humidity 5.96 

LPC Inlet Relative Humidity 5.71 

LPC Exit Relative Humidity 3.40 

HPC Relative Humidity 0.02 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 479.99 Fan/LPC Inlet Flow Velocity 173.45 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.18 

Ambient Static Temperature 481.63 Fan/LPC Inlet Static Temperature 498.31 

Additional Water at LPC Exit 0.0002441 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 18.00 386.71 642.4 1.3769 884.50 6.7810 479.99 5.289 0.902 10.000 1650.5 1554.6 1125.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 386.71 9.342 500.81 -13.05 0.0000 597.77 8.149 481.63 2541.0 0.4460 1.40040 0.0004484 386.53 0.173 0.0004

FS1 Inlet.Fl_O 386.71 9.342 500.81 -13.05 0.0000 597.77 8.941 494.57 4168.2 0.2511 1.40040 0.0004484 386.53 0.173 0.0004

FS12 Splitter.Fl_02 337.01 9.337 500.81 -13.05 0.0000 521.20 8.912 494.17 3531.8 0.2590 1.40040 0.0004484 336.86 0.151 0.0004

FS2 Splitter.Fl_01 49.70 9.337 500.81 -13.05 0.0000 76.86 9.175 498.31 830.5 0.1585 1.40040 0.0004484 49.68 0.022 0.0004

FS14 Fan.Fl_O 337.01 9.814 508.80 -11.14 0.0000 499.85 9.027 496.79 2606.7 0.3474 1.40030 0.0004484 336.86 0.151 0.0004

FS23 LPC.Fl_O 49.70 10.432 523.19 -7.68 0.0000 70.32 9.786 513.71 412.6 0.3036 1.40011 0.0004484 49.68 0.022 0.0004

FS24 VaporIN.Fl_O 49.71 10.432 523.55 -9.00 0.0000 70.36 9.785 514.06 412.6 0.3038 1.40007 0.0006925 49.68 0.034 0.0007

FS25 Bleed2.Fl_O 29.83 10.432 523.55 -9.00 0.0000 42.21 10.210 520.34 412.6 0.1758 1.40007 0.0006925 29.81 0.021 0.0007

FS3 HPC.Fl_O 28.38 49.407 888.07 79.31 0.0000 11.05 43.872 859.06 49.7 0.4171 1.38717 0.0006925 28.36 0.020 0.0007

FS36 Bleed3.Fl_O 21.99 49.407 888.07 79.31 0.0000 8.56 46.214 871.64 49.3 0.3117 1.38717 0.0006925 21.98 0.015 0.0007

FS4 Burner.Fl_O 22.24 48.269 1650.48 66.82 0.0112 12.08 45.581 1626.90 74.6 0.2940 1.33453 0.0006925 21.98 0.015 0.0143

FS45 HPT.Fl_O 29.72 14.275 1130.53 -18.14 0.0083 45.18 13.391 1111.29 265.4 0.3070 1.36656 0.0006925 29.46 0.020 0.0109

FS49 LPT.Fl_O 30.07 8.396 1006.43 -47.86 0.0082 73.32 8.273 1002.37 860.2 0.1470 1.37460 0.0006925 29.81 0.021 0.0108

FS5 TEGV.Fl_O 30.07 8.396 1006.50 -47.85 0.0082 73.33 8.273 1002.44 860.2 0.1470 1.37460 0.0006925 29.81 0.021 0.0108

FS8 Core_Nozz.Fl_O 30.07 8.396 1006.57 -47.85 0.0082 73.33 8.149 998.41 613.4 0.2088 1.37459 0.0006925 29.81 0.021 0.0108

FS17 FanDuctLkg.Fl_O 337.01 9.814 508.80 -11.14 0.0000 499.85 9.027 496.79 2606.7 0.3474 1.40030 0.0004484 336.86 0.151 0.0004

FS171 Bleed15.Fl_O 356.89 9.814 509.62 -11.02 0.0000 529.77 8.814 494.20 2481.9 0.3947 1.40029 0.0004619 356.73 0.165 0.0005

FS172 FanDuct.Fl_O 356.89 9.814 509.62 -11.02 0.0000 529.77 8.814 494.20 2481.9 0.3947 1.40029 0.0004619 356.73 0.165 0.0005 

FS173 Byp_Nozz.Fl_O 356.89 9.814 509.62 -11.02 0.0000 529.77 8.149 483.25 2006.9 0.5221 1.40029 0.0004619 356.73 0.165 0.0005

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 521.20 1.051 0.8983 1610.488 1.0159 0.8990 -913.2 -1525.87 44.72

LPC 76.86 1.117 0.7208 1610.488 1.0447 0.7252 -377.4 8.26 1.96

HPC 42.21 4.736 0.7955 8540.623 1.6962 0.8340 -3636.5 68.26 63.04

HPT 12.08 3.381 0.8666 211.212 1.3031 0.8467 3636.5 

LPT 45.18 1.700 0.8005 47.066 1.1197 0.7882 1290.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 605.59 1.050 0.9001 1595.132 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 39.71 1.184 0.7480 0.425 0.0000 1.9357 0.6360 0.9636 0.0003

HPC 38.39 4.560 0.8038 8312.935 10.7596 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.315 0.8666 1.269 3.3155 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.527 0.8064 0.529 1.5266 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–45
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2541.02 5769.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0976 706.89 35.15 14.275

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3490 706.89 35.15 8.396

TEGV 0.0000 0.1470 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.63 30.74 19.007

FanDuct 0.0000 0.3947 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 801.45 58.12 34.597

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.63 30.74 19.007

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 888.07 79.31 49.407

Splitter 6.7810 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.63 30.74 19.007

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8580.7 2225.9 3636.5 WB17Y Bleed> 0.4000 1.0000 1.0000 19.8844 523.55 -9.00 10.432

LP_Shaft 1582.5 4283.4 1290.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4056 888.07 79.31 48.269

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9800 888.07 79.31 28.824

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 888.07 79.31 49.407

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 888.07 79.31 49.407

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 888.07 79.31 49.407

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 508.80 -11.14 9.814

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 508.80 -11.14 9.814

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 508.80 -11.14 9.814

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 508.80 -11.14 9.814

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1650.42 0.9995 0.0230 0.24569 0.01118 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.030 0.9802 1.0000 0.9800 613.40 0.209 314.2 293.6 

Byp_Nozz 1.204 0.9800 1.0000 0.9800 2006.86 0.522 551.5 6117.8

NASA/TM—2013-218094 N–46
25μm, ISA +36R 

************************************************************************************************************************************ 

Date:05/13/13 Time:10:04:47 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 12/ 26/ 1/10 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 483.68 Stator 1 exit: 491.45 Stator 2 inlet: 501.22 Stator 2 exit: 506.21 

 Stator 3 inlet: 516.31 Stator 3 exit: 520.84 Stator 4 inlet: 530.29 Stator 4 exit: 534.15 

 Stator 5 inlet: 541.91 Stator 5 exit: 545.29 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.97 

Fan Bypass Relative Humidity 1.41 

LPC Inlet Relative Humidity 1.30 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 192.84 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 474.82 

Additional Water at LPC Exit 0.0004075 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 252.17 619.1 1.1433 707.76 8.5687 789.49 9.519 0.736 10.000 1760.6 1665.7 1159.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.17 4.267 477.92 -16.44 0.0000 833.74 2.854 425.97 2543.6 0.7800 1.40068 0.0000851 252.15 0.021 0.0001

FS1 Inlet.Fl_O 252.17 4.267 477.92 -16.44 0.0000 833.74 3.891 465.50 4168.2 0.3649 1.40068 0.0000851 252.15 0.021 0.0001

FS12 Splitter.Fl_02 225.82 4.265 477.92 -16.44 0.0000 746.98 3.839 463.77 3531.8 0.3902 1.40068 0.0000851 225.80 0.019 0.0001

FS2 Splitter.Fl_01 26.35 4.265 477.92 -16.44 0.0000 87.17 4.169 474.82 830.5 0.1805 1.40068 0.0000851 26.35 0.002 0.0001

FS14 Fan.Fl_O 225.82 4.817 496.65 -11.95 0.0000 674.09 4.043 472.35 2606.7 0.5067 1.40049 0.0000851 225.80 0.019 0.0001

FS23 LPC.Fl_O 26.35 6.656 555.11 2.08 0.0000 60.19 6.360 547.94 412.6 0.2558 1.39967 0.0000851 26.35 0.002 0.0001

FS24 VaporIN.Fl_O 26.36 6.656 555.68 -0.13 0.0000 60.25 6.359 548.49 412.6 0.2561 1.39961 0.0004925 26.35 0.013 0.0005

FS25 Bleed2.Fl_O 23.73 6.656 555.68 -0.13 0.0000 54.23 6.418 549.94 412.6 0.2287 1.39961 0.0004925 23.72 0.012 0.0005

FS3 HPC.Fl_O 22.58 40.613 1007.14 109.89 0.0000 11.38 35.728 972.14 49.7 0.4344 1.38021 0.0004925 22.57 0.011 0.0005

FS36 Bleed3.Fl_O 17.50 40.613 1007.14 109.89 0.0000 8.82 37.810 987.47 49.3 0.3234 1.38021 0.0004925 17.49 0.009 0.0005

FS4 Burner.Fl_O 17.69 39.678 1760.56 97.00 0.0112 12.07 37.470 1735.71 74.6 0.2944 1.32934 0.0004925 17.49 0.009 0.0142

FS45 HPT.Fl_O 23.65 9.523 1163.38 -9.52 0.0084 54.66 8.626 1133.00 265.4 0.3830 1.36444 0.0004925 23.44 0.012 0.0107

FS49 LPT.Fl_O 23.92 3.262 910.91 -71.53 0.0083 142.86 3.070 895.85 860.2 0.2971 1.38043 0.0004925 23.72 0.012 0.0106

FS5 TEGV.Fl_O 23.92 3.262 910.98 -71.53 0.0083 142.86 3.070 895.92 860.2 0.2971 1.38043 0.0004925 23.72 0.012 0.0106

FS8 Core_Nozz.Fl_O 23.92 3.262 911.06 -71.53 0.0083 142.87 2.854 878.09 613.4 0.4436 1.38042 0.0004925 23.72 0.012 0.0106

FS17 FanDuctLkg.Fl_O 225.82 4.817 496.65 -11.95 0.0000 674.09 4.043 472.35 2606.7 0.5067 1.40049 0.0000851 225.80 0.019 0.0001

FS171 Bleed15.Fl_O 228.45 4.817 497.33 -11.82 0.0000 682.42 3.909 468.47 2481.9 0.5546 1.40048 0.0000898 228.43 0.021 0.0001

FS172 FanDuct.Fl_O 228.45 4.817 497.33 -11.82 0.0000 682.42 3.909 468.47 2481.9 0.5546 1.40048 0.0000898 228.43 0.021 0.0001

FS173 Byp_Nozz.Fl_O 228.45 4.817 497.33 -11.82 0.0000 682.42 2.854 428.14 2006.9 0.8979 1.40048 0.0000898 228.43 0.021 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.98 1.130 0.9055 2568.797 1.0392 0.9071 -1434.2 1605.87 54.82

LPC 87.17 1.561 0.8402 2568.797 1.1615 0.8499 -690.4 6.97 3.73

HPC 54.23 6.102 0.8186 8965.163 1.8124 0.8573 -3604.3 61.37 58.05

HPT 12.07 4.167 0.8772 221.157 1.3647 0.8552 3604.3 

LPT 54.66 2.920 0.8557 72.294 1.2754 0.8361 2124.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 867.92 1.127 0.9073 2544.304 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 73.93 1.522 0.7799 0.678 0.0000 1.1791 1.0738 1.0773 0.0003

HPC 49.32 5.861 0.8271 8726.157 10.9732 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.079 0.8772 1.329 4.0789 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.444 0.8621 0.813 2.4438 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–47
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2543.57 6187.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8732 783.47 54.88 9.523

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2776 783.47 54.88 3.262

TEGV 0.0000 0.2971 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.84 49.38 14.127

FanDuct 0.0000 0.5546 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 900.43 83.49 27.709

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.84 49.38 14.127

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1007.14 109.89 40.613

Splitter 8.5687 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.84 49.38 14.127

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9279.5 2040.0 3604.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6364 555.68 -0.13 6.656

LP_Shaft 2465.8 4525.2 2124.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7092 1007.14 109.89 39.678

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3706 1007.14 109.89 22.429

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.14 109.89 40.613

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.14 109.89 40.613

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1007.14 109.89 40.613

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 496.65 -11.95 4.817

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 496.65 -11.95 4.817

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 496.65 -11.95 4.817

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 496.65 -11.95 4.817

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1760.51 0.9995 0.0230 0.19660 0.01124 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.444 627.6 466.7

Byp_Nozz 1.688 0.9800 1.0000 0.9800 2006.86 0.898 892.9 6340.2

NASA/TM—2013-218094 N–48
************************************************************************************************************************************ 

Date:05/13/13 Time:10:05:02 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.92 Stator 1 exit: 484.20 Stator 2 inlet: 493.33 Stator 2 exit: 497.99 

 Stator 3 inlet: 507.43 Stator 3 exit: 511.65 Stator 4 inlet: 520.47 Stator 4 exit: 524.06 

 Stator 5 inlet: 531.29 Stator 5 exit: 534.41 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.46 

Fan Bypass Relative Humidity 1.80 

LPC Inlet Relative Humidity 1.64 

LPC Exit Relative Humidity 0.18 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 738.88 Fan/LPC Inlet Flow Velocity 185.92 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 468.60 

Additional Water at LPC Exit 0.0003590 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 36.00 245.33 608.3 1.1083 674.22 8.6649 738.88 9.233 0.764 10.000 1733.0 1638.7 1142.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 245.33 4.201 471.48 -17.97 0.0000 818.16 2.947 425.97 2560.7 0.7300 1.40073 0.0000824 245.31 0.020 0.0001

FS1 Inlet.Fl_O 245.33 4.201 471.48 -17.97 0.0000 818.16 3.847 459.74 4168.2 0.3569 1.40073 0.0000824 245.31 0.020 0.0001

FS12 Splitter.Fl_02 219.94 4.199 471.48 -17.97 0.0000 733.88 3.797 458.08 3531.8 0.3819 1.40073 0.0000824 219.92 0.018 0.0001

FS2 Splitter.Fl_01 25.38 4.199 471.48 -17.97 0.0000 84.70 4.110 468.60 830.5 0.1751 1.40073 0.0000824 25.38 0.002 0.0001

FS14 Fan.Fl_O 219.94 4.712 488.93 -13.79 0.0000 666.05 3.976 465.76 2606.7 0.4983 1.40058 0.0000824 219.92 0.018 0.0001

FS23 LPC.Fl_O 25.38 6.416 543.74 -0.64 0.0000 59.53 6.137 536.88 412.6 0.2528 1.39985 0.0000824 25.38 0.002 0.0001

FS24 VaporIN.Fl_O 25.39 6.416 544.25 -2.59 0.0000 59.58 6.137 537.38 412.6 0.2530 1.39980 0.0004414 25.38 0.011 0.0004

FS25 Bleed2.Fl_O 22.85 6.416 544.25 -2.59 0.0000 53.62 6.192 538.76 412.6 0.2260 1.39980 0.0004414 22.84 0.010 0.0004

FS3 HPC.Fl_O 21.74 38.789 984.71 104.61 0.0000 11.35 34.155 950.65 49.7 0.4326 1.38160 0.0004414 21.74 0.010 0.0004

FS36 Bleed3.Fl_O 16.85 38.789 984.71 104.61 0.0000 8.80 36.128 965.55 49.3 0.3222 1.38160 0.0004414 16.84 0.007 0.0004

FS4 Burner.Fl_O 17.04 37.896 1732.95 91.91 0.0111 12.08 35.785 1708.40 74.6 0.2944 1.33069 0.0004414 16.84 0.007 0.0140

FS45 HPT.Fl_O 22.77 9.211 1146.52 -11.84 0.0083 54.02 8.366 1117.32 265.4 0.3775 1.36559 0.0004414 22.58 0.010 0.0106

FS49 LPT.Fl_O 23.04 3.311 908.54 -70.13 0.0082 135.33 3.138 895.19 860.2 0.2798 1.38064 0.0004414 22.84 0.010 0.0105

FS5 TEGV.Fl_O 23.04 3.311 908.62 -70.13 0.0082 135.34 3.138 895.26 860.2 0.2798 1.38063 0.0004414 22.84 0.010 0.0105

FS8 Core_Nozz.Fl_O 23.04 3.311 908.69 -70.13 0.0082 135.34 2.947 879.89 613.4 0.4142 1.38063 0.0004414 22.84 0.010 0.0105

FS17 FanDuctLkg.Fl_O 219.94 4.712 488.93 -13.79 0.0000 666.05 3.976 465.76 2606.7 0.4983 1.40058 0.0000824 219.92 0.018 0.0001

FS171 Bleed15.Fl_O 222.48 4.712 489.56 -13.66 0.0000 674.18 3.851 462.12 2481.9 0.5444 1.40057 0.0000865 222.46 0.019 0.0001

FS172 FanDuct.Fl_O 222.48 4.712 489.56 -13.66 0.0000 674.18 3.851 462.12 2481.9 0.5444 1.40057 0.0000865 222.46 0.019 0.0001

FS173 Byp_Nozz.Fl_O 222.48 4.712 489.56 -13.66 0.0000 674.18 2.947 428.04 2006.9 0.8468 1.40057 0.0000865 222.46 0.019 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 733.88 1.122 0.9047 2504.901 1.0370 0.9063 -1301.6 2182.81 54.68

LPC 84.70 1.528 0.8406 2504.901 1.1533 0.8499 -622.4 6.78 3.35

HPC 53.62 6.046 0.8178 8945.664 1.8093 0.8565 -3381.9 61.29 57.92

HPT 12.08 4.114 0.8760 220.128 1.3615 0.8539 3381.9 

LPT 54.02 2.781 0.8501 70.532 1.2600 0.8308 1924.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 852.70 1.119 0.9065 2481.017 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 71.17 1.494 0.7769 0.662 0.0000 1.1901 1.0693 1.0820 0.0003

HPC 48.77 5.808 0.8263 8707.178 10.9852 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.028 0.8760 1.323 4.0281 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.340 0.8564 0.793 2.3399 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–49
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2560.72 5633.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8410 766.36 51.01 9.211

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2674 766.36 51.01 3.311

TEGV 0.0000 0.2798 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 744.28 45.65 13.538

FanDuct 0.0000 0.5444 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 880.50 78.88 26.487

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 744.28 45.65 13.538

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 984.71 104.61 38.789

Splitter 8.6649 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 744.28 45.65 13.538

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9163.6 1938.3 3381.9 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5392 544.25 -2.59 6.416

LP_Shaft 2388.2 4231.2 1924.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6094 984.71 104.61 37.896

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2832 984.71 104.61 21.488

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 984.71 104.61 38.789

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 984.71 104.61 38.789

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 984.71 104.61 38.789

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 488.93 -13.79 4.712

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 488.93 -13.79 4.712

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 488.93 -13.79 4.712

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 488.93 -13.79 4.712

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1732.90 0.9995 0.0230 0.18728 0.01112 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.414 586.5 420.0

Byp_Nozz 1.599 0.9800 1.0000 0.9800 2006.86 0.847 842.0 5822.3

NASA/TM—2013-218094 N–50
************************************************************************************************************************************ 

Date:05/13/13 Time:10:05:18 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 474.83 Stator 1 exit: 481.92 Stator 2 inlet: 490.81 Stator 2 exit: 495.35 

 Stator 3 inlet: 504.53 Stator 3 exit: 508.64 Stator 4 inlet: 517.22 Stator 4 exit: 520.70 

 Stator 5 inlet: 527.74 Stator 5 exit: 530.76 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.63 

Fan Bypass Relative Humidity 1.95 

LPC Inlet Relative Humidity 1.76 

LPC Exit Relative Humidity 0.19 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 722.68 Fan/LPC Inlet Flow Velocity 183.09 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 466.71 

Additional Water at LPC Exit 0.0003278 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 36.00 251.86 621.4 1.1026 685.21 8.7107 722.68 9.103 0.772 10.000 1722.0 1628.1 1135.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 251.86 4.339 469.50 -18.42 0.0000 811.56 3.088 425.97 2564.6 0.7140 1.40075 0.0000786 251.84 0.020 0.0001

FS1 Inlet.Fl_O 251.86 4.339 469.50 -18.42 0.0000 811.56 3.980 458.03 4168.2 0.3535 1.40075 0.0000786 251.84 0.020 0.0001

FS12 Splitter.Fl_02 225.93 4.337 469.50 -18.42 0.0000 728.35 3.929 456.40 3531.8 0.3785 1.40075 0.0000786 225.91 0.018 0.0001

FS2 Splitter.Fl_01 25.94 4.337 469.50 -18.42 0.0000 83.62 4.248 466.71 830.5 0.1728 1.40075 0.0000786 25.93 0.002 0.0001

FS14 Fan.Fl_O 225.93 4.853 486.46 -14.36 0.0000 662.60 4.105 463.72 2606.7 0.4947 1.40060 0.0000786 225.91 0.018 0.0001

FS23 LPC.Fl_O 25.94 6.569 539.89 -1.54 0.0000 59.20 6.287 533.16 412.6 0.2512 1.39992 0.0000786 25.93 0.002 0.0001

FS24 VaporIN.Fl_O 25.95 6.569 540.37 -3.32 0.0000 59.25 6.286 533.62 412.6 0.2515 1.39986 0.0004064 25.93 0.011 0.0004

FS25 Bleed2.Fl_O 23.35 6.569 540.37 -3.32 0.0000 53.32 6.342 534.97 412.6 0.2246 1.39986 0.0004064 23.34 0.009 0.0004

FS3 HPC.Fl_O 22.22 39.501 976.54 102.78 0.0000 11.34 34.792 942.80 49.7 0.4321 1.38210 0.0004064 22.21 0.009 0.0004

FS36 Bleed3.Fl_O 17.22 39.501 976.54 102.78 0.0000 8.79 36.796 957.56 49.3 0.3218 1.38210 0.0004064 17.21 0.007 0.0004

FS4 Burner.Fl_O 17.41 38.591 1721.96 90.16 0.0111 12.08 36.442 1697.53 74.6 0.2944 1.33125 0.0004064 17.21 0.007 0.0139

FS45 HPT.Fl_O 23.27 9.423 1139.87 -12.51 0.0083 53.80 8.567 1111.09 265.4 0.3755 1.36606 0.0004064 23.07 0.009 0.0105

FS49 LPT.Fl_O 23.54 3.451 907.39 -69.39 0.0082 132.60 3.278 894.63 860.2 0.2736 1.38074 0.0004064 23.34 0.009 0.0104

FS5 TEGV.Fl_O 23.54 3.451 907.46 -69.39 0.0082 132.60 3.278 894.70 860.2 0.2736 1.38073 0.0004064 23.34 0.009 0.0104

FS8 Core_Nozz.Fl_O 23.54 3.451 907.53 -69.39 0.0082 132.61 3.088 880.14 613.4 0.4038 1.38073 0.0004064 23.34 0.009 0.0104

FS17 FanDuctLkg.Fl_O 225.93 4.853 486.46 -14.36 0.0000 662.60 4.105 463.72 2606.7 0.4947 1.40060 0.0000786 225.91 0.018 0.0001

FS171 Bleed15.Fl_O 228.52 4.853 487.07 -14.23 0.0000 670.64 3.979 460.17 2481.9 0.5401 1.40060 0.0000823 228.50 0.019 0.0001

FS172 FanDuct.Fl_O 228.52 4.853 487.07 -14.23 0.0000 670.64 3.979 460.17 2481.9 0.5401 1.40060 0.0000823 228.50 0.019 0.0001

FS173 Byp_Nozz.Fl_O 228.52 4.853 487.07 -14.23 0.0000 670.64 3.088 428.00 2006.9 0.8298 1.40060 0.0000823 228.50 0.019 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 728.35 1.119 0.9043 2478.068 1.0361 0.9058 -1299.1 2574.39 54.61

LPC 83.62 1.515 0.8406 2478.068 1.1499 0.8497 -619.4 6.69 3.28

HPC 53.32 6.013 0.8173 8935.880 1.8072 0.8560 -3420.2 61.38 57.97

HPT 12.08 4.095 0.8754 219.799 1.3603 0.8533 3420.2 

LPT 53.80 2.731 0.8479 69.833 1.2542 0.8288 1918.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 846.27 1.116 0.9061 2454.440 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 70.00 1.482 0.7757 0.655 0.0000 1.1945 1.0683 1.0837 0.0003

HPC 48.50 5.777 0.8258 8697.655 10.9835 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.010 0.8754 1.321 4.0096 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.302 0.8542 0.786 2.3016 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–51
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2564.57 5657.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8593 760.27 49.73 9.423

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2732 760.27 49.73 3.451

TEGV 0.0000 0.2736 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.41 44.43 13.814

FanDuct 0.0000 0.5401 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 873.31 77.32 26.987

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.41 44.43 13.814

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 976.54 102.78 39.501

Splitter 8.7107 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 738.41 44.43 13.814

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9120.9 1969.5 3420.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5945 540.37 -3.32 6.569

LP_Shaft 2357.7 4273.9 1918.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6662 976.54 102.78 38.591

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3330 976.54 102.78 21.907

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.54 102.78 39.501

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.54 102.78 39.501

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 976.54 102.78 39.501

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.46 -14.36 4.853

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.46 -14.36 4.853

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.46 -14.36 4.853

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.46 -14.36 4.853

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1721.90 0.9995 0.0230 0.19033 0.01106 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.404 571.9 418.5

Byp_Nozz 1.571 0.9800 1.0000 0.9800 2006.86 0.830 825.1 5860.2

NASA/TM—2013-218094 N–52
************************************************************************************************************************************ 

Date:05/13/13 Time:10:05:32 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.23 Stator 1 exit: 482.87 Stator 2 inlet: 491.17 Stator 2 exit: 495.40 

 Stator 3 inlet: 503.96 Stator 3 exit: 507.77 Stator 4 inlet: 515.77 Stator 4 exit: 518.98 

 Stator 5 inlet: 525.53 Stator 5 exit: 528.30 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.24 

Fan Bypass Relative Humidity 2.48 

LPC Inlet Relative Humidity 2.22 

LPC Exit Relative Humidity 0.28 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 682.24 Fan/LPC Inlet Flow Velocity 176.55 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 432.42 Fan/LPC Inlet Static Temperature 468.62 

Additional Water at LPC Exit 0.0003050 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 36.00 272.67 668.1 1.0939 730.83 8.8177 682.24 8.727 0.795 10.000 1711.3 1617.6 1130.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 272.67 4.831 471.21 -18.12 0.0000 790.60 3.578 432.42 2577.1 0.6690 1.40074 0.0000968 272.64 0.026 0.0001

FS1 Inlet.Fl_O 272.67 4.831 471.21 -18.12 0.0000 790.60 4.453 460.36 4168.2 0.3429 1.40074 0.0000968 272.64 0.026 0.0001

FS12 Splitter.Fl_02 244.89 4.829 471.21 -18.12 0.0000 710.43 4.399 458.80 3531.8 0.3674 1.40074 0.0000968 244.87 0.024 0.0001

FS2 Splitter.Fl_01 27.77 4.829 471.21 -18.12 0.0000 80.57 4.736 468.62 830.5 0.1663 1.40074 0.0000968 27.77 0.003 0.0001

FS14 Fan.Fl_O 244.89 5.360 487.03 -14.32 0.0000 650.64 4.571 465.33 2606.7 0.4824 1.40059 0.0000968 244.87 0.024 0.0001

FS23 LPC.Fl_O 27.77 7.122 537.04 -2.33 0.0000 58.31 6.826 530.56 412.6 0.2472 1.39996 0.0000968 27.77 0.003 0.0001

FS24 VaporIN.Fl_O 27.78 7.122 537.49 -3.98 0.0000 58.36 6.825 530.99 412.6 0.2474 1.39991 0.0004018 27.77 0.011 0.0004

FS25 Bleed2.Fl_O 25.00 7.122 537.49 -3.98 0.0000 52.52 6.884 532.29 412.6 0.2210 1.39991 0.0004018 24.99 0.010 0.0004

FS3 HPC.Fl_O 23.79 42.162 967.59 100.59 0.0000 11.33 37.152 934.25 49.7 0.4312 1.38263 0.0004018 23.78 0.010 0.0004

FS36 Bleed3.Fl_O 18.44 42.162 967.59 100.59 0.0000 8.78 39.284 948.83 49.3 0.3212 1.38263 0.0004018 18.43 0.007 0.0004

FS4 Burner.Fl_O 18.64 41.191 1711.28 88.04 0.0110 12.08 38.896 1686.99 74.6 0.2943 1.33178 0.0004018 18.43 0.007 0.0138

FS45 HPT.Fl_O 24.91 10.174 1135.00 -13.13 0.0082 53.24 9.271 1107.02 265.4 0.3708 1.36639 0.0004018 24.70 0.010 0.0105

FS49 LPT.Fl_O 25.21 3.940 915.91 -66.65 0.0081 124.95 3.766 904.59 860.2 0.2565 1.38026 0.0004018 24.99 0.010 0.0103

FS5 TEGV.Fl_O 25.21 3.940 915.99 -66.65 0.0081 124.95 3.766 904.66 860.2 0.2565 1.38025 0.0004018 24.99 0.010 0.0103

FS8 Core_Nozz.Fl_O 25.21 3.940 916.06 -66.65 0.0081 124.96 3.578 892.04 613.3 0.3759 1.38025 0.0004018 24.99 0.010 0.0103

FS17 FanDuctLkg.Fl_O 244.89 5.360 487.03 -14.32 0.0000 650.64 4.571 465.33 2606.7 0.4824 1.40059 0.0000968 244.87 0.024 0.0001

FS171 Bleed15.Fl_O 247.67 5.360 487.60 -14.21 0.0000 658.40 4.440 462.02 2481.9 0.5256 1.40059 0.0001002 247.65 0.025 0.0001

FS172 FanDuct.Fl_O 247.67 5.360 487.60 -14.21 0.0000 658.40 4.440 462.02 2481.9 0.5256 1.40059 0.0001002 247.65 0.025 0.0001

FS173 Byp_Nozz.Fl_O 247.67 5.360 487.60 -14.21 0.0000 658.40 3.578 434.35 2006.9 0.7821 1.40059 0.0001002 247.65 0.025 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.43 1.110 0.9032 2395.649 1.0336 0.9046 -1313.8 5797.22 54.20

LPC 80.57 1.475 0.8412 2395.649 1.1397 0.8497 -620.3 6.41 3.05

HPC 52.52 5.920 0.8157 8909.582 1.8002 0.8545 -3609.5 61.81 58.30

HPT 12.08 4.049 0.8747 219.248 1.3569 0.8527 3609.5 

LPT 53.24 2.582 0.8428 67.778 1.2370 0.8242 1934.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.45 1.108 0.9050 2372.807 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.44 1.445 0.7718 0.633 0.0000 1.2128 1.0676 1.0900 0.0003

HPC 47.77 5.688 0.8242 8672.058 10.9678 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.964 0.8746 1.318 3.9642 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.190 0.8490 0.762 2.1902 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–53
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2577.08 5781.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9201 754.28 48.30 10.174

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2925 754.28 48.30 3.940

TEGV 0.0000 0.2565 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.72 43.07 14.831

FanDuct 0.0000 0.5256 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.76 75.49 28.847

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.72 43.07 14.831

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 967.59 100.59 42.162

Splitter 8.8177 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.72 43.07 14.831

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9069.8 2090.2 3609.5 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7782 537.49 -3.98 7.122

LP_Shaft 2283.4 4448.5 1934.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8549 967.59 100.59 41.191

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4981 967.59 100.59 23.449

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.59 100.59 42.162

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.59 100.59 42.162

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 967.59 100.59 42.162

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 487.03 -14.32 5.360

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 487.03 -14.32 5.360

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 487.03 -14.32 5.360

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 487.03 -14.32 5.360

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1711.22 0.9995 0.0230 0.20301 0.01101 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.101 0.9801 1.0000 0.9800 613.40 0.376 535.8 419.8

Byp_Nozz 1.498 0.9800 1.0000 0.9800 2006.86 0.782 783.3 6030.1

NASA/TM—2013-218094 N–54
************************************************************************************************************************************ 

Date:05/13/13 Time:10:05:49 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 14/ 28/ 1/12 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.51 Stator 1 exit: 490.21 Stator 2 inlet: 497.25 Stator 2 exit: 500.66 

 Stator 3 inlet: 508.01 Stator 3 exit: 511.00 Stator 4 inlet: 517.92 Stator 4 exit: 520.39 

 Stator 5 inlet: 525.96 Stator 5 exit: 528.05 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.18 

Fan Bypass Relative Humidity 3.37 

LPC Inlet Relative Humidity 3.05 

LPC Exit Relative Humidity 0.57 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 630.80 Fan/LPC Inlet Flow Velocity 177.28 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 447.58 Fan/LPC Inlet Static Temperature 478.12 

Additional Water at LPC Exit 0.0003156 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 36.00 298.12 711.1 1.1099 789.23 8.4157 630.80 8.109 0.827 10.000 1709.2 1615.2 1132.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 298.12 5.595 480.74 -16.28 0.0000 753.87 4.358 447.58 2589.7 0.6080 1.40064 0.0001750 298.07 0.052 0.0002

FS1 Inlet.Fl_O 298.12 5.595 480.74 -16.28 0.0000 753.87 5.201 470.80 4168.2 0.3247 1.40064 0.0001750 298.07 0.052 0.0002

FS12 Splitter.Fl_02 266.46 5.592 480.74 -16.28 0.0000 674.15 5.149 469.51 3531.8 0.3455 1.40064 0.0001750 266.42 0.047 0.0002

FS2 Splitter.Fl_01 31.66 5.592 480.74 -16.28 0.0000 80.11 5.487 478.12 830.5 0.1653 1.40064 0.0001750 31.66 0.006 0.0002

FS14 Fan.Fl_O 266.46 6.131 494.95 -12.88 0.0000 623.95 5.315 475.14 2606.7 0.4561 1.40050 0.0001750 266.42 0.047 0.0002

FS23 LPC.Fl_O 31.66 7.805 536.97 -2.80 0.0000 60.66 7.452 529.92 412.6 0.2580 1.39995 0.0001750 31.66 0.006 0.0002

FS24 VaporIN.Fl_O 31.67 7.805 537.43 -4.51 0.0000 60.71 7.451 530.36 412.6 0.2582 1.39990 0.0004905 31.66 0.016 0.0005

FS25 Bleed2.Fl_O 26.92 7.805 537.43 -4.51 0.0000 51.60 7.553 532.42 412.6 0.2170 1.39990 0.0004905 26.91 0.013 0.0005

FS3 HPC.Fl_O 25.62 45.368 962.98 98.94 0.0000 11.31 40.000 929.92 49.7 0.4302 1.38289 0.0004905 25.60 0.013 0.0005

FS36 Bleed3.Fl_O 19.85 45.368 962.98 98.94 0.0000 8.76 42.284 944.37 49.3 0.3205 1.38289 0.0004905 19.84 0.010 0.0005

FS4 Burner.Fl_O 20.07 44.323 1709.17 86.38 0.0110 12.08 41.854 1684.90 74.6 0.2943 1.33184 0.0004905 19.84 0.010 0.0140

FS45 HPT.Fl_O 26.83 11.109 1136.62 -13.67 0.0082 52.53 10.152 1109.46 265.4 0.3651 1.36626 0.0004905 26.59 0.013 0.0106

FS49 LPT.Fl_O 27.14 4.710 937.83 -62.14 0.0081 113.87 4.539 928.34 860.2 0.2322 1.37892 0.0004905 26.91 0.013 0.0105

FS5 TEGV.Fl_O 27.14 4.710 937.90 -62.14 0.0081 113.87 4.539 928.41 860.2 0.2322 1.37892 0.0004905 26.91 0.013 0.0105

FS8 Core_Nozz.Fl_O 27.14 4.710 937.98 -62.14 0.0081 113.88 4.358 918.16 613.4 0.3372 1.37891 0.0004905 26.91 0.013 0.0105

FS17 FanDuctLkg.Fl_O 266.46 6.131 494.95 -12.88 0.0000 623.95 5.315 475.14 2606.7 0.4561 1.40050 0.0001750 266.42 0.047 0.0002

FS171 Bleed15.Fl_O 271.21 6.131 495.69 -12.73 0.0000 635.55 5.169 472.07 2481.9 0.4998 1.40049 0.0001805 271.16 0.049 0.0002

FS172 FanDuct.Fl_O 271.21 6.131 495.69 -12.73 0.0000 635.55 5.169 472.07 2481.9 0.4998 1.40049 0.0001805 271.16 0.049 0.0002

FS173 Byp_Nozz.Fl_O 271.21 6.131 495.69 -12.73 0.0000 635.55 4.358 449.59 2006.9 0.7154 1.40049 0.0001805 271.16 0.049 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 674.15 1.096 0.9014 2239.512 1.0296 0.9027 -1284.2 -8416.53 52.79

LPC 80.11 1.396 0.8547 2239.512 1.1170 0.8614 -604.2 5.98 2.60

HPC 51.60 5.813 0.8138 8879.291 1.7918 0.8527 -3844.7 62.30 58.68

HPT 12.08 3.990 0.8744 218.626 1.3525 0.8526 3844.7 

LPT 52.53 2.359 0.8338 63.952 1.2095 0.8163 1888.4 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 783.29 1.094 0.9033 2218.159 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 59.99 1.378 0.7653 0.592 0.0000 1.3353 1.0454 1.1169 0.0003

HPC 46.93 5.586 0.8222 8642.575 10.9499 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.907 0.8743 1.314 3.9070 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.022 0.8399 0.719 2.0218 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–55
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2589.67 5845.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9907 751.89 47.22 11.109

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3150 751.89 47.22 4.710

TEGV 0.0000 0.2322 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.57 42.04 16.069

FanDuct 0.0000 0.4998 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 862.20 74.11 31.094

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.57 42.04 16.069

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 962.98 98.94 45.368

Splitter 8.4157 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.57 42.04 16.069

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9038.5 2234.1 3844.7 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7509 537.43 -4.51 7.805

LP_Shaft 2156.1 4600.2 1888.4 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.0739 962.98 98.94 44.323

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.6897 962.98 98.94 25.325

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.98 98.94 45.368

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.98 98.94 45.368

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.98 98.94 45.368

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 494.95 -12.88 6.131

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 494.95 -12.88 6.131

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 494.95 -12.88 6.131

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 494.95 -12.88 6.131

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1709.11 0.9995 0.0230 0.21923 0.01105 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.081 0.9801 1.0000 0.9800 613.40 0.337 487.5 411.2

Byp_Nozz 1.407 0.9800 1.0000 0.9800 2006.86 0.715 729.0 6144.8

NASA/TM—2013-218094 N–56
************************************************************************************************************************************ 

Date:05/13/13 Time:10:06:18 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 19/ 47/ 2/16 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 492.29 Stator 1 exit: 496.45 Stator 2 inlet: 501.18 Stator 2 exit: 503.04 

 Stator 3 inlet: 508.30 Stator 3 exit: 509.74 Stator 4 inlet: 514.78 Stator 4 exit: 515.82 

 Stator 5 inlet: 519.50 Stator 5 exit: 520.25 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.02 

Fan Bypass Relative Humidity 4.21 

LPC Inlet Relative Humidity 4.03 

LPC Exit Relative Humidity 1.37 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 582.56 Fan/LPC Inlet Flow Velocity 195.51 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 463.14 Fan/LPC Inlet Static Temperature 488.23 

Additional Water at LPC Exit 0.0002946 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 36.00 322.29 711.3 1.1716 833.38 7.1225 582.56 7.195 0.857 10.000 1713.8 1617.8 1140.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 322.29 6.516 491.41 -14.47 0.0000 707.51 5.297 463.14 2581.2 0.5520 1.40052 0.0003043 322.19 0.098 0.0003

FS1 Inlet.Fl_O 322.29 6.516 491.41 -14.47 0.0000 707.51 6.116 482.59 4168.2 0.3022 1.40052 0.0003043 322.19 0.098 0.0003

FS12 Splitter.Fl_02 282.61 6.513 491.41 -14.47 0.0000 620.72 6.082 481.88 3531.8 0.3143 1.40052 0.0003043 282.52 0.086 0.0003

FS2 Splitter.Fl_01 39.68 6.513 491.41 -14.47 0.0000 87.15 6.366 488.23 830.5 0.1805 1.40052 0.0003043 39.67 0.012 0.0003

FS14 Fan.Fl_O 282.61 7.039 503.66 -11.54 0.0000 581.42 6.246 486.73 2606.7 0.4167 1.40039 0.0003043 282.52 0.086 0.0003

FS23 LPC.Fl_O 39.68 8.183 531.64 -4.82 0.0000 72.15 7.647 521.45 412.6 0.3125 1.40001 0.0003043 39.67 0.012 0.0003

FS24 VaporIN.Fl_O 39.69 8.183 532.07 -6.42 0.0000 72.20 7.646 521.86 412.6 0.3128 1.39996 0.0005989 39.67 0.024 0.0006

FS25 Bleed2.Fl_O 27.78 8.183 532.07 -6.42 0.0000 50.54 7.930 527.32 412.6 0.2122 1.39996 0.0005989 27.77 0.017 0.0006

FS3 HPC.Fl_O 26.44 46.883 950.19 95.16 0.0000 11.22 41.439 918.17 49.7 0.4258 1.38363 0.0005989 26.42 0.016 0.0006

FS36 Bleed3.Fl_O 20.49 46.883 950.19 95.16 0.0000 8.69 43.750 932.13 49.3 0.3176 1.38363 0.0005989 20.48 0.012 0.0006

FS4 Burner.Fl_O 20.72 45.803 1713.83 82.35 0.0113 12.08 43.250 1689.50 74.6 0.2945 1.33143 0.0005989 20.48 0.012 0.0144

FS45 HPT.Fl_O 27.69 11.867 1144.85 -15.75 0.0084 50.94 10.912 1119.39 265.4 0.3523 1.36558 0.0005989 27.44 0.016 0.0109

FS49 LPT.Fl_O 28.01 5.615 969.67 -58.34 0.0083 100.25 5.459 962.19 860.2 0.2031 1.37685 0.0005989 27.77 0.017 0.0108

FS5 TEGV.Fl_O 28.01 5.615 969.74 -58.34 0.0083 100.25 5.459 962.26 860.2 0.2031 1.37684 0.0005989 27.77 0.017 0.0108

FS8 Core_Nozz.Fl_O 28.01 5.615 969.81 -58.34 0.0083 100.26 5.297 954.43 613.4 0.2923 1.37684 0.0005989 27.77 0.017 0.0108

FS17 FanDuctLkg.Fl_O 282.61 7.039 503.66 -11.54 0.0000 581.42 6.246 486.73 2606.7 0.4167 1.40039 0.0003043 282.52 0.086 0.0003

FS171 Bleed15.Fl_O 294.52 7.039 504.81 -11.33 0.0000 606.61 6.054 483.51 2481.9 0.4690 1.40037 0.0003162 294.42 0.093 0.0003

FS172 FanDuct.Fl_O 294.52 7.039 504.81 -11.33 0.0000 606.61 6.054 483.51 2481.9 0.4690 1.40037 0.0003162 294.42 0.093 0.0003

FS173 Byp_Nozz.Fl_O 294.52 7.039 504.81 -11.33 0.0000 606.61 5.297 465.38 2006.9 0.6504 1.40037 0.0003162 294.42 0.093 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 620.72 1.081 0.9017 2025.930 1.0249 0.9028 -1174.2 -2600.98 50.00

LPC 87.15 1.256 0.8236 2025.930 1.0819 0.8292 -541.7 6.43 2.41

HPC 50.54 5.730 0.8121 8845.414 1.7858 0.8511 -3896.1 61.75 58.03

HPT 12.08 3.860 0.8752 216.408 1.3429 0.8542 3896.1 

LPT 50.94 2.113 0.8234 58.281 1.1778 0.8076 1715.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 721.21 1.079 0.9035 2006.613 0.0424 0.8607 1.0235 0.9980 0.9905

LPC 52.85 1.305 0.7603 0.535 0.0000 1.6491 0.8415 1.0832 0.0003

HPC 45.97 5.507 0.8205 8609.601 10.9973 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.780 0.8752 1.301 3.7804 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.837 0.8295 0.656 1.8374 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–57
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2581.16 5835.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0224 742.72 44.37 11.867

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3251 742.72 44.37 5.615

TEGV 0.0000 0.2031 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.77 39.29 16.697

FanDuct 0.0000 0.4690 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 851.12 70.78 32.177

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.77 39.29 16.697

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 950.19 95.16 46.883

Splitter 7.1225 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.77 39.29 16.697

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8959.0 2284.1 3896.1 WB17Y Bleed> 0.3000 1.0000 1.0000 11.9071 532.07 -6.42 8.183

LP_Shaft 1972.0 4570.0 1715.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1723 950.19 95.16 45.803

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7758 950.19 95.16 26.392

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 950.19 95.16 46.883

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 950.19 95.16 46.883

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 950.19 95.16 46.883

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 503.66 -11.54 7.039

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 503.66 -11.54 7.039

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 503.66 -11.54 7.039

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 503.66 -11.54 7.039

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1713.77 0.9995 0.0230 0.23149 0.01131 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.060 0.9801 1.0000 0.9800 613.40 0.292 430.4 374.7

Byp_Nozz 1.329 0.9800 1.0000 0.9800 2006.86 0.650 674.3 6172.1

NASA/TM—2013-218094 N–58
************************************************************************************************************************************ 

Date:05/13/13 Time:10:06:48 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 24/ 52/ 2/21 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 505.23 Stator 1 exit: 508.19 Stator 2 inlet: 510.98 Stator 2 exit: 511.77 

 Stator 3 inlet: 515.13 Stator 3 exit: 515.50 Stator 4 inlet: 518.77 Stator 4 exit: 518.84 

 Stator 5 inlet: 520.73 Stator 5 exit: 520.60 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.01 

Fan Bypass Relative Humidity 5.19 

LPC Inlet Relative Humidity 5.20 

LPC Exit Relative Humidity 2.84 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000250 Inlet Length 40.00 

Ambient Flow Velocity 528.20 Fan/LPC Inlet Flow Velocity 203.11 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 483.18 Fan/LPC Inlet Static Temperature 502.97 

Additional Water at LPC Exit 0.0003085 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 36.00 357.72 763.9 1.1954 913.19 6.3434 528.20 6.256 0.888 10.000 1737.5 1638.0 1166.5

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 357.72 7.943 506.41 -12.46 0.0000 653.97 6.740 483.18 2591.1 0.4900 1.40031 0.0005787 357.51 0.207 0.0006

FS1 Inlet.Fl_O 357.72 7.943 506.41 -12.46 0.0000 653.97 7.531 498.75 4168.2 0.2770 1.40031 0.0005787 357.51 0.207 0.0006

FS12 Splitter.Fl_02 309.01 7.939 506.41 -12.46 0.0000 565.19 7.509 498.41 3531.8 0.2831 1.40031 0.0005787 308.83 0.179 0.0006

FS2 Splitter.Fl_01 48.71 7.939 506.41 -12.46 0.0000 89.10 7.752 502.97 830.5 0.1847 1.40031 0.0005787 48.68 0.028 0.0006

FS14 Fan.Fl_O 309.01 8.480 517.07 -9.90 0.0000 534.68 7.691 502.83 2606.7 0.3762 1.40018 0.0005787 308.83 0.179 0.0006

FS23 LPC.Fl_O 48.71 9.056 534.30 -5.77 0.0000 80.23 8.308 521.29 412.6 0.3531 1.39993 0.0005787 48.68 0.028 0.0006

FS24 VaporIN.Fl_O 48.73 9.056 534.75 -7.44 0.0000 80.29 8.306 521.71 412.6 0.3535 1.39988 0.0008871 48.68 0.043 0.0009

FS25 Bleed2.Fl_O 29.24 9.056 534.75 -7.44 0.0000 48.18 8.802 530.43 412.6 0.2018 1.39988 0.0008871 29.21 0.026 0.0009

FS3 HPC.Fl_O 27.82 49.690 944.13 92.03 0.0000 11.10 44.057 913.08 49.7 0.4203 1.38394 0.0008871 27.79 0.025 0.0009

FS36 Bleed3.Fl_O 21.56 49.690 944.13 92.03 0.0000 8.60 46.443 926.57 49.3 0.3139 1.38394 0.0008871 21.54 0.019 0.0009

FS4 Burner.Fl_O 21.81 48.546 1737.49 78.73 0.0118 12.09 45.838 1712.87 74.6 0.2947 1.32997 0.0008871 21.54 0.019 0.0152

FS45 HPT.Fl_O 29.15 13.284 1171.24 -17.10 0.0088 48.46 12.326 1148.07 265.4 0.3328 1.36361 0.0008871 28.87 0.026 0.0116

FS49 LPT.Fl_O 29.49 7.031 1018.01 -54.27 0.0087 86.36 6.886 1012.29 860.2 0.1740 1.37355 0.0008871 29.21 0.026 0.0115

FS5 TEGV.Fl_O 29.49 7.031 1018.08 -54.27 0.0087 86.36 6.886 1012.36 860.2 0.1741 1.37354 0.0008871 29.21 0.026 0.0115

FS8 Core_Nozz.Fl_O 29.49 7.031 1018.15 -54.27 0.0087 86.36 6.740 1006.52 613.4 0.2486 1.37354 0.0008871 29.21 0.026 0.0115

FS17 FanDuctLkg.Fl_O 309.01 8.480 517.07 -9.90 0.0000 534.68 7.691 502.83 2606.7 0.3762 1.40018 0.0005787 308.83 0.179 0.0006

FS171 Bleed15.Fl_O 328.50 8.480 518.12 -9.76 0.0000 568.98 7.461 499.50 2481.9 0.4315 1.40016 0.0005970 328.30 0.196 0.0006

FS172 FanDuct.Fl_O 328.50 8.480 518.12 -9.76 0.0000 568.98 7.461 499.50 2481.9 0.4315 1.40016 0.0005970 328.30 0.196 0.0006

FS173 Byp_Nozz.Fl_O 328.50 8.480 518.12 -9.76 0.0000 568.98 6.740 485.20 2006.9 0.5822 1.40016 0.0005970 328.30 0.196 0.0006

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 565.19 1.068 0.9035 1815.905 1.0211 0.9044 -1118.3 -1833.94 46.56

LPC 89.10 1.141 0.6960 1815.905 1.0551 0.7016 -461.3 7.12 2.04

HPC 48.18 5.487 0.8076 8765.283 1.7656 0.8467 -4014.5 62.15 58.13

HPT 12.09 3.655 0.8766 213.518 1.3265 0.8567 4014.5 

LPT 48.46 1.889 0.8152 52.429 1.1472 0.8014 1579.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 656.70 1.067 0.9054 1798.590 0.0437 0.8607 1.0235 0.9980 0.9905

LPC 46.03 1.238 0.7547 0.480 0.0000 1.9357 0.5898 0.9221 0.0003

HPC 43.82 5.276 0.8160 8531.607 11.0073 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.581 0.8766 1.283 3.5810 12.6299 0.9723 1.0000 0.0003

LPT 0.74 1.669 0.8213 0.590 1.6689 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–59
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2591.06 5872.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0759 740.95 42.29 13.284

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3421 740.95 42.29 7.031

TEGV 0.0000 0.1740 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.44 37.32 17.995

FanDuct 0.0000 0.4315 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 847.09 68.15 34.249

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.44 37.32 17.995

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 944.13 92.03 49.690

Splitter 6.3434 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.44 37.32 17.995

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8900.1 2369.1 4014.5 WB17Y Bleed> 0.4000 1.0000 1.0000 19.4912 534.75 -7.44 9.056

LP_Shaft 1794.3 4623.6 1579.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3383 944.13 92.03 48.546

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9211 944.13 92.03 28.376

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.13 92.03 49.690

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.13 92.03 49.690

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 944.13 92.03 49.690

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 517.07 -9.90 8.480

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 517.07 -9.90 8.480

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 517.07 -9.90 8.480

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 517.07 -9.90 8.480

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1737.43 0.9995 0.0230 0.25367 0.01178 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.043 0.9801 1.0000 0.9800 613.40 0.249 375.5 344.2

Byp_Nozz 1.258 0.9800 1.0000 0.9800 2006.86 0.582 616.3 6292.4

NASA/TM—2013-218094 N–60
50μm, ISA +18R 

************************************************************************************************************************************ 

Date:07/05/13 Time:09:26:29 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 463.24 Stator 1 exit: 470.64 Stator 2 inlet: 479.94 Stator 2 exit: 484.70 

 Stator 3 inlet: 494.32 Stator 3 exit: 498.64 Stator 4 inlet: 507.63 Stator 4 exit: 511.31 

 Stator 5 inlet: 518.70 Stator 5 exit: 521.92 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.76 

Fan Bypass Relative Humidity 1.24 

LPC Inlet Relative Humidity 1.13 

LPC Exit Relative Humidity 0.10 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 187.91 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 454.80 

Additional Water at LPC Exit 0.0000542 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 257.26 608.4 1.1341 690.03 8.5932 772.64 9.489 0.736 10.000 1693.4 1601.4 1112.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.26 4.267 457.74 -20.96 0.0000 832.41 2.854 407.97 2539.4 0.7800 1.40084 0.0000295 257.26 0.008 0.0000

FS1 Inlet.Fl_O 257.26 4.267 457.74 -20.96 0.0000 832.41 3.893 445.88 4168.2 0.3642 1.40084 0.0000295 257.26 0.008 0.0000

FS12 Splitter.Fl_02 230.45 4.265 457.74 -20.96 0.0000 746.01 3.841 444.23 3531.8 0.3896 1.40084 0.0000295 230.44 0.007 0.0000

FS2 Splitter.Fl_01 26.82 4.265 457.74 -20.96 0.0000 86.81 4.170 454.80 830.5 0.1797 1.40084 0.0000295 26.82 0.001 0.0000

FS14 Fan.Fl_O 230.45 4.811 475.49 -16.70 0.0000 673.99 4.037 452.23 2606.7 0.5066 1.40071 0.0000295 230.44 0.007 0.0000

FS23 LPC.Fl_O 26.82 6.639 531.26 -3.33 0.0000 60.08 6.345 524.42 412.6 0.2553 1.40005 0.0000295 26.82 0.001 0.0000

FS24 VaporIN.Fl_O 26.82 6.639 531.36 -3.62 0.0000 60.09 6.345 524.52 412.6 0.2553 1.40004 0.0000837 26.82 0.002 0.0001

FS25 Bleed2.Fl_O 24.14 6.639 531.36 -3.62 0.0000 54.08 6.403 525.89 412.6 0.2280 1.40004 0.0000837 24.13 0.002 0.0001

FS3 HPC.Fl_O 22.97 40.488 964.30 101.58 0.0000 11.37 35.638 930.77 49.7 0.4331 1.38288 0.0000837 22.96 0.002 0.0001

FS36 Bleed3.Fl_O 17.80 40.488 964.30 101.58 0.0000 8.81 37.704 945.45 49.3 0.3224 1.38288 0.0000837 17.80 0.001 0.0001

FS4 Burner.Fl_O 17.99 39.555 1693.36 89.30 0.0108 12.08 37.354 1669.26 74.6 0.2941 1.33284 0.0000837 17.80 0.001 0.0132

FS45 HPT.Fl_O 24.05 9.489 1116.92 -12.58 0.0080 54.65 8.596 1087.58 265.4 0.3824 1.36774 0.0000837 23.85 0.002 0.0099

FS49 LPT.Fl_O 24.33 3.259 875.30 -71.58 0.0079 142.53 3.069 860.85 860.2 0.2960 1.38276 0.0000837 24.13 0.002 0.0098

FS5 TEGV.Fl_O 24.33 3.259 875.38 -71.58 0.0079 142.53 3.069 860.92 860.2 0.2960 1.38275 0.0000837 24.13 0.002 0.0098

FS8 Core_Nozz.Fl_O 24.33 3.259 875.45 -71.58 0.0079 142.54 2.854 843.84 613.4 0.4418 1.38275 0.0000837 24.13 0.002 0.0098

FS17 FanDuctLkg.Fl_O 230.45 4.811 475.49 -16.70 0.0000 673.99 4.037 452.23 2606.7 0.5066 1.40071 0.0000295 230.44 0.007 0.0000

FS171 Bleed15.Fl_O 233.13 4.811 476.13 -16.55 0.0000 682.30 3.904 448.50 2481.9 0.5544 1.40070 0.0000301 233.12 0.007 0.0000

FS172 FanDuct.Fl_O 233.13 4.811 476.13 -16.55 0.0000 682.30 3.904 448.50 2481.9 0.5544 1.40070 0.0000301 233.12 0.007 0.0000

FS173 Byp_Nozz.Fl_O 233.13 4.811 476.13 -16.55 0.0000 682.30 2.854 410.03 2006.9 0.8967 1.40070 0.0000301 233.12 0.007 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.01 1.128 0.9051 2560.883 1.0388 0.9067 -1386.4 1662.37 54.94

LPC 86.81 1.557 0.8402 2560.883 1.1606 0.8499 -668.8 6.95 3.67

HPC 54.08 6.098 0.8187 8960.639 1.8148 0.8574 -3505.3 61.08 57.75

HPT 12.08 4.168 0.8739 220.402 1.3661 0.8512 3505.3 

LPT 54.65 2.912 0.8506 71.985 1.2742 0.8304 2055.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 866.79 1.125 0.9070 2536.465 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 73.59 1.519 0.7796 0.676 0.0000 1.1797 1.0734 1.0778 0.0003

HPC 49.18 5.858 0.8271 8721.754 10.9930 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.081 0.8739 1.325 4.0806 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.438 0.8569 0.810 2.4380 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–61
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2539.40 6178.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8882 749.57 48.98 9.489

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2824 749.57 48.98 3.259

TEGV 0.0000 0.2960 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 727.87 43.72 14.086

FanDuct 0.0000 0.5544 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 861.79 76.33 27.625

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 727.87 43.72 14.086

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 964.30 101.58 40.488

Splitter 8.5932 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 727.87 43.72 14.086

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9069.6 2029.9 3505.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6819 531.36 -3.62 6.639

LP_Shaft 2405.8 4486.7 2055.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7560 964.30 101.58 39.555

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4115 964.30 101.58 22.357

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.30 101.58 40.488

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.30 101.58 40.488 

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.30 101.58 40.488

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.49 -16.70 4.811

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.49 -16.70 4.811

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.49 -16.70 4.811

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.49 -16.70 4.811

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1693.29 0.9995 0.0230 0.19168 0.01077 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.142 0.9801 1.0000 0.9800 613.40 0.442 613.1 463.6

Byp_Nozz 1.686 0.9800 1.0000 0.9800 2006.86 0.897 872.6 6322.8

NASA/TM—2013-218094 N–62
************************************************************************************************************************************ 

Date:07/05/13 Time:09:26:46 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.76 Stator 1 exit: 463.69 Stator 2 inlet: 472.40 Stator 2 exit: 476.84 

 Stator 3 inlet: 485.83 Stator 3 exit: 489.85 Stator 4 inlet: 498.26 Stator 4 exit: 501.67 

 Stator 5 inlet: 508.57 Stator 5 exit: 511.54 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.23 

Fan Bypass Relative Humidity 1.61 

LPC Inlet Relative Humidity 1.45 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 723.11 Fan/LPC Inlet Flow Velocity 181.25 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 448.83 

Additional Water at LPC Exit 0.0000485 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 18.00 250.31 599.3 1.0980 657.99 8.6866 723.11 9.209 0.763 10.000 1667.2 1575.9 1097.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 250.31 4.201 451.57 -22.43 0.0000 816.95 2.947 407.97 2556.8 0.7300 1.40089 0.0000285 250.30 0.007 0.0000

FS1 Inlet.Fl_O 250.31 4.201 451.57 -22.43 0.0000 816.95 3.848 440.36 4168.2 0.3563 1.40089 0.0000285 250.30 0.007 0.0000

FS12 Splitter.Fl_02 224.47 4.199 451.57 -22.43 0.0000 732.97 3.798 438.77 3531.8 0.3813 1.40089 0.0000285 224.46 0.006 0.0000

FS2 Splitter.Fl_01 25.84 4.199 451.57 -22.43 0.0000 84.38 4.111 448.83 830.5 0.1745 1.40089 0.0000285 25.84 0.001 0.0000

FS14 Fan.Fl_O 224.47 4.706 468.12 -18.46 0.0000 665.89 3.972 445.95 2606.7 0.4981 1.40077 0.0000285 224.46 0.006 0.0000

FS23 LPC.Fl_O 25.84 6.402 520.42 -5.92 0.0000 59.42 6.125 513.88 412.6 0.2522 1.40021 0.0000285 25.84 0.001 0.0000

FS24 VaporIN.Fl_O 25.84 6.402 520.52 -6.18 0.0000 59.43 6.125 513.97 412.6 0.2523 1.40020 0.0000770 25.84 0.002 0.0001

FS25 Bleed2.Fl_O 23.26 6.402 520.52 -6.18 0.0000 53.49 6.179 515.28 412.6 0.2253 1.40020 0.0000770 23.26 0.002 0.0001

FS3 HPC.Fl_O 22.13 38.692 942.96 96.34 0.0000 11.33 34.090 910.34 49.7 0.4313 1.38414 0.0000770 22.13 0.002 0.0001

FS36 Bleed3.Fl_O 17.15 38.692 942.96 96.34 0.0000 8.78 36.048 924.60 49.3 0.3212 1.38414 0.0000770 17.15 0.001 0.0001

FS4 Burner.Fl_O 17.33 37.801 1667.21 84.23 0.0107 12.08 35.696 1643.41 74.6 0.2940 1.33417 0.0000770 17.15 0.001 0.0131

FS45 HPT.Fl_O 23.17 9.183 1101.02 -15.03 0.0080 54.02 8.341 1072.82 265.4 0.3770 1.36883 0.0000770 22.98 0.002 0.0098

FS49 LPT.Fl_O 23.44 3.309 873.17 -70.51 0.0079 135.06 3.137 860.35 860.2 0.2789 1.38293 0.0000770 23.26 0.002 0.0097

FS5 TEGV.Fl_O 23.44 3.309 873.25 -70.51 0.0079 135.07 3.137 860.42 860.2 0.2789 1.38293 0.0000770 23.26 0.002 0.0097

FS8 Core_Nozz.Fl_O 23.44 3.309 873.32 -70.51 0.0079 135.08 2.947 845.68 613.4 0.4127 1.38292 0.0000770 23.26 0.002 0.0097

FS17 FanDuctLkg.Fl_O 224.47 4.706 468.12 -18.46 0.0000 665.89 3.972 445.95 2606.7 0.4981 1.40077 0.0000285 224.46 0.006 0.0000

FS171 Bleed15.Fl_O 227.05 4.706 468.72 -18.32 0.0000 673.99 3.848 442.46 2481.9 0.5441 1.40077 0.0000291 227.04 0.007 0.0000

FS172 FanDuct.Fl_O 227.05 4.706 468.72 -18.32 0.0000 673.99 3.848 442.46 2481.9 0.5441 1.40077 0.0000291 227.04 0.007 0.0000

FS173 Byp_Nozz.Fl_O 227.05 4.706 468.72 -18.32 0.0000 673.99 2.947 409.94 2006.9 0.8457 1.40077 0.0000291 227.04 0.007 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 732.97 1.121 0.9043 2497.804 1.0367 0.9059 -1259.8 2276.91 54.77

LPC 84.38 1.524 0.8406 2497.804 1.1525 0.8498 -603.5 6.76 3.33

HPC 53.49 6.044 0.8179 8941.570 1.8116 0.8566 -3291.6 60.99 57.61

HPT 12.08 4.116 0.8726 219.377 1.3628 0.8499 3291.6 

LPT 54.02 2.775 0.8451 70.239 1.2589 0.8253 1863.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 851.64 1.118 0.9062 2473.988 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 70.86 1.491 0.7766 0.660 0.0000 1.1908 1.0692 1.0824 0.0003

HPC 48.64 5.806 0.8263 8703.194 11.0056 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.030 0.8726 1.318 4.0300 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.335 0.8514 0.790 2.3350 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–63
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2556.80 5625.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8559 733.31 45.08 9.183

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2721 733.31 45.08 3.309

TEGV 0.0000 0.2789 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.14 39.95 13.506

FanDuct 0.0000 0.5441 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 842.84 71.73 26.422

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.14 39.95 13.506

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 942.96 96.34 38.692

Splitter 8.6866 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.14 39.95 13.506

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8957.5 1930.0 3291.6 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5842 520.52 -6.18 6.402

LP_Shaft 2330.6 4198.8 1863.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6556 942.96 96.34 37.801

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3237 942.96 96.34 21.431

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 942.96 96.34 38.692

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 942.96 96.34 38.692

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 942.96 96.34 38.692

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1667.15 0.9995 0.0230 0.18278 0.01066 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.123 0.9801 1.0000 0.9800 613.40 0.413 573.4 417.7

Byp_Nozz 1.597 0.9800 1.0000 0.9800 2006.86 0.846 822.9 5807.2

NASA/TM—2013-218094 N–64
************************************************************************************************************************************ 

Date:07/05/13 Time:09:27:02 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 454.76 Stator 1 exit: 461.52 Stator 2 inlet: 470.01 Stator 2 exit: 474.34 

 Stator 3 inlet: 483.09 Stator 3 exit: 487.01 Stator 4 inlet: 495.20 Stator 4 exit: 498.51 

 Stator 5 inlet: 505.23 Stator 5 exit: 508.11 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.40 

Fan Bypass Relative Humidity 1.75 

LPC Inlet Relative Humidity 1.56 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 707.26 Fan/LPC Inlet Flow Velocity 178.68 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 447.01 

Additional Water at LPC Exit 0.0000445 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 18.00 257.06 614.4 1.0902 669.83 8.7256 707.26 9.092 0.772 10.000 1657.3 1566.3 1091.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.06 4.339 449.68 -22.87 0.0000 810.62 3.088 407.97 2561.5 0.7140 1.40090 0.0000272 257.05 0.007 0.0000

FS1 Inlet.Fl_O 257.06 4.339 449.68 -22.87 0.0000 810.62 3.981 438.72 4168.2 0.3530 1.40090 0.0000272 257.05 0.007 0.0000

FS12 Splitter.Fl_02 230.63 4.337 449.68 -22.87 0.0000 727.63 3.930 437.15 3531.8 0.3780 1.40090 0.0000272 230.62 0.006 0.0000

FS2 Splitter.Fl_01 26.43 4.337 449.68 -22.87 0.0000 83.39 4.248 447.01 830.5 0.1723 1.40090 0.0000272 26.43 0.001 0.0000

FS14 Fan.Fl_O 230.63 4.848 465.79 -19.01 0.0000 662.46 4.102 444.03 2606.7 0.4945 1.40079 0.0000272 230.62 0.006 0.0000

FS23 LPC.Fl_O 26.43 6.557 516.81 -6.78 0.0000 59.13 6.276 510.38 412.6 0.2509 1.40025 0.0000272 26.43 0.001 0.0000

FS24 VaporIN.Fl_O 26.43 6.557 516.90 -7.02 0.0000 59.14 6.276 510.47 412.6 0.2509 1.40025 0.0000717 26.43 0.002 0.0001

FS25 Bleed2.Fl_O 23.79 6.557 516.90 -7.02 0.0000 53.22 6.332 511.75 412.6 0.2241 1.40025 0.0000717 23.79 0.002 0.0001

FS3 HPC.Fl_O 22.64 39.452 935.48 94.52 0.0000 11.32 34.769 903.16 49.7 0.4307 1.38458 0.0000717 22.63 0.002 0.0001

FS36 Bleed3.Fl_O 17.54 39.452 935.48 94.52 0.0000 8.78 36.762 917.29 49.3 0.3209 1.38458 0.0000717 17.54 0.001 0.0001

FS4 Burner.Fl_O 17.73 38.544 1657.32 82.49 0.0106 12.08 36.397 1633.62 74.6 0.2940 1.33468 0.0000717 17.54 0.001 0.0130

FS45 HPT.Fl_O 23.70 9.404 1095.02 -15.81 0.0079 53.81 8.550 1067.20 265.4 0.3751 1.36925 0.0000717 23.51 0.002 0.0098

FS49 LPT.Fl_O 23.98 3.450 872.21 -70.01 0.0078 132.45 3.278 859.93 860.2 0.2730 1.38301 0.0000717 23.79 0.002 0.0097

FS5 TEGV.Fl_O 23.98 3.450 872.29 -70.01 0.0078 132.45 3.278 860.00 860.2 0.2730 1.38300 0.0000717 23.79 0.002 0.0097

FS8 Core_Nozz.Fl_O 23.98 3.450 872.36 -70.01 0.0078 132.46 3.088 846.01 613.4 0.4028 1.38300 0.0000717 23.79 0.002 0.0097

FS17 FanDuctLkg.Fl_O 230.63 4.848 465.79 -19.01 0.0000 662.46 4.102 444.03 2606.7 0.4945 1.40079 0.0000272 230.62 0.006 0.0000

FS171 Bleed15.Fl_O 233.27 4.848 466.37 -18.88 0.0000 670.47 3.976 440.63 2481.9 0.5399 1.40078 0.0000277 233.27 0.006 0.0000

FS172 FanDuct.Fl_O 233.27 4.848 466.37 -18.88 0.0000 670.47 3.976 440.63 2481.9 0.5399 1.40078 0.0000277 233.27 0.006 0.0000

FS173 Byp_Nozz.Fl_O 233.27 4.848 466.37 -18.88 0.0000 670.47 3.088 409.90 2006.9 0.8289 1.40078 0.0000277 233.27 0.006 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 727.63 1.118 0.9040 2472.475 1.0358 0.9055 -1260.2 2677.24 54.68

LPC 83.39 1.512 0.8407 2472.475 1.1493 0.8497 -601.8 6.67 3.26

HPC 53.22 6.016 0.8174 8933.056 1.8098 0.8562 -3334.7 61.04 57.63

HPT 12.08 4.099 0.8721 219.055 1.3617 0.8494 3334.7 

LPT 53.81 2.726 0.8431 69.571 1.2534 0.8234 1861.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 845.44 1.115 0.9058 2448.900 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 69.76 1.479 0.7754 0.653 0.0000 1.1954 1.0682 1.0842 0.0003

HPC 48.41 5.780 0.8259 8694.906 11.0056 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.013 0.8721 1.316 4.0128 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.298 0.8493 0.783 2.2982 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–65
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.47 5650.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8754 727.71 43.75 9.404

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2783 727.71 43.75 3.450

TEGV 0.0000 0.2730 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 706.73 38.67 13.794

FanDuct 0.0000 0.5399 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 836.24 70.15 26.952

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 706.73 38.67 13.794

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 935.48 94.52 39.452

Splitter 8.7256 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 706.73 38.67 13.794

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8917.8 1963.9 3334.7 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6433 516.90 -7.02 6.557

LP_Shaft 2302.2 4247.8 1861.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7163 935.48 94.52 38.544

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3768 935.48 94.52 21.876

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.48 94.52 39.452

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.48 94.52 39.452

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.48 94.52 39.452

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1657.26 0.9995 0.0230 0.18606 0.01061 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.403 559.8 417.1

Byp_Nozz 1.570 0.9800 1.0000 0.9800 2006.86 0.829 806.6 5848.1

NASA/TM—2013-218094 N–66
************************************************************************************************************************************ 

Date:07/05/13 Time:09:27:18 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.41 Stator 1 exit: 462.77 Stator 2 inlet: 470.73 Stator 2 exit: 474.78 

 Stator 3 inlet: 482.99 Stator 3 exit: 486.64 Stator 4 inlet: 494.31 Stator 4 exit: 497.39 

 Stator 5 inlet: 503.67 Stator 5 exit: 506.33 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.00 

Fan Bypass Relative Humidity 2.26 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.22 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 667.90 Fan/LPC Inlet Flow Velocity 173.04 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 414.42 Fan/LPC Inlet Static Temperature 449.11 

Additional Water at LPC Exit 0.0000322 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 18.00 278.58 669.5 1.0739 719.01 8.8076 667.90 8.757 0.795 10.000 1650.5 1559.4 1088.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 278.58 4.831 451.61 -22.45 0.0000 790.74 3.578 414.42 2577.4 0.6690 1.40088 0.0000348 278.57 0.010 0.0000

FS1 Inlet.Fl_O 278.58 4.831 451.61 -22.45 0.0000 790.74 4.453 441.21 4168.2 0.3430 1.40088 0.0000348 278.57 0.010 0.0000

FS12 Splitter.Fl_02 250.17 4.829 451.61 -22.45 0.0000 710.47 4.399 439.71 3531.8 0.3674 1.40088 0.0000348 250.16 0.009 0.0000

FS2 Splitter.Fl_01 28.40 4.829 451.61 -22.45 0.0000 80.67 4.736 449.11 830.5 0.1665 1.40088 0.0000348 28.40 0.001 0.0000

FS14 Fan.Fl_O 250.17 5.360 466.78 -18.82 0.0000 650.68 4.571 445.97 2606.7 0.4824 1.40078 0.0000348 250.16 0.009 0.0000

FS23 LPC.Fl_O 28.40 7.122 514.69 -7.33 0.0000 58.39 6.825 508.46 412.6 0.2475 1.40028 0.0000348 28.40 0.001 0.0000

FS24 VaporIN.Fl_O 28.40 7.122 514.77 -7.50 0.0000 58.39 6.825 508.53 412.6 0.2475 1.40028 0.0000670 28.40 0.002 0.0001

FS25 Bleed2.Fl_O 25.56 7.122 514.77 -7.50 0.0000 52.55 6.883 509.78 412.6 0.2211 1.40028 0.0000670 25.56 0.002 0.0001

FS3 HPC.Fl_O 24.32 42.305 928.66 92.86 0.0000 11.31 37.301 896.67 49.7 0.4298 1.38497 0.0000670 24.32 0.002 0.0001

FS36 Bleed3.Fl_O 18.85 42.305 928.66 92.86 0.0000 8.76 39.429 910.65 49.3 0.3203 1.38497 0.0000670 18.85 0.001 0.0001

FS4 Burner.Fl_O 19.05 41.330 1650.47 80.87 0.0106 12.08 39.027 1626.86 74.6 0.2940 1.33503 0.0000670 18.85 0.001 0.0130

FS45 HPT.Fl_O 25.47 10.192 1092.43 -16.28 0.0079 53.29 9.287 1065.30 265.4 0.3708 1.36943 0.0000670 25.26 0.002 0.0097

FS49 LPT.Fl_O 25.76 3.941 881.38 -67.55 0.0078 125.23 3.767 870.38 860.2 0.2569 1.38250 0.0000670 25.56 0.002 0.0096

FS5 TEGV.Fl_O 25.76 3.941 881.45 -67.55 0.0078 125.23 3.767 870.45 860.2 0.2569 1.38250 0.0000670 25.56 0.002 0.0096

FS8 Core_Nozz.Fl_O 25.76 3.941 881.52 -67.55 0.0078 125.24 3.578 858.21 613.4 0.3764 1.38249 0.0000670 25.56 0.002 0.0096

FS17 FanDuctLkg.Fl_O 250.17 5.360 466.78 -18.82 0.0000 650.68 4.571 445.97 2606.7 0.4824 1.40078 0.0000348 250.16 0.009 0.0000

FS171 Bleed15.Fl_O 253.01 5.360 467.32 -18.69 0.0000 658.44 4.440 442.79 2481.9 0.5256 1.40078 0.0000351 253.00 0.009 0.0000

FS172 FanDuct.Fl_O 253.01 5.360 467.32 -18.69 0.0000 658.44 4.440 442.79 2481.9 0.5256 1.40078 0.0000351 253.00 0.009 0.0000

FS173 Byp_Nozz.Fl_O 253.01 5.360 467.32 -18.69 0.0000 658.44 3.578 416.27 2006.9 0.7821 1.40078 0.0000351 253.00 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.47 1.110 0.9032 2395.792 1.0336 0.9046 -1286.3 5784.67 54.21

LPC 80.67 1.475 0.8416 2395.792 1.1397 0.8501 -607.7 6.41 3.05

HPC 52.55 5.940 0.8161 8911.057 1.8040 0.8550 -3542.1 61.34 57.85

HPT 12.08 4.055 0.8716 218.517 1.3586 0.8490 3542.1 

LPT 53.29 2.586 0.8385 67.638 1.2372 0.8195 1894.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.49 1.108 0.9050 2372.948 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.44 1.445 0.7718 0.633 0.0000 1.2141 1.0673 1.0904 0.0003

HPC 47.80 5.707 0.8246 8673.494 10.9958 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.970 0.8716 1.313 3.9703 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.193 0.8448 0.761 2.1929 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–67
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2577.38 5782.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9408 723.18 42.68 10.192

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2991 723.18 42.68 3.941

TEGV 0.0000 0.2569 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.44 37.66 14.862

FanDuct 0.0000 0.5256 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 830.51 68.77 28.935

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.44 37.66 14.862

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 928.66 92.86 42.305

Splitter 8.8076 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.44 37.66 14.862

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8877.5 2095.6 3542.1 WB17Y Bleed> 0.1000 1.0000 1.0000 2.8405 514.77 -7.50 7.122

LP_Shaft 2235.6 4449.7 1894.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.9190 928.66 92.86 41.330

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5541 928.66 92.86 23.519

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.66 92.86 42.305

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.66 92.86 42.305

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.66 92.86 42.305

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 466.78 -18.82 5.360

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1650.41 0.9995 0.0230 0.19972 0.01060 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.376 526.7 421.8

Byp_Nozz 1.498 0.9800 1.0000 0.9800 2006.86 0.782 766.9 6030.7

NASA/TM—2013-218094 N–68
************************************************************************************************************************************ 

Date:07/05/13 Time:09:27:35 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 14/ 28/ 1/12 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.04 Stator 1 exit: 470.56 Stator 2 inlet: 477.37 Stator 2 exit: 480.66 

 Stator 3 inlet: 487.79 Stator 3 exit: 490.68 Stator 4 inlet: 497.38 Stator 4 exit: 499.77 

 Stator 5 inlet: 505.17 Stator 5 exit: 507.19 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.96 

Fan Bypass Relative Humidity 3.12 

LPC Inlet Relative Humidity 2.83 

LPC Exit Relative Humidity 0.47 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 617.99 Fan/LPC Inlet Flow Velocity 174.99 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 429.58 Fan/LPC Inlet Static Temperature 458.86 

Additional Water at LPC Exit 0.0000397 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 18.00 305.09 728.9 1.0766 784.71 8.3707 617.99 8.197 0.828 10.000 1654.9 1563.1 1093.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 305.09 5.595 461.42 -20.30 0.0000 755.82 4.358 429.58 2596.2 0.6080 1.40081 0.0000681 305.07 0.021 0.0001

FS1 Inlet.Fl_O 305.09 5.595 461.42 -20.30 0.0000 755.82 5.199 451.82 4168.2 0.3256 1.40081 0.0000681 305.07 0.021 0.0001

FS12 Splitter.Fl_02 272.54 5.592 461.42 -20.30 0.0000 675.50 5.147 450.59 3531.8 0.3462 1.40081 0.0000681 272.52 0.019 0.0001

FS2 Splitter.Fl_01 32.56 5.592 461.42 -20.30 0.0000 80.70 5.485 458.86 830.5 0.1666 1.40081 0.0000681 32.56 0.002 0.0001

FS14 Fan.Fl_O 272.54 6.139 475.25 -16.98 0.0000 624.50 5.321 456.19 2606.7 0.4566 1.40070 0.0000681 272.52 0.019 0.0001

FS23 LPC.Fl_O 32.56 7.826 515.84 -7.25 0.0000 60.97 7.468 508.98 412.6 0.2594 1.40026 0.0000681 32.56 0.002 0.0001

FS24 VaporIN.Fl_O 32.56 7.826 515.92 -7.46 0.0000 60.98 7.468 509.07 412.6 0.2594 1.40025 0.0001078 32.56 0.004 0.0001

FS25 Bleed2.Fl_O 27.68 7.826 515.92 -7.46 0.0000 51.83 7.571 511.07 412.6 0.2179 1.40025 0.0001078 27.67 0.003 0.0001

FS3 HPC.Fl_O 26.33 45.862 927.46 92.34 0.0000 11.28 40.463 895.68 49.7 0.4287 1.38504 0.0001078 26.33 0.003 0.0001

FS36 Bleed3.Fl_O 20.41 45.862 927.46 92.34 0.0000 8.74 42.759 909.56 49.3 0.3195 1.38504 0.0001078 20.41 0.002 0.0001

FS4 Burner.Fl_O 20.63 44.806 1654.85 80.25 0.0107 12.08 42.309 1631.18 74.6 0.2940 1.33474 0.0001078 20.41 0.002 0.0131

FS45 HPT.Fl_O 27.57 11.202 1098.00 -16.30 0.0080 52.62 10.234 1071.52 265.4 0.3654 1.36902 0.0001078 27.35 0.003 0.0099

FS49 LPT.Fl_O 27.89 4.717 904.54 -63.23 0.0079 114.77 4.543 895.19 860.2 0.2340 1.38113 0.0001078 27.67 0.003 0.0098

FS5 TEGV.Fl_O 27.89 4.717 904.61 -63.23 0.0079 114.77 4.543 895.26 860.2 0.2340 1.38112 0.0001078 27.67 0.003 0.0098

FS8 Core_Nozz.Fl_O 27.89 4.717 904.68 -63.23 0.0079 114.78 4.358 885.15 613.4 0.3400 1.38112 0.0001078 27.67 0.003 0.0098

FS17 FanDuctLkg.Fl_O 272.54 6.139 475.25 -16.98 0.0000 624.50 5.321 456.19 2606.7 0.4566 1.40070 0.0000681 272.52 0.019 0.0001

FS171 Bleed15.Fl_O 277.42 6.139 475.96 -16.82 0.0000 636.17 5.173 453.22 2481.9 0.5005 1.40070 0.0000688 277.40 0.019 0.0001

FS172 FanDuct.Fl_O 277.42 6.139 475.96 -16.82 0.0000 636.17 5.173 453.22 2481.9 0.5005 1.40070 0.0000688 277.40 0.019 0.0001

FS173 Byp_Nozz.Fl_O 277.42 6.139 475.96 -16.82 0.0000 636.17 4.358 431.52 2006.9 0.7168 1.40070 0.0000688 277.40 0.019 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 675.50 1.098 0.9021 2249.411 1.0300 0.9034 -1278.1 -9306.19 52.72

LPC 80.70 1.399 0.8552 2249.411 1.1179 0.8619 -601.0 5.96 2.63

HPC 51.83 5.860 0.8147 8887.489 1.7977 0.8536 -3813.0 61.61 58.03

HPT 12.08 4.000 0.8718 217.895 1.3544 0.8495 3812.9 

LPT 52.62 2.375 0.8303 64.028 1.2114 0.8124 1879.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 784.86 1.096 0.9039 2227.963 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 60.32 1.382 0.7655 0.594 0.0000 1.3379 1.0459 1.1172 0.0003

HPC 47.14 5.631 0.8231 8650.554 10.9887 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.917 0.8718 1.310 3.9166 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.034 0.8365 0.720 2.0342 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–69
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.15 5860.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0185 723.14 42.44 11.202

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3238 723.14 42.44 4.717

TEGV 0.0000 0.2340 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.52 37.45 16.194

FanDuct 0.0000 0.5005 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 829.87 68.38 31.408

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.52 37.45 16.194

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 927.46 92.34 45.862

Splitter 8.3707 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.52 37.45 16.194

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8863.9 2259.3 3812.9 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8839 515.92 -7.46 7.826

LP_Shaft 2121.6 4651.8 1879.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1600 927.46 92.34 44.806

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7651 927.46 92.34 25.585

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.46 92.34 45.862

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.46 92.34 45.862

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.46 92.34 45.862

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1654.79 0.9995 0.0230 0.21797 0.01068 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 482.9 418.6

Byp_Nozz 1.409 0.9800 1.0000 0.9800 2006.86 0.717 715.6 6170.4

NASA/TM—2013-218094 N–70
************************************************************************************************************************************ 

Date:07/05/13 Time:09:27:57 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 36/ 1/20 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.11 Stator 1 exit: 477.17 Stator 2 inlet: 481.78 Stator 2 exit: 483.58 

 Stator 3 inlet: 488.72 Stator 3 exit: 490.11 Stator 4 inlet: 495.04 Stator 4 exit: 496.04 

 Stator 5 inlet: 499.63 Stator 5 exit: 500.35 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.82 

Fan Bypass Relative Humidity 3.94 

LPC Inlet Relative Humidity 3.82 

LPC Exit Relative Humidity 1.20 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 571.13 Fan/LPC Inlet Flow Velocity 194.56 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.36 

Ambient Static Temperature 445.14 Fan/LPC Inlet Static Temperature 469.17 

Additional Water at LPC Exit 0.0000436 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 18.00 330.54 748.3 1.1193 837.60 7.0492 571.13 7.334 0.859 10.000 1665.6 1571.6 1105.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 330.54 6.516 472.33 -18.03 0.0000 711.38 5.297 445.14 2595.0 0.5520 1.40072 0.0001274 330.50 0.042 0.0001

FS1 Inlet.Fl_O 330.54 6.516 472.33 -18.03 0.0000 711.38 6.111 463.74 4168.2 0.3040 1.40072 0.0001274 330.50 0.042 0.0001

FS12 Splitter.Fl_02 289.48 6.513 472.33 -18.03 0.0000 623.31 6.078 463.07 3531.8 0.3157 1.40072 0.0001274 289.44 0.037 0.0001

FS2 Splitter.Fl_01 41.06 6.513 472.33 -18.03 0.0000 88.42 6.362 469.17 830.5 0.1832 1.40072 0.0001274 41.06 0.005 0.0001

FS14 Fan.Fl_O 289.48 7.057 484.46 -15.12 0.0000 582.63 6.258 468.09 2606.7 0.4177 1.40061 0.0001274 289.44 0.037 0.0001

FS23 LPC.Fl_O 41.06 8.206 511.58 -8.61 0.0000 73.04 7.654 501.50 412.6 0.3168 1.40031 0.0001274 41.06 0.005 0.0001

FS24 VaporIN.Fl_O 41.07 8.206 511.67 -8.85 0.0000 73.05 7.654 501.59 412.6 0.3169 1.40030 0.0001709 41.06 0.007 0.0002

FS25 Bleed2.Fl_O 28.75 8.206 511.67 -8.85 0.0000 51.14 7.946 506.99 412.6 0.2148 1.40030 0.0001709 28.74 0.005 0.0002

FS3 HPC.Fl_O 27.35 47.792 918.60 89.79 0.0000 11.19 42.271 887.70 49.7 0.4243 1.38554 0.0001709 27.35 0.005 0.0002

FS36 Bleed3.Fl_O 21.20 47.792 918.60 89.79 0.0000 8.67 44.614 901.16 49.3 0.3166 1.38554 0.0001709 21.19 0.004 0.0002

FS4 Burner.Fl_O 21.43 46.691 1665.62 77.40 0.0110 12.09 44.088 1641.82 74.6 0.2942 1.33401 0.0001709 21.19 0.004 0.0136

FS45 HPT.Fl_O 28.64 12.030 1109.37 -17.89 0.0082 51.17 11.053 1084.34 265.4 0.3537 1.36811 0.0001709 28.41 0.005 0.0102

FS49 LPT.Fl_O 28.98 5.626 937.03 -59.60 0.0081 101.74 5.464 929.54 860.2 0.2061 1.37905 0.0001709 28.74 0.005 0.0101

FS5 TEGV.Fl_O 28.98 5.626 937.10 -59.60 0.0081 101.75 5.464 929.61 860.2 0.2061 1.37904 0.0001709 28.74 0.005 0.0101

FS8 Core_Nozz.Fl_O 28.98 5.626 937.18 -59.60 0.0081 101.75 5.297 921.76 613.4 0.2968 1.37904 0.0001709 28.74 0.005 0.0101

FS17 FanDuctLkg.Fl_O 289.48 7.057 484.46 -15.12 0.0000 582.63 6.258 468.09 2606.7 0.4177 1.40061 0.0001274 289.44 0.037 0.0001

FS171 Bleed15.Fl_O 301.80 7.057 485.57 -14.86 0.0000 608.12 6.063 464.95 2481.9 0.4705 1.40060 0.0001291 301.76 0.039 0.0001

FS172 FanDuct.Fl_O 301.80 7.057 485.57 -14.86 0.0000 608.12 6.063 464.95 2481.9 0.4705 1.40060 0.0001291 301.76 0.039 0.0001

FS173 Byp_Nozz.Fl_O 301.80 7.057 485.57 -14.86 0.0000 608.12 5.297 447.31 2006.9 0.6533 1.40060 0.0001291 301.76 0.039 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.31 1.083 0.9032 2044.668 1.0257 0.9043 -1191.1 -2766.16 49.88

LPC 88.42 1.260 0.8218 2044.668 1.0831 0.8276 -546.8 6.38 2.41

HPC 51.14 5.824 0.8139 8865.693 1.7953 0.8529 -3914.5 60.72 57.10

HPT 12.09 3.881 0.8732 215.761 1.3457 0.8517 3914.5 

LPT 51.17 2.138 0.8210 58.581 1.1810 0.8047 1737.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.23 1.082 0.9050 2025.172 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.47 1.311 0.7607 0.540 0.0000 1.6537 0.8353 1.0803 0.0003

HPC 46.51 5.597 0.8223 8629.340 11.0519 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.801 0.8732 1.297 3.8014 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.856 0.8271 0.659 1.8561 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–71
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2595.01 5867.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0579 716.52 40.47 12.030

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3363 716.52 40.47 5.626

TEGV 0.0000 0.2061 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.13 35.54 16.915

FanDuct 0.0000 0.4705 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 822.06 66.12 32.749

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.13 35.54 16.915

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 918.60 89.79 47.792

Splitter 7.0492 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.13 35.54 16.915

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8805.7 2334.8 3914.5 WB17Y Bleed> 0.3000 1.0000 1.0000 12.3200 511.67 -8.85 8.206

LP_Shaft 1951.2 4678.1 1737.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2823 918.60 89.79 46.691

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8721 918.60 89.79 26.865

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.60 89.79 47.792

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.60 89.79 47.792

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.60 89.79 47.792

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1665.56 0.9995 0.0230 0.23267 0.01098 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.297 429.9 387.2

Byp_Nozz 1.332 0.9800 1.0000 0.9800 2006.86 0.653 664.0 6228.6

NASA/TM—2013-218094 N–72
************************************************************************************************************************************ 

Date:07/05/13 Time:09:28:20 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 26/ 40/ 1/24 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 486.26 Stator 1 exit: 489.21 Stator 2 inlet: 491.94 Stator 2 exit: 492.70 

 Stator 3 inlet: 496.03 Stator 3 exit: 496.35 Stator 4 inlet: 499.60 Stator 4 exit: 499.62 

 Stator 5 inlet: 501.46 Stator 5 exit: 501.30 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.85 

Fan Bypass Relative Humidity 4.91 

LPC Inlet Relative Humidity 5.02 

LPC Exit Relative Humidity 2.62 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 518.26 Fan/LPC Inlet Flow Velocity 204.34 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.74 

Ambient Static Temperature 465.18 Fan/LPC Inlet Static Temperature 484.08 

Additional Water at LPC Exit 0.0000541 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 18.00 368.15 831.7 1.1214 932.67 6.2370 518.26 6.453 0.890 10.000 1698.7 1600.6 1135.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 368.15 7.943 487.56 -15.16 0.0000 660.37 6.740 465.18 2616.0 0.4900 1.40057 0.0002627 368.05 0.097 0.0003

FS1 Inlet.Fl_O 368.15 7.943 487.56 -15.16 0.0000 660.37 7.522 480.02 4168.2 0.2799 1.40057 0.0002627 368.05 0.097 0.0003

FS12 Splitter.Fl_02 317.28 7.939 487.56 -15.16 0.0000 569.40 7.503 479.73 3531.8 0.2854 1.40057 0.0002627 317.19 0.083 0.0003

FS2 Splitter.Fl_01 50.87 7.939 487.56 -15.16 0.0000 91.29 7.743 484.08 830.5 0.1894 1.40057 0.0002627 50.86 0.013 0.0003

FS14 Fan.Fl_O 317.28 8.512 498.39 -12.56 0.0000 536.97 7.712 484.52 2606.7 0.3780 1.40045 0.0002627 317.19 0.083 0.0003

FS23 LPC.Fl_O 50.87 9.078 515.18 -8.53 0.0000 82.08 8.289 501.97 412.6 0.3626 1.40024 0.0002627 50.86 0.013 0.0003

FS24 VaporIN.Fl_O 50.87 9.078 515.28 -8.82 0.0000 82.09 8.289 502.06 412.6 0.3627 1.40023 0.0003168 50.86 0.016 0.0003

FS25 Bleed2.Fl_O 30.52 9.078 515.28 -8.82 0.0000 49.25 8.812 510.92 412.6 0.2065 1.40023 0.0003168 30.51 0.010 0.0003

FS3 HPC.Fl_O 29.04 51.262 917.93 88.80 0.0000 11.08 45.481 887.82 49.7 0.4188 1.38556 0.0003168 29.03 0.009 0.0003

FS36 Bleed3.Fl_O 22.51 51.262 917.93 88.80 0.0000 8.58 47.929 900.90 49.3 0.3129 1.38556 0.0003168 22.50 0.007 0.0003

FS4 Burner.Fl_O 22.77 50.081 1698.67 75.82 0.0115 12.09 47.287 1674.48 74.6 0.2946 1.33204 0.0003168 22.50 0.007 0.0143

FS45 HPT.Fl_O 30.43 13.553 1140.38 -18.27 0.0086 48.92 12.555 1117.24 265.4 0.3361 1.36580 0.0003168 30.16 0.010 0.0108

FS49 LPT.Fl_O 30.78 7.047 987.09 -55.31 0.0085 88.56 6.895 981.21 860.2 0.1785 1.37572 0.0003168 30.51 0.010 0.0107

FS5 TEGV.Fl_O 30.78 7.047 987.16 -55.31 0.0085 88.56 6.895 981.28 860.2 0.1785 1.37571 0.0003168 30.51 0.010 0.0107

FS8 Core_Nozz.Fl_O 30.78 7.047 987.23 -55.31 0.0085 88.56 6.740 975.28 613.4 0.2552 1.37571 0.0003168 30.51 0.010 0.0107

FS17 FanDuctLkg.Fl_O 317.28 8.512 498.39 -12.56 0.0000 536.97 7.712 484.52 2606.7 0.3780 1.40045 0.0002627 317.19 0.083 0.0003

FS171 Bleed15.Fl_O 337.63 8.512 499.41 -12.34 0.0000 571.99 7.477 481.23 2481.9 0.4343 1.40044 0.0002660 337.54 0.090 0.0003

FS172 FanDuct.Fl_O 337.63 8.512 499.41 -12.34 0.0000 571.99 7.477 481.23 2481.9 0.4343 1.40044 0.0002660 337.54 0.090 0.0003

FS173 Byp_Nozz.Fl_O 337.63 8.512 499.41 -12.34 0.0000 571.99 6.740 467.16 2006.9 0.5870 1.40044 0.0002660 337.54 0.090 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 569.40 1.072 0.9054 1848.716 1.0222 0.9063 -1165.9 -1881.95 46.42

LPC 91.29 1.143 0.6893 1848.716 1.0567 0.6952 -476.8 6.97 2.19

HPC 49.25 5.647 0.8099 8804.946 1.7814 0.8491 -4113.5 60.54 56.71

HPT 12.09 3.695 0.8753 212.936 1.3307 0.8549 4113.5 

LPT 48.92 1.923 0.8141 53.078 1.1519 0.7997 1642.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 661.59 1.070 0.9072 1831.089 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 47.04 1.247 0.7558 0.488 0.0000 1.9411 0.5802 0.9120 0.0003

HPC 44.80 5.428 0.8182 8570.212 11.0889 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.621 0.8752 1.280 3.6206 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.694 0.8201 0.597 1.6943 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–73
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2615.99 5930.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.1233 717.97 39.99 13.553

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3571 717.97 39.99 7.047

TEGV 0.0000 0.1785 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.79 35.11 18.358

FanDuct 0.0000 0.4343 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 822.39 65.37 35.232

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.79 35.11 18.358

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 917.93 88.80 51.262

Splitter 6.2370 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.79 35.11 18.358

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8776.1 2461.7 4113.5 WB17Y Bleed> 0.4000 1.0000 1.0000 20.3492 515.28 -8.82 9.078

LP_Shaft 1792.4 4813.5 1642.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4852 917.93 88.80 50.081

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 3.0496 917.93 88.80 29.187

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 917.93 88.80 51.262

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 917.93 88.80 51.262

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 917.93 88.80 51.262

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 498.39 -12.56 8.512

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1698.60 0.9995 0.0230 0.25908 0.01151 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.046 0.9801 1.0000 0.9800 613.40 0.255 379.7 363.3

Byp_Nozz 1.263 0.9800 1.0000 0.9800 2006.86 0.587 609.7 6398.5

NASA/TM—2013-218094 N–74
************************************************************************************************************************************ 

Date:07/05/13 Time:09:28:48 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 23/ 51/ 2/20 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 500.26 Stator 1 exit: 502.62 Stator 2 inlet: 504.93 Stator 2 exit: 505.65 

 Stator 3 inlet: 508.35 Stator 3 exit: 508.75 Stator 4 inlet: 511.35 Stator 4 exit: 511.52 

 Stator 5 inlet: 513.11 Stator 5 exit: 513.12 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.53 

Fan Bypass Relative Humidity 5.96 

LPC Inlet Relative Humidity 5.71 

LPC Exit Relative Humidity 3.40 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 479.99 Fan/LPC Inlet Flow Velocity 173.49 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.17 

Ambient Static Temperature 481.63 Fan/LPC Inlet Static Temperature 498.31 

Additional Water at LPC Exit 0.0000738 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 18.00 386.68 641.2 1.3788 884.08 6.7788 479.99 5.288 0.902 10.000 1649.9 1554.0 1125.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 386.68 9.342 500.81 -13.05 0.0000 597.73 8.149 481.63 2540.9 0.4460 1.40040 0.0004484 386.51 0.173 0.0004

FS1 Inlet.Fl_O 386.68 9.342 500.81 -13.05 0.0000 597.73 8.941 494.57 4168.2 0.2511 1.40040 0.0004484 386.51 0.173 0.0004

FS12 Splitter.Fl_02 336.97 9.337 500.81 -13.05 0.0000 521.15 8.912 494.17 3531.8 0.2590 1.40040 0.0004484 336.82 0.151 0.0004

FS2 Splitter.Fl_01 49.71 9.337 500.81 -13.05 0.0000 76.88 9.175 498.31 830.5 0.1585 1.40040 0.0004484 49.69 0.022 0.0004

FS14 Fan.Fl_O 336.97 9.813 508.79 -11.14 0.0000 499.82 9.027 496.79 2606.7 0.3474 1.40030 0.0004484 336.82 0.151 0.0004

FS23 LPC.Fl_O 49.71 10.431 523.17 -7.69 0.0000 70.34 9.784 513.69 412.6 0.3037 1.40011 0.0004484 49.69 0.022 0.0004

FS24 VaporIN.Fl_O 49.71 10.431 523.30 -8.08 0.0000 70.35 9.784 513.82 412.6 0.3038 1.40010 0.0005221 49.69 0.026 0.0005

FS25 Bleed2.Fl_O 29.83 10.431 523.30 -8.08 0.0000 42.21 10.209 520.09 412.6 0.1758 1.40010 0.0005221 29.81 0.016 0.0005

FS3 HPC.Fl_O 28.38 49.399 887.67 80.18 0.0000 11.05 43.866 858.67 49.7 0.4171 1.38722 0.0005221 28.37 0.015 0.0005

FS36 Bleed3.Fl_O 22.00 49.399 887.67 80.18 0.0000 8.56 46.207 871.25 49.3 0.3117 1.38722 0.0005221 21.98 0.011 0.0005

FS4 Burner.Fl_O 22.24 48.261 1649.87 67.68 0.0112 12.08 45.574 1626.30 74.6 0.2940 1.33459 0.0005221 21.98 0.011 0.0141

FS45 HPT.Fl_O 29.72 14.273 1130.09 -17.22 0.0083 45.18 13.390 1110.87 265.4 0.3069 1.36661 0.0005221 29.46 0.015 0.0107

FS49 LPT.Fl_O 30.07 8.396 1006.05 -46.91 0.0082 73.31 8.272 1002.00 860.2 0.1469 1.37466 0.0005221 29.81 0.016 0.0106

FS5 TEGV.Fl_O 30.07 8.396 1006.13 -46.91 0.0082 73.32 8.272 1002.07 860.2 0.1469 1.37465 0.0005221 29.81 0.016 0.0106

FS8 Core_Nozz.Fl_O 30.07 8.396 1006.20 -46.91 0.0082 73.32 8.149 998.04 613.5 0.2087 1.37465 0.0005221 29.81 0.016 0.0106

FS17 FanDuctLkg.Fl_O 336.97 9.813 508.79 -11.14 0.0000 499.82 9.027 496.79 2606.7 0.3474 1.40030 0.0004484 336.82 0.151 0.0004

FS171 Bleed15.Fl_O 356.86 9.813 509.60 -10.97 0.0000 529.73 8.814 494.19 2481.9 0.3947 1.40029 0.0004525 356.70 0.161 0.0005

FS172 FanDuct.Fl_O 356.86 9.813 509.60 -10.97 0.0000 529.73 8.814 494.19 2481.9 0.3947 1.40029 0.0004525 356.70 0.161 0.0005

FS173 Byp_Nozz.Fl_O 356.86 9.813 509.60 -10.97 0.0000 529.73 8.149 483.23 2006.9 0.5220 1.40029 0.0004525 356.70 0.161 0.0005

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 521.15 1.051 0.8982 1610.128 1.0159 0.8989 -912.4 -1526.11 44.72

LPC 76.88 1.117 0.7204 1610.128 1.0447 0.7248 -377.3 8.26 1.96

HPC 42.21 4.736 0.7955 8540.487 1.6963 0.8340 -3634.6 68.26 63.03

HPT 12.08 3.381 0.8666 211.198 1.3031 0.8466 3634.5 

LPT 45.18 1.700 0.8004 47.065 1.1197 0.7881 1289.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 605.53 1.050 0.9000 1594.776 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 39.70 1.184 0.7480 0.425 0.0000 1.9366 0.6356 0.9631 0.0003

HPC 38.39 4.560 0.8038 8312.803 10.7600 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.315 0.8666 1.269 3.3153 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.527 0.8063 0.529 1.5265 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–75
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2540.86 5768.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0977 706.56 36.05 14.273

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3490 706.56 36.05 8.396

TEGV 0.0000 0.1469 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.31 31.64 19.004

FanDuct 0.0000 0.3947 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 801.09 59.00 34.591

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.31 31.64 19.004

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 887.67 80.18 49.399

Splitter 6.7788 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.31 31.64 19.004

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8578.6 2225.2 3634.5 WB17Y Bleed> 0.4000 1.0000 1.0000 19.8855 523.30 -8.08 10.431

LP_Shaft 1582.2 4281.4 1289.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4058 887.67 80.18 48.261

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9801 887.67 80.18 28.820

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 887.67 80.18 49.399

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 887.67 80.18 49.399

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 887.67 80.18 49.399

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1649.80 0.9995 0.0230 0.24558 0.01117 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.030 0.9802 1.0000 0.9800 613.40 0.209 314.0 293.5

Byp_Nozz 1.204 0.9800 1.0000 0.9800 2006.86 0.522 551.5 6116.5

NASA/TM—2013-218094 N–76
50μm, ISA +36R 

************************************************************************************************************************************ 

Date:07/05/13 Time:09:37:23 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 483.67 Stator 1 exit: 491.43 Stator 2 inlet: 501.20 Stator 2 exit: 506.18 

 Stator 3 inlet: 516.28 Stator 3 exit: 520.81 Stator 4 inlet: 530.25 Stator 4 exit: 534.12 

 Stator 5 inlet: 541.87 Stator 5 exit: 545.25 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.97 

Fan Bypass Relative Humidity 1.41 

LPC Inlet Relative Humidity 1.30 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 192.96 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 474.82 

Additional Water at LPC Exit 0.0000859 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 252.16 617.7 1.1451 707.33 8.5627 789.49 9.518 0.736 10.000 1759.5 1664.7 1158.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.16 4.267 477.92 -16.44 0.0000 833.71 2.854 425.97 2543.5 0.7800 1.40068 0.0000851 252.14 0.021 0.0001

FS1 Inlet.Fl_O 252.16 4.267 477.92 -16.44 0.0000 833.71 3.892 465.50 4168.2 0.3649 1.40068 0.0000851 252.14 0.021 0.0001

FS12 Splitter.Fl_02 225.79 4.265 477.92 -16.44 0.0000 746.90 3.839 463.77 3531.8 0.3902 1.40068 0.0000851 225.77 0.019 0.0001

FS2 Splitter.Fl_01 26.37 4.265 477.92 -16.44 0.0000 87.23 4.169 474.82 830.5 0.1806 1.40068 0.0000851 26.37 0.002 0.0001

FS14 Fan.Fl_O 225.79 4.817 496.63 -11.96 0.0000 674.07 4.042 472.33 2606.7 0.5067 1.40049 0.0000851 225.77 0.019 0.0001

FS23 LPC.Fl_O 26.37 6.654 555.04 2.06 0.0000 60.24 6.358 547.86 412.6 0.2561 1.39968 0.0000851 26.37 0.002 0.0001

FS24 VaporIN.Fl_O 26.37 6.654 555.19 1.60 0.0000 60.26 6.358 548.00 412.6 0.2561 1.39966 0.0001710 26.37 0.005 0.0002

FS25 Bleed2.Fl_O 23.73 6.654 555.19 1.60 0.0000 54.23 6.416 549.44 412.6 0.2287 1.39966 0.0001710 23.73 0.004 0.0002

FS3 HPC.Fl_O 22.58 40.611 1006.37 111.52 0.0000 11.38 35.727 971.40 49.7 0.4343 1.38031 0.0001710 22.58 0.004 0.0002

FS36 Bleed3.Fl_O 17.50 40.611 1006.37 111.52 0.0000 8.82 37.809 986.71 49.3 0.3233 1.38031 0.0001710 17.50 0.003 0.0002

FS4 Burner.Fl_O 17.70 39.676 1759.47 98.62 0.0112 12.07 37.468 1734.63 74.6 0.2944 1.32945 0.0001710 17.50 0.003 0.0139

FS45 HPT.Fl_O 23.65 9.522 1162.57 -7.79 0.0084 54.65 8.626 1132.22 265.4 0.3829 1.36454 0.0001710 23.45 0.004 0.0104

FS49 LPT.Fl_O 23.93 3.261 910.27 -69.74 0.0083 142.85 3.070 895.22 860.2 0.2970 1.38052 0.0001710 23.73 0.004 0.0103

FS5 TEGV.Fl_O 23.93 3.261 910.34 -69.74 0.0083 142.86 3.070 895.30 860.2 0.2971 1.38052 0.0001710 23.73 0.004 0.0103

FS8 Core_Nozz.Fl_O 23.93 3.261 910.42 -69.74 0.0083 142.86 2.854 877.48 613.4 0.4435 1.38051 0.0001710 23.73 0.004 0.0103

FS17 FanDuctLkg.Fl_O 225.79 4.817 496.63 -11.96 0.0000 674.07 4.042 472.33 2606.7 0.5067 1.40049 0.0000851 225.77 0.019 0.0001

FS171 Bleed15.Fl_O 228.43 4.817 497.31 -11.80 0.0000 682.41 3.908 468.45 2481.9 0.5546 1.40048 0.0000861 228.41 0.020 0.0001

FS172 FanDuct.Fl_O 228.43 4.817 497.31 -11.80 0.0000 682.41 3.908 468.45 2481.9 0.5546 1.40048 0.0000861 228.41 0.020 0.0001

FS173 Byp_Nozz.Fl_O 228.43 4.817 497.31 -11.80 0.0000 682.41 2.854 428.14 2006.9 0.8978 1.40048 0.0000861 228.41 0.020 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.90 1.130 0.9055 2568.150 1.0391 0.9071 -1432.7 1610.34 54.83

LPC 87.23 1.560 0.8405 2568.150 1.1614 0.8502 -690.1 6.97 3.73

HPC 54.23 6.103 0.8187 8965.332 1.8127 0.8573 -3601.9 61.35 58.03

HPT 12.07 4.167 0.8772 221.131 1.3648 0.8551 3601.9 

LPT 54.65 2.920 0.8556 72.301 1.2754 0.8360 2122.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 867.82 1.127 0.9073 2543.663 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 73.90 1.522 0.7799 0.678 0.0000 1.1803 1.0736 1.0777 0.0003

HPC 49.32 5.862 0.8271 8726.322 10.9744 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.079 0.8772 1.329 4.0790 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.444 0.8620 0.813 2.4438 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–77
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2543.48 6187.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8734 782.83 56.56 9.522

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2777 782.83 56.56 3.261

TEGV 0.0000 0.2970 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.21 51.06 14.125

FanDuct 0.0000 0.5546 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 899.72 85.14 27.707

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.21 51.06 14.125

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1006.37 111.52 40.611

Splitter 8.5627 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.21 51.06 14.125

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9275.6 2039.5 3601.9 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6372 555.19 1.60 6.654

LP_Shaft 2465.2 4522.8 2122.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7100 1006.37 111.52 39.676

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3713 1006.37 111.52 22.428

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1006.37 111.52 40.611

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1006.37 111.52 40.611

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1006.37 111.52 40.611

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1759.41 0.9995 0.0230 0.19648 0.01123 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.443 627.2 466.5

Byp_Nozz 1.688 0.9800 1.0000 0.9800 2006.86 0.898 892.8 6338.7

NASA/TM—2013-218094 N–78
************************************************************************************************************************************ 

Date:07/05/13 Time:09:37:38 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.90 Stator 1 exit: 484.18 Stator 2 inlet: 493.31 Stator 2 exit: 497.97 

 Stator 3 inlet: 507.40 Stator 3 exit: 511.62 Stator 4 inlet: 520.44 Stator 4 exit: 524.02 

 Stator 5 inlet: 531.26 Stator 5 exit: 534.37 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.46 

Fan Bypass Relative Humidity 1.80 

LPC Inlet Relative Humidity 1.64 

LPC Exit Relative Humidity 0.18 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 738.88 Fan/LPC Inlet Flow Velocity 186.02 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 468.59 

Additional Water at LPC Exit 0.0000765 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 36.00 245.32 607.1 1.1099 673.82 8.6594 738.88 9.232 0.764 10.000 1731.9 1637.7 1141.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 245.32 4.201 471.48 -17.97 0.0000 818.13 2.947 425.97 2560.6 0.7300 1.40073 0.0000824 245.29 0.020 0.0001

FS1 Inlet.Fl_O 245.32 4.201 471.48 -17.97 0.0000 818.13 3.847 459.74 4168.2 0.3569 1.40073 0.0000824 245.29 0.020 0.0001

FS12 Splitter.Fl_02 219.92 4.199 471.48 -17.97 0.0000 733.80 3.797 458.09 3531.8 0.3819 1.40073 0.0000824 219.90 0.018 0.0001

FS2 Splitter.Fl_01 25.40 4.199 471.48 -17.97 0.0000 84.74 4.110 468.59 830.5 0.1752 1.40073 0.0000824 25.39 0.002 0.0001

FS14 Fan.Fl_O 219.92 4.711 488.91 -13.79 0.0000 666.03 3.976 465.75 2606.7 0.4982 1.40058 0.0000824 219.90 0.018 0.0001

FS23 LPC.Fl_O 25.40 6.415 543.68 -0.65 0.0000 59.57 6.136 536.81 412.6 0.2529 1.39986 0.0000824 25.39 0.002 0.0001

FS24 VaporIN.Fl_O 25.40 6.415 543.81 -1.06 0.0000 59.58 6.135 536.94 412.6 0.2530 1.39984 0.0001589 25.39 0.004 0.0002

FS25 Bleed2.Fl_O 22.86 6.415 543.81 -1.06 0.0000 53.62 6.191 538.32 412.6 0.2260 1.39984 0.0001589 22.86 0.004 0.0002

FS3 HPC.Fl_O 21.75 38.786 984.01 106.03 0.0000 11.35 34.154 949.97 49.7 0.4325 1.38169 0.0001589 21.75 0.003 0.0002

FS36 Bleed3.Fl_O 16.86 38.786 984.01 106.03 0.0000 8.80 36.127 964.87 49.3 0.3221 1.38169 0.0001589 16.85 0.003 0.0002

FS4 Burner.Fl_O 17.04 37.893 1731.93 93.33 0.0111 12.08 35.783 1707.39 74.6 0.2944 1.33079 0.0001589 16.85 0.003 0.0137

FS45 HPT.Fl_O 22.78 9.210 1145.77 -10.32 0.0083 54.02 8.366 1116.60 265.4 0.3775 1.36569 0.0001589 22.59 0.004 0.0103

FS49 LPT.Fl_O 23.05 3.311 907.95 -68.55 0.0082 135.33 3.138 894.61 860.2 0.2797 1.38072 0.0001589 22.86 0.004 0.0102

FS5 TEGV.Fl_O 23.05 3.311 908.02 -68.55 0.0082 135.33 3.138 894.68 860.2 0.2797 1.38071 0.0001589 22.86 0.004 0.0102

FS8 Core_Nozz.Fl_O 23.05 3.311 908.09 -68.55 0.0082 135.34 2.947 879.32 613.4 0.4141 1.38071 0.0001589 22.86 0.004 0.0102

FS17 FanDuctLkg.Fl_O 219.92 4.711 488.91 -13.79 0.0000 666.03 3.976 465.75 2606.7 0.4982 1.40058 0.0000824 219.90 0.018 0.0001

FS171 Bleed15.Fl_O 222.46 4.711 489.54 -13.65 0.0000 674.16 3.851 462.10 2481.9 0.5444 1.40057 0.0000833 222.44 0.019 0.0001

FS172 FanDuct.Fl_O 222.46 4.711 489.54 -13.65 0.0000 674.16 3.851 462.10 2481.9 0.5444 1.40057 0.0000833 222.44 0.019 0.0001

FS173 Byp_Nozz.Fl_O 222.46 4.711 489.54 -13.65 0.0000 674.16 2.947 428.03 2006.9 0.8467 1.40057 0.0000833 222.44 0.019 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 733.80 1.122 0.9047 2504.280 1.0370 0.9062 -1300.4 2190.73 54.69

LPC 84.74 1.528 0.8409 2504.280 1.1531 0.8501 -622.2 6.78 3.35

HPC 53.62 6.046 0.8178 8945.742 1.8095 0.8565 -3379.7 61.28 57.90 

HPT 12.08 4.114 0.8759 220.105 1.3615 0.8539 3379.7 

LPT 54.02 2.781 0.8500 70.537 1.2600 0.8307 1922.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 852.60 1.119 0.9065 2480.402 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 71.14 1.493 0.7769 0.661 0.0000 1.1912 1.0692 1.0824 0.0003

HPC 48.77 5.809 0.8263 8707.255 10.9862 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.028 0.8759 1.323 4.0281 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.340 0.8563 0.793 2.3398 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–79
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2560.61 5633.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8412 765.78 52.49 9.210

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2674 765.78 52.49 3.311

TEGV 0.0000 0.2797 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.72 47.13 13.536

FanDuct 0.0000 0.5444 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 879.85 80.33 26.485

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.72 47.13 13.536

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 984.01 106.03 38.786

Splitter 8.6594 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.72 47.13 13.536

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9160.0 1937.9 3379.7 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5399 543.81 -1.06 6.415

LP_Shaft 2387.6 4229.1 1922.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6100 984.01 106.03 37.893

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2838 984.01 106.03 21.486

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 984.01 106.03 38.786

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 984.01 106.03 38.786

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 984.01 106.03 38.786

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1731.87 0.9995 0.0230 0.18717 0.01111 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.414 586.2 419.9

Byp_Nozz 1.599 0.9800 1.0000 0.9800 2006.86 0.847 841.9 5820.9

NASA/TM—2013-218094 N–80
************************************************************************************************************************************ 

Date:07/05/13 Time:09:37:54 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 474.82 Stator 1 exit: 481.90 Stator 2 inlet: 490.80 Stator 2 exit: 495.33 

 Stator 3 inlet: 504.51 Stator 3 exit: 508.61 Stator 4 inlet: 517.19 Stator 4 exit: 520.67 

 Stator 5 inlet: 527.71 Stator 5 exit: 530.72 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.63 

Fan Bypass Relative Humidity 1.95 

LPC Inlet Relative Humidity 1.76 

LPC Exit Relative Humidity 0.19 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 722.68 Fan/LPC Inlet Flow Velocity 183.18 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 466.71 

Additional Water at LPC Exit 0.0000701 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 36.00 251.85 620.3 1.1040 684.84 8.7056 722.68 9.103 0.772 10.000 1721.1 1627.2 1135.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 251.85 4.339 469.50 -18.42 0.0000 811.53 3.088 425.97 2564.5 0.7140 1.40075 0.0000786 251.83 0.020 0.0001

FS1 Inlet.Fl_O 251.85 4.339 469.50 -18.42 0.0000 811.53 3.980 458.03 4168.2 0.3535 1.40075 0.0000786 251.83 0.020 0.0001

FS12 Splitter.Fl_02 225.90 4.337 469.50 -18.42 0.0000 728.28 3.929 456.40 3531.8 0.3784 1.40075 0.0000786 225.89 0.018 0.0001

FS2 Splitter.Fl_01 25.95 4.337 469.50 -18.42 0.0000 83.66 4.247 466.71 830.5 0.1729 1.40075 0.0000786 25.95 0.002 0.0001

FS14 Fan.Fl_O 225.90 4.852 486.45 -14.36 0.0000 662.59 4.105 463.71 2606.7 0.4947 1.40060 0.0000786 225.89 0.018 0.0001

FS23 LPC.Fl_O 25.95 6.568 539.84 -1.55 0.0000 59.24 6.285 533.10 412.6 0.2514 1.39992 0.0000786 25.95 0.002 0.0001

FS24 VaporIN.Fl_O 25.95 6.568 539.97 -1.93 0.0000 59.25 6.285 533.23 412.6 0.2515 1.39991 0.0001487 25.95 0.004 0.0001

FS25 Bleed2.Fl_O 23.36 6.568 539.97 -1.93 0.0000 53.32 6.341 534.58 412.6 0.2246 1.39991 0.0001487 23.35 0.003 0.0001

FS3 HPC.Fl_O 22.22 39.498 975.91 104.09 0.0000 11.34 34.791 942.20 49.7 0.4320 1.38217 0.0001487 22.22 0.003 0.0001

FS36 Bleed3.Fl_O 17.22 39.498 975.91 104.09 0.0000 8.79 36.795 956.95 49.3 0.3217 1.38217 0.0001487 17.22 0.003 0.0001

FS4 Burner.Fl_O 17.41 38.589 1721.05 91.46 0.0110 12.08 36.439 1696.64 74.6 0.2943 1.33134 0.0001487 17.22 0.003 0.0136

FS45 HPT.Fl_O 23.27 9.422 1139.20 -11.12 0.0082 53.79 8.567 1110.45 265.4 0.3755 1.36614 0.0001487 23.08 0.003 0.0102

FS49 LPT.Fl_O 23.55 3.451 906.86 -67.95 0.0081 132.59 3.278 894.11 860.2 0.2735 1.38081 0.0001487 23.35 0.003 0.0101

FS5 TEGV.Fl_O 23.55 3.451 906.93 -67.95 0.0081 132.60 3.278 894.18 860.2 0.2735 1.38081 0.0001487 23.35 0.003 0.0101

FS8 Core_Nozz.Fl_O 23.55 3.451 907.00 -67.95 0.0081 132.60 3.088 879.63 613.4 0.4037 1.38080 0.0001487 23.35 0.003 0.0101

FS17 FanDuctLkg.Fl_O 225.90 4.852 486.45 -14.36 0.0000 662.59 4.105 463.71 2606.7 0.4947 1.40060 0.0000786 225.89 0.018 0.0001

FS171 Bleed15.Fl_O 228.50 4.852 487.06 -14.22 0.0000 670.62 3.978 460.16 2481.9 0.5401 1.40060 0.0000794 228.48 0.018 0.0001

FS172 FanDuct.Fl_O 228.50 4.852 487.06 -14.22 0.0000 670.62 3.978 460.16 2481.9 0.5401 1.40060 0.0000794 228.48 0.018 0.0001

FS173 Byp_Nozz.Fl_O 228.50 4.852 487.06 -14.22 0.0000 670.62 3.088 427.99 2006.9 0.8297 1.40060 0.0000794 228.48 0.018 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 728.28 1.119 0.9043 2477.503 1.0361 0.9058 -1298.0 2584.42 54.62

LPC 83.66 1.514 0.8408 2477.503 1.1498 0.8498 -619.3 6.69 3.27

HPC 53.32 6.014 0.8173 8935.972 1.8073 0.8561 -3418.2 61.37 57.96

HPT 12.08 4.095 0.8753 219.778 1.3603 0.8533 3418.2 

LPT 53.79 2.730 0.8478 69.837 1.2542 0.8287 1917.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 846.19 1.116 0.9061 2453.880 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 69.98 1.481 0.7756 0.654 0.0000 1.1954 1.0682 1.0840 0.0003

HPC 48.50 5.778 0.8258 8697.745 10.9845 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.010 0.8753 1.321 4.0096 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.302 0.8541 0.786 2.3015 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–81
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2564.46 5657.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8595 759.75 51.08 9.422

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2733 759.75 51.08 3.451

TEGV 0.0000 0.2735 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 737.90 45.78 13.812

FanDuct 0.0000 0.5401 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 872.73 78.64 26.985

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 737.90 45.78 13.812

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 975.91 104.09 39.498

Splitter 8.7056 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 737.90 45.78 13.812

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9117.6 1969.0 3418.2 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5951 539.97 -1.93 6.568

LP_Shaft 2357.2 4272.0 1917.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6668 975.91 104.09 38.589

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3335 975.91 104.09 21.906

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 975.91 104.09 39.498

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 975.91 104.09 39.498

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 975.91 104.09 39.498

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.45 -14.36 4.852

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.45 -14.36 4.852

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.45 -14.36 4.852

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.45 -14.36 4.852

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1721.00 0.9995 0.0230 0.19023 0.01105 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.404 571.6 418.3

Byp_Nozz 1.571 0.9800 1.0000 0.9800 2006.86 0.830 825.0 5859.0

NASA/TM—2013-218094 N–82
************************************************************************************************************************************ 

Date:07/05/13 Time:09:38:09 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.22 Stator 1 exit: 482.86 Stator 2 inlet: 491.16 Stator 2 exit: 495.38 

 Stator 3 inlet: 503.94 Stator 3 exit: 507.74 Stator 4 inlet: 515.75 Stator 4 exit: 518.95 

 Stator 5 inlet: 525.50 Stator 5 exit: 528.27 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.24 

Fan Bypass Relative Humidity 2.48 

LPC Inlet Relative Humidity 2.22 

LPC Exit Relative Humidity 0.28 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 682.24 Fan/LPC Inlet Flow Velocity 176.63 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 432.42 Fan/LPC Inlet Static Temperature 468.61 

Additional Water at LPC Exit 0.0000690 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 36.00 272.66 667.0 1.0952 730.45 8.8130 682.24 8.726 0.795 10.000 1710.4 1616.8 1130.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 272.66 4.831 471.21 -18.12 0.0000 790.57 3.578 432.42 2577.0 0.6690 1.40074 0.0000968 272.63 0.026 0.0001

FS1 Inlet.Fl_O 272.66 4.831 471.21 -18.12 0.0000 790.57 4.453 460.37 4168.2 0.3429 1.40074 0.0000968 272.63 0.026 0.0001

FS12 Splitter.Fl_02 244.87 4.829 471.21 -18.12 0.0000 710.36 4.399 458.81 3531.8 0.3674 1.40074 0.0000968 244.85 0.024 0.0001

FS2 Splitter.Fl_01 27.78 4.829 471.21 -18.12 0.0000 80.60 4.736 468.61 830.5 0.1664 1.40074 0.0000968 27.78 0.003 0.0001

FS14 Fan.Fl_O 244.87 5.360 487.02 -14.33 0.0000 650.62 4.570 465.32 2606.7 0.4824 1.40059 0.0000968 244.85 0.024 0.0001

FS23 LPC.Fl_O 27.78 7.120 536.98 -2.35 0.0000 58.35 6.823 530.49 412.6 0.2474 1.39996 0.0000968 27.78 0.003 0.0001

FS24 VaporIN.Fl_O 27.79 7.120 537.10 -2.71 0.0000 58.36 6.823 530.61 412.6 0.2474 1.39995 0.0001658 27.78 0.005 0.0002

FS25 Bleed2.Fl_O 25.01 7.120 537.10 -2.71 0.0000 52.53 6.882 531.91 412.6 0.2210 1.39995 0.0001658 25.00 0.004 0.0002

FS3 HPC.Fl_O 23.80 42.157 966.99 101.78 0.0000 11.33 37.149 933.67 49.7 0.4312 1.38270 0.0001658 23.79 0.004 0.0002

FS36 Bleed3.Fl_O 18.44 42.157 966.99 101.78 0.0000 8.78 39.280 948.24 49.3 0.3212 1.38270 0.0001658 18.44 0.003 0.0002

FS4 Burner.Fl_O 18.64 41.186 1710.41 89.23 0.0110 12.08 38.892 1686.13 74.6 0.2943 1.33186 0.0001658 18.44 0.003 0.0136

FS45 HPT.Fl_O 24.92 10.173 1134.37 -11.86 0.0082 53.24 9.270 1106.40 265.4 0.3708 1.36647 0.0001658 24.71 0.004 0.0102

FS49 LPT.Fl_O 25.21 3.939 915.40 -65.33 0.0081 124.94 3.766 904.09 860.2 0.2564 1.38033 0.0001658 25.00 0.004 0.0101

FS5 TEGV.Fl_O 25.21 3.939 915.48 -65.33 0.0081 124.95 3.766 904.16 860.2 0.2564 1.38032 0.0001658 25.00 0.004 0.0101

FS8 Core_Nozz.Fl_O 25.21 3.939 915.55 -65.33 0.0081 124.95 3.578 891.56 613.4 0.3757 1.38032 0.0001658 25.00 0.004 0.0101

FS17 FanDuctLkg.Fl_O 244.87 5.360 487.02 -14.33 0.0000 650.62 4.570 465.32 2606.7 0.4824 1.40059 0.0000968 244.85 0.024 0.0001

FS171 Bleed15.Fl_O 247.65 5.360 487.58 -14.20 0.0000 658.38 4.440 462.01 2481.9 0.5256 1.40059 0.0000976 247.62 0.024 0.0001

FS172 FanDuct.Fl_O 247.65 5.360 487.58 -14.20 0.0000 658.38 4.440 462.01 2481.9 0.5256 1.40059 0.0000976 247.62 0.024 0.0001

FS173 Byp_Nozz.Fl_O 247.65 5.360 487.58 -14.20 0.0000 658.38 3.578 434.35 2006.9 0.7820 1.40059 0.0000976 247.62 0.024 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.36 1.110 0.9031 2395.161 1.0335 0.9046 -1312.8 5841.49 54.21

LPC 80.60 1.475 0.8415 2395.161 1.1396 0.8499 -620.0 6.40 3.05

HPC 52.53 5.921 0.8158 8909.698 1.8004 0.8545 -3607.5 61.79 58.29

HPT 12.08 4.049 0.8746 219.228 1.3570 0.8526 3607.5 

LPT 53.24 2.582 0.8427 67.783 1.2370 0.8241 1932.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.37 1.107 0.9050 2372.323 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.41 1.445 0.7718 0.633 0.0000 1.2135 1.0672 1.0903 0.0003

HPC 47.77 5.689 0.8242 8672.172 10.9686 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.964 0.8746 1.318 3.9641 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.190 0.8489 0.762 2.1901 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–83
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2576.97 5781.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9203 753.78 49.53 10.173

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2926 753.78 49.53 3.939

TEGV 0.0000 0.2564 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.23 44.31 14.828

FanDuct 0.0000 0.5256 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.20 76.70 28.843

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.23 44.31 14.828

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 966.99 101.78 42.157

Splitter 8.8130 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.23 44.31 14.828

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9066.7 2089.7 3607.5 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7787 537.10 -2.71 7.120

LP_Shaft 2283.0 4446.5 1932.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8554 966.99 101.78 41.186

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4986 966.99 101.78 23.446

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.99 101.78 42.157

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.99 101.78 42.157

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.99 101.78 42.157

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1710.35 0.9995 0.0230 0.20290 0.01100 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.101 0.9801 1.0000 0.9800 613.40 0.376 535.4 419.6

Byp_Nozz 1.498 0.9800 1.0000 0.9800 2006.86 0.782 783.3 6028.9

NASA/TM—2013-218094 N–84
************************************************************************************************************************************ 

Date:07/05/13 Time:09:38:26 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 14/ 28/ 1/12 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.51 Stator 1 exit: 490.20 Stator 2 inlet: 497.24 Stator 2 exit: 500.64 

 Stator 3 inlet: 507.99 Stator 3 exit: 510.98 Stator 4 inlet: 517.90 Stator 4 exit: 520.36 

 Stator 5 inlet: 525.93 Stator 5 exit: 528.02 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.18 

Fan Bypass Relative Humidity 3.37 

LPC Inlet Relative Humidity 3.05 

LPC Exit Relative Humidity 0.57 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 630.80 Fan/LPC Inlet Flow Velocity 177.35 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 447.58 Fan/LPC Inlet Static Temperature 478.12 

Additional Water at LPC Exit 0.0000791 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 36.00 298.11 710.0 1.1111 788.84 8.4114 630.80 8.108 0.827 10.000 1708.3 1614.4 1131.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 298.11 5.595 480.74 -16.28 0.0000 753.84 4.358 447.58 2589.6 0.6080 1.40064 0.0001750 298.06 0.052 0.0002

FS1 Inlet.Fl_O 298.11 5.595 480.74 -16.28 0.0000 753.84 5.201 470.80 4168.2 0.3247 1.40064 0.0001750 298.06 0.052 0.0002

FS12 Splitter.Fl_02 266.44 5.592 480.74 -16.28 0.0000 674.08 5.149 469.51 3531.8 0.3454 1.40064 0.0001750 266.39 0.047 0.0002

FS2 Splitter.Fl_01 31.68 5.592 480.74 -16.28 0.0000 80.14 5.486 478.12 830.5 0.1654 1.40064 0.0001750 31.67 0.006 0.0002

FS14 Fan.Fl_O 266.44 6.130 494.94 -12.88 0.0000 623.92 5.315 475.14 2606.7 0.4561 1.40050 0.0001750 266.39 0.047 0.0002

FS23 LPC.Fl_O 31.68 7.803 536.93 -2.81 0.0000 60.70 7.450 529.86 412.6 0.2581 1.39995 0.0001750 31.67 0.006 0.0002

FS24 VaporIN.Fl_O 31.68 7.803 537.07 -3.23 0.0000 60.71 7.450 530.00 412.6 0.2582 1.39994 0.0002541 31.67 0.008 0.0003

FS25 Bleed2.Fl_O 26.93 7.803 537.07 -3.23 0.0000 51.60 7.551 532.06 412.6 0.2169 1.39994 0.0002541 26.92 0.007 0.0003

FS3 HPC.Fl_O 25.62 45.365 962.40 100.14 0.0000 11.31 39.999 929.37 49.7 0.4301 1.38296 0.0002541 25.61 0.007 0.0003

FS36 Bleed3.Fl_O 19.86 45.365 962.40 100.14 0.0000 8.76 42.282 943.80 49.3 0.3205 1.38296 0.0002541 19.85 0.005 0.0003

FS4 Burner.Fl_O 20.08 44.320 1708.34 87.57 0.0110 12.08 41.851 1684.08 74.6 0.2943 1.33192 0.0002541 19.85 0.005 0.0137

FS45 HPT.Fl_O 26.83 11.108 1136.01 -12.40 0.0082 52.53 10.152 1108.86 265.4 0.3650 1.36634 0.0002541 26.60 0.007 0.0103

FS49 LPT.Fl_O 27.15 4.710 937.33 -60.83 0.0081 113.86 4.539 927.84 860.2 0.2322 1.37899 0.0002541 26.92 0.007 0.0102

FS5 TEGV.Fl_O 27.15 4.710 937.40 -60.83 0.0081 113.86 4.539 927.91 860.2 0.2322 1.37899 0.0002541 26.92 0.007 0.0102

FS8 Core_Nozz.Fl_O 27.15 4.710 937.48 -60.83 0.0081 113.87 4.358 917.67 613.4 0.3372 1.37898 0.0002541 26.92 0.007 0.0102

FS17 FanDuctLkg.Fl_O 266.44 6.130 494.94 -12.88 0.0000 623.92 5.315 475.14 2606.7 0.4561 1.40050 0.0001750 266.39 0.047 0.0002

FS171 Bleed15.Fl_O 271.19 6.130 495.68 -12.71 0.0000 635.52 5.168 472.06 2481.9 0.4998 1.40049 0.0001764 271.14 0.048 0.0002

FS172 FanDuct.Fl_O 271.19 6.130 495.68 -12.71 0.0000 635.52 5.168 472.06 2481.9 0.4998 1.40049 0.0001764 271.14 0.048 0.0002

FS173 Byp_Nozz.Fl_O 271.19 6.130 495.68 -12.71 0.0000 635.52 4.358 449.59 2006.9 0.7153 1.40049 0.0001764 271.14 0.048 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 674.08 1.096 0.9014 2239.031 1.0295 0.9027 -1283.3 -8377.61 52.80

LPC 80.14 1.395 0.8549 2239.031 1.1169 0.8616 -604.0 5.98 2.60

HPC 51.60 5.814 0.8138 8879.365 1.7920 0.8527 -3842.6 62.28 58.66

HPT 12.08 3.990 0.8743 218.606 1.3525 0.8525 3842.6 

LPT 52.53 2.358 0.8337 63.955 1.2095 0.8162 1887.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 783.22 1.094 0.9032 2217.682 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 59.98 1.378 0.7652 0.591 0.0000 1.3363 1.0451 1.1172 0.0003

HPC 46.93 5.587 0.8222 8642.647 10.9508 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.907 0.8743 1.314 3.9070 12.6299 0.9723 1.0000 0.0003

LPT 0.80 2.022 0.8399 0.719 2.0217 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–85
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2589.57 5844.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9909 751.42 48.45 11.108

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3150 751.42 48.45 4.710

TEGV 0.0000 0.2322 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.10 43.29 16.067

FanDuct 0.0000 0.4998 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 861.67 75.33 31.091

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.10 43.29 16.067

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 962.40 100.14 45.365

Splitter 8.4114 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 730.10 43.29 16.067

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9035.5 2233.6 3842.6 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7517 537.07 -3.23 7.803

LP_Shaft 2155.6 4598.2 1887.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.0745 962.40 100.14 44.320

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.6902 962.40 100.14 25.323

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.40 100.14 45.365

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.40 100.14 45.365

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.40 100.14 45.365

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 494.94 -12.88 6.130

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 494.94 -12.88 6.130

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 494.94 -12.88 6.130

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 494.94 -12.88 6.130

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1708.28 0.9995 0.0230 0.21912 0.01104 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.081 0.9801 1.0000 0.9800 613.40 0.337 487.2 411.1

Byp_Nozz 1.407 0.9800 1.0000 0.9800 2006.86 0.715 728.9 6143.6

NASA/TM—2013-218094 N–86
************************************************************************************************************************************ 

Date:07/05/13 Time:09:38:56 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 50/ 2/19 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 492.28 Stator 1 exit: 496.44 Stator 2 inlet: 501.17 Stator 2 exit: 503.03 

 Stator 3 inlet: 508.28 Stator 3 exit: 509.72 Stator 4 inlet: 514.76 Stator 4 exit: 515.79 

 Stator 5 inlet: 519.47 Stator 5 exit: 520.22 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.02 

Fan Bypass Relative Humidity 4.21 

LPC Inlet Relative Humidity 4.03 

LPC Exit Relative Humidity 1.37 

HPC Relative Humidity 0.00 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 582.56 Fan/LPC Inlet Flow Velocity 195.58 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 463.14 Fan/LPC Inlet Static Temperature 488.23 

Additional Water at LPC Exit 0.0000812 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 36.00 322.28 710.2 1.1729 833.00 7.1195 582.56 7.194 0.857 10.000 1713.1 1617.1 1139.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 322.28 6.516 491.41 -14.47 0.0000 707.48 5.297 463.14 2581.1 0.5520 1.40052 0.0003043 322.18 0.098 0.0003

FS1 Inlet.Fl_O 322.28 6.516 491.41 -14.47 0.0000 707.48 6.116 482.59 4168.2 0.3022 1.40052 0.0003043 322.18 0.098 0.0003

FS12 Splitter.Fl_02 282.59 6.513 491.41 -14.47 0.0000 620.66 6.082 481.88 3531.8 0.3143 1.40052 0.0003043 282.50 0.086 0.0003

FS2 Splitter.Fl_01 39.69 6.513 491.41 -14.47 0.0000 87.18 6.366 488.23 830.5 0.1805 1.40052 0.0003043 39.68 0.012 0.0003

FS14 Fan.Fl_O 282.59 7.039 503.65 -11.54 0.0000 581.39 6.246 486.73 2606.7 0.4167 1.40039 0.0003043 282.50 0.086 0.0003

FS23 LPC.Fl_O 39.69 8.181 531.61 -4.83 0.0000 72.19 7.644 521.41 412.6 0.3127 1.40001 0.0003043 39.68 0.012 0.0003

FS24 VaporIN.Fl_O 39.69 8.181 531.75 -5.27 0.0000 72.20 7.644 521.54 412.6 0.3128 1.40000 0.0003856 39.68 0.015 0.0004

FS25 Bleed2.Fl_O 27.79 8.181 531.75 -5.27 0.0000 50.54 7.928 527.00 412.6 0.2122 1.40000 0.0003856 27.78 0.011 0.0004

FS3 HPC.Fl_O 26.44 46.878 949.69 96.25 0.0000 11.22 41.436 917.69 49.7 0.4257 1.38370 0.0003856 26.43 0.010 0.0004

FS36 Bleed3.Fl_O 20.49 46.878 949.69 96.25 0.0000 8.69 43.746 931.64 49.3 0.3175 1.38370 0.0003856 20.48 0.008 0.0004

FS4 Burner.Fl_O 20.72 45.799 1713.12 83.43 0.0113 12.08 43.246 1688.80 74.6 0.2945 1.33150 0.0003856 20.48 0.008 0.0141

FS45 HPT.Fl_O 27.69 11.866 1144.33 -14.60 0.0084 50.94 10.912 1118.88 265.4 0.3522 1.36565 0.0003856 27.45 0.011 0.0107

FS49 LPT.Fl_O 28.02 5.615 969.24 -57.16 0.0083 100.24 5.459 961.76 860.2 0.2031 1.37691 0.0003856 27.78 0.011 0.0106

FS5 TEGV.Fl_O 28.02 5.615 969.31 -57.16 0.0083 100.24 5.459 961.83 860.2 0.2031 1.37691 0.0003856 27.78 0.011 0.0106

FS8 Core_Nozz.Fl_O 28.02 5.615 969.38 -57.16 0.0083 100.25 5.297 954.01 613.4 0.2922 1.37690 0.0003856 27.78 0.011 0.0106

FS17 FanDuctLkg.Fl_O 282.59 7.039 503.65 -11.54 0.0000 581.39 6.246 486.73 2606.7 0.4167 1.40039 0.0003043 282.50 0.086 0.0003

FS171 Bleed15.Fl_O 294.49 7.039 504.79 -11.28 0.0000 606.58 6.054 483.49 2481.9 0.4690 1.40037 0.0003076 294.40 0.091 0.0003

FS172 FanDuct.Fl_O 294.49 7.039 504.79 -11.28 0.0000 606.58 6.054 483.49 2481.9 0.4690 1.40037 0.0003076 294.40 0.091 0.0003

FS173 Byp_Nozz.Fl_O 294.49 7.039 504.79 -11.28 0.0000 606.58 5.297 465.37 2006.9 0.6503 1.40037 0.0003076 294.40 0.091 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 620.66 1.081 0.9017 2025.533 1.0249 0.9028 -1173.3 -2597.69 50.01

LPC 87.18 1.256 0.8234 2025.533 1.0818 0.8290 -541.4 6.43 2.41

HPC 50.54 5.730 0.8121 8845.497 1.7860 0.8511 -3894.1 61.74 58.02

HPT 12.08 3.860 0.8752 216.389 1.3429 0.8541 3894.1 

LPT 50.94 2.113 0.8233 58.283 1.1777 0.8075 1714.7 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 721.15 1.079 0.9035 2006.219 0.0424 0.8607 1.0235 0.9980 0.9905

LPC 52.83 1.305 0.7603 0.535 0.0000 1.6500 0.8409 1.0830 0.0003

HPC 45.97 5.507 0.8205 8609.682 10.9982 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.780 0.8752 1.300 3.7804 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.837 0.8294 0.656 1.8373 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–87
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2581.06 5835.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0225 742.30 45.49 11.866

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3251 742.30 45.49 5.615

TEGV 0.0000 0.2031 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.36 40.42 16.694

FanDuct 0.0000 0.4690 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 850.66 71.88 32.173

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.36 40.42 16.694

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 949.69 96.25 46.878

Splitter 7.1195 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.36 40.42 16.694

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8956.3 2283.5 3894.1 WB17Y Bleed> 0.3000 1.0000 1.0000 11.9085 531.75 -5.27 8.181

LP_Shaft 1971.6 4567.9 1714.7 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1727 949.69 96.25 45.799

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7761 949.69 96.25 26.389

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.69 96.25 46.878

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.69 96.25 46.878

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.69 96.25 46.878

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1713.06 0.9995 0.0230 0.23139 0.01130 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.060 0.9801 1.0000 0.9800 613.40 0.292 430.2 374.6

Byp_Nozz 1.329 0.9800 1.0000 0.9800 2006.86 0.650 674.2 6170.9

NASA/TM—2013-218094 N–88
************************************************************************************************************************************ 

Date:07/05/13 Time:09:39:25 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 50/ 2/19 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 505.22 Stator 1 exit: 508.18 Stator 2 inlet: 510.96 Stator 2 exit: 511.76 

 Stator 3 inlet: 515.11 Stator 3 exit: 515.48 Stator 4 inlet: 518.75 Stator 4 exit: 518.81 

 Stator 5 inlet: 520.69 Stator 5 exit: 520.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.01 

Fan Bypass Relative Humidity 5.19 

LPC Inlet Relative Humidity 5.20 

LPC Exit Relative Humidity 2.84 

HPC Relative Humidity 0.01 

Drop Diameter 0.0000500 Inlet Length 40.00 

Ambient Flow Velocity 528.20 Fan/LPC Inlet Flow Velocity 203.15 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 483.18 Fan/LPC Inlet Static Temperature 502.97 

Additional Water at LPC Exit 0.0000933 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 36.00 357.70 762.5 1.1969 912.63 6.3414 528.20 6.254 0.888 10.000 1736.7 1637.2 1166.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 357.70 7.943 506.41 -12.46 0.0000 653.92 6.740 483.18 2590.9 0.4900 1.40031 0.0005787 357.49 0.207 0.0006

FS1 Inlet.Fl_O 357.70 7.943 506.41 -12.46 0.0000 653.92 7.531 498.75 4168.2 0.2770 1.40031 0.0005787 357.49 0.207 0.0006

FS12 Splitter.Fl_02 308.97 7.939 506.41 -12.46 0.0000 565.13 7.509 498.41 3531.8 0.2831 1.40031 0.0005787 308.79 0.179 0.0006

FS2 Splitter.Fl_01 48.72 7.939 506.41 -12.46 0.0000 89.12 7.752 502.97 830.5 0.1847 1.40031 0.0005787 48.70 0.028 0.0006

FS14 Fan.Fl_O 308.97 8.480 517.06 -9.90 0.0000 534.65 7.690 502.82 2606.7 0.3761 1.40018 0.0005787 308.79 0.179 0.0006

FS23 LPC.Fl_O 48.72 9.054 534.27 -5.77 0.0000 80.27 8.305 521.26 412.6 0.3533 1.39993 0.0005787 48.70 0.028 0.0006

FS24 VaporIN.Fl_O 48.73 9.054 534.43 -6.27 0.0000 80.29 8.305 521.40 412.6 0.3534 1.39992 0.0006720 48.70 0.033 0.0007

FS25 Bleed2.Fl_O 29.24 9.054 534.43 -6.27 0.0000 48.17 8.800 530.11 412.6 0.2018 1.39992 0.0006720 29.22 0.020 0.0007

FS3 HPC.Fl_O 27.82 49.678 943.60 93.12 0.0000 11.10 44.047 912.57 49.7 0.4202 1.38401 0.0006720 27.80 0.019 0.0007

FS36 Bleed3.Fl_O 21.56 49.678 943.60 93.12 0.0000 8.60 46.433 926.06 49.3 0.3138 1.38401 0.0006720 21.55 0.014 0.0007

FS4 Burner.Fl_O 21.81 48.534 1736.73 79.81 0.0118 12.09 45.827 1712.12 74.6 0.2947 1.33004 0.0006720 21.55 0.014 0.0150

FS45 HPT.Fl_O 29.15 13.282 1170.70 -15.95 0.0088 48.45 12.324 1147.54 265.4 0.3327 1.36368 0.0006720 28.88 0.019 0.0114

FS49 LPT.Fl_O 29.49 7.031 1017.56 -53.08 0.0087 86.34 6.886 1011.84 860.2 0.1740 1.37361 0.0006720 29.22 0.020 0.0113

FS5 TEGV.Fl_O 29.49 7.031 1017.63 -53.08 0.0087 86.34 6.886 1011.91 860.2 0.1740 1.37361 0.0006720 29.22 0.020 0.0113

FS8 Core_Nozz.Fl_O 29.49 7.031 1017.70 -53.08 0.0087 86.35 6.740 1006.09 613.5 0.2485 1.37360 0.0006720 29.22 0.020 0.0113

FS17 FanDuctLkg.Fl_O 308.97 8.480 517.06 -9.90 0.0000 534.65 7.690 502.82 2606.7 0.3761 1.40018 0.0005787 308.79 0.179 0.0006

FS171 Bleed15.Fl_O 328.46 8.480 518.09 -9.69 0.0000 568.94 7.461 499.48 2481.9 0.4314 1.40016 0.0005842 328.27 0.192 0.0006

FS172 FanDuct.Fl_O 328.46 8.480 518.09 -9.69 0.0000 568.94 7.461 499.48 2481.9 0.4314 1.40016 0.0005842 328.27 0.192 0.0006

FS173 Byp_Nozz.Fl_O 328.46 8.480 518.09 -9.69 0.0000 568.94 6.740 485.18 2006.9 0.5821 1.40016 0.0005842 328.27 0.192 0.0006

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 565.13 1.068 0.9035 1815.414 1.0210 0.9044 -1117.3 -1833.24 46.56

LPC 89.12 1.140 0.6954 1815.414 1.0550 0.7011 -460.9 7.12 2.04

HPC 48.17 5.487 0.8076 8765.136 1.7656 0.8467 -4011.6 62.14 58.12

HPT 12.09 3.654 0.8765 213.497 1.3265 0.8566 4011.6 

LPT 48.45 1.889 0.8151 52.427 1.1472 0.8013 1578.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 656.63 1.067 0.9053 1798.104 0.0437 0.8607 1.0235 0.9980 0.9905

LPC 46.01 1.238 0.7547 0.479 0.0000 1.9367 0.5891 0.9214 0.0003

HPC 43.81 5.276 0.8160 8531.463 11.0079 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.581 0.8765 1.283 3.5807 12.6299 0.9723 1.0000 0.0003

LPT 0.74 1.669 0.8212 0.590 1.6687 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–89
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2590.88 5872.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0759 740.53 43.42 13.282

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3421 740.53 43.42 7.031

TEGV 0.0000 0.1740 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.02 38.45 17.991

FanDuct 0.0000 0.4314 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 846.61 69.26 34.241

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.02 38.45 17.991

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 943.60 93.12 49.678

Splitter 6.3414 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 720.02 38.45 17.991

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8897.3 2368.1 4011.6 WB17Y Bleed> 0.4000 1.0000 1.0000 19.4912 534.43 -6.27 9.054

LP_Shaft 1793.8 4620.6 1578.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3383 943.60 93.12 48.534

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9210 943.60 93.12 28.370

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.60 93.12 49.678

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.60 93.12 49.678

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.60 93.12 49.678

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1736.67 0.9995 0.0230 0.25351 0.01177 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.043 0.9801 1.0000 0.9800 613.40 0.249 375.3 344.0

Byp_Nozz 1.258 0.9800 1.0000 0.9800 2006.86 0.582 616.2 6290.8

NASA/TM—2013-218094 N–90
100μm, ISA +18R 

************************************************************************************************************************************ 

Date:07/05/13 Time:09:49:59 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 463.24 Stator 1 exit: 470.64 Stator 2 inlet: 479.94 Stator 2 exit: 484.70 

 Stator 3 inlet: 494.31 Stator 3 exit: 498.63 Stator 4 inlet: 507.63 Stator 4 exit: 511.31 

 Stator 5 inlet: 518.70 Stator 5 exit: 521.92 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.76 

Fan Bypass Relative Humidity 1.24 

LPC Inlet Relative Humidity 1.13 

LPC Exit Relative Humidity 0.10 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 772.64 Fan/LPC Inlet Flow Velocity 187.93 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 454.80 

Additional Water at LPC Exit 0.0000180 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 18.00 257.26 608.3 1.1343 689.97 8.5924 772.64 9.489 0.736 10.000 1693.2 1601.3 1112.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.26 4.267 457.74 -20.96 0.0000 832.40 2.854 407.97 2539.4 0.7800 1.40084 0.0000295 257.25 0.008 0.0000

FS1 Inlet.Fl_O 257.26 4.267 457.74 -20.96 0.0000 832.40 3.893 445.88 4168.2 0.3642 1.40084 0.0000295 257.25 0.008 0.0000

FS12 Splitter.Fl_02 230.44 4.265 457.74 -20.96 0.0000 746.00 3.841 444.23 3531.8 0.3896 1.40084 0.0000295 230.44 0.007 0.0000

FS2 Splitter.Fl_01 26.82 4.265 457.74 -20.96 0.0000 86.82 4.170 454.80 830.5 0.1797 1.40084 0.0000295 26.82 0.001 0.0000

FS14 Fan.Fl_O 230.44 4.811 475.48 -16.70 0.0000 673.99 4.037 452.22 2606.7 0.5066 1.40071 0.0000295 230.44 0.007 0.0000

FS23 LPC.Fl_O 26.82 6.639 531.25 -3.33 0.0000 60.08 6.345 524.41 412.6 0.2553 1.40005 0.0000295 26.82 0.001 0.0000

FS24 VaporIN.Fl_O 26.82 6.639 531.30 -3.42 0.0000 60.08 6.345 524.47 412.6 0.2553 1.40005 0.0000475 26.82 0.001 0.0000

FS25 Bleed2.Fl_O 24.14 6.639 531.30 -3.42 0.0000 54.08 6.403 525.84 412.6 0.2280 1.40005 0.0000475 24.14 0.001 0.0000

FS3 HPC.Fl_O 22.97 40.487 964.20 101.76 0.0000 11.37 35.638 930.68 49.7 0.4331 1.38289 0.0000475 22.97 0.001 0.0000

FS36 Bleed3.Fl_O 17.80 40.487 964.20 101.76 0.0000 8.81 37.704 945.35 49.3 0.3224 1.38289 0.0000475 17.80 0.001 0.0000

FS4 Burner.Fl_O 17.99 39.555 1693.20 89.48 0.0108 12.08 37.353 1669.10 74.6 0.2941 1.33285 0.0000475 17.80 0.001 0.0132

FS45 HPT.Fl_O 24.05 9.489 1116.81 -12.39 0.0080 54.65 8.596 1087.47 265.4 0.3824 1.36775 0.0000475 23.85 0.001 0.0099

FS49 LPT.Fl_O 24.33 3.259 875.22 -71.37 0.0079 142.53 3.069 860.76 860.2 0.2960 1.38277 0.0000475 24.14 0.001 0.0098

FS5 TEGV.Fl_O 24.33 3.259 875.29 -71.37 0.0079 142.53 3.069 860.84 860.2 0.2960 1.38276 0.0000475 24.14 0.001 0.0098

FS8 Core_Nozz.Fl_O 24.33 3.259 875.36 -71.37 0.0079 142.54 2.854 843.76 613.4 0.4418 1.38276 0.0000475 24.14 0.001 0.0098

FS17 FanDuctLkg.Fl_O 230.44 4.811 475.48 -16.70 0.0000 673.99 4.037 452.22 2606.7 0.5066 1.40071 0.0000295 230.44 0.007 0.0000

FS171 Bleed15.Fl_O 233.12 4.811 476.13 -16.55 0.0000 682.30 3.904 448.50 2481.9 0.5544 1.40070 0.0000297 233.12 0.007 0.0000

FS172 FanDuct.Fl_O 233.12 4.811 476.13 -16.55 0.0000 682.30 3.904 448.50 2481.9 0.5544 1.40070 0.0000297 233.12 0.007 0.0000

FS173 Byp_Nozz.Fl_O 233.12 4.811 476.13 -16.55 0.0000 682.30 2.854 410.03 2006.9 0.8966 1.40070 0.0000297 233.12 0.007 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.00 1.128 0.9051 2560.797 1.0388 0.9067 -1386.3 1663.00 54.94

LPC 86.82 1.557 0.8403 2560.797 1.1606 0.8500 -668.7 6.95 3.67

HPC 54.08 6.098 0.8187 8960.611 1.8148 0.8574 -3505.0 61.08 57.75

HPT 12.08 4.168 0.8739 220.399 1.3661 0.8512 3505.0 

LPT 54.65 2.912 0.8506 71.986 1.2742 0.8304 2055.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 866.78 1.125 0.9070 2536.380 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 73.59 1.519 0.7795 0.676 0.0000 1.1798 1.0735 1.0779 0.0003

HPC 49.18 5.858 0.8271 8721.727 10.9930 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.081 0.8739 1.325 4.0806 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.438 0.8569 0.810 2.4380 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–91
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2539.39 6178.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8883 749.49 49.17 9.489

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2824 749.49 49.17 3.259

TEGV 0.0000 0.2960 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 727.79 43.91 14.086

FanDuct 0.0000 0.5544 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 861.70 76.51 27.625 

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 727.79 43.91 14.086

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 964.20 101.76 40.487

Splitter 8.5924 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 727.79 43.91 14.086

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9069.1 2029.8 3505.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6820 531.30 -3.42 6.639

LP_Shaft 2405.7 4486.4 2055.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7561 964.20 101.76 39.555

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4116 964.20 101.76 22.357

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.20 101.76 40.487

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.20 101.76 40.487

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 964.20 101.76 40.487

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.48 -16.70 4.811

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.48 -16.70 4.811

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.48 -16.70 4.811

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.48 -16.70 4.811

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1693.14 0.9995 0.0230 0.19166 0.01077 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.142 0.9801 1.0000 0.9800 613.40 0.442 613.1 463.6

Byp_Nozz 1.686 0.9800 1.0000 0.9800 2006.86 0.897 872.6 6322.7

NASA/TM—2013-218094 N–92
************************************************************************************************************************************ 

Date:07/05/13 Time:09:50:15 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.76 Stator 1 exit: 463.69 Stator 2 inlet: 472.40 Stator 2 exit: 476.84 

 Stator 3 inlet: 485.83 Stator 3 exit: 489.85 Stator 4 inlet: 498.26 Stator 4 exit: 501.67 

 Stator 5 inlet: 508.57 Stator 5 exit: 511.54 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.23 

Fan Bypass Relative Humidity 1.61 

LPC Inlet Relative Humidity 1.45 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 723.11 Fan/LPC Inlet Flow Velocity 181.26 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 448.83 

Additional Water at LPC Exit 0.0000171 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 18.00 250.31 599.2 1.0981 657.95 8.6859 723.11 9.209 0.763 10.000 1667.1 1575.8 1096.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 250.31 4.201 451.57 -22.43 0.0000 816.94 2.947 407.97 2556.8 0.7300 1.40089 0.0000285 250.30 0.007 0.0000

FS1 Inlet.Fl_O 250.31 4.201 451.57 -22.43 0.0000 816.94 3.848 440.36 4168.2 0.3563 1.40089 0.0000285 250.30 0.007 0.0000

FS12 Splitter.Fl_02 224.46 4.199 451.57 -22.43 0.0000 732.96 3.798 438.77 3531.8 0.3813 1.40089 0.0000285 224.46 0.006 0.0000

FS2 Splitter.Fl_01 25.84 4.199 451.57 -22.43 0.0000 84.39 4.111 448.83 830.5 0.1745 1.40089 0.0000285 25.84 0.001 0.0000

FS14 Fan.Fl_O 224.46 4.706 468.12 -18.46 0.0000 665.89 3.972 445.95 2606.7 0.4981 1.40077 0.0000285 224.46 0.006 0.0000

FS23 LPC.Fl_O 25.84 6.402 520.42 -5.92 0.0000 59.42 6.125 513.88 412.6 0.2522 1.40021 0.0000285 25.84 0.001 0.0000

FS24 VaporIN.Fl_O 25.84 6.402 520.48 -6.01 0.0000 59.43 6.125 513.93 412.6 0.2523 1.40020 0.0000457 25.84 0.001 0.0000

FS25 Bleed2.Fl_O 23.26 6.402 520.48 -6.01 0.0000 53.48 6.180 515.24 412.6 0.2253 1.40020 0.0000457 23.26 0.001 0.0000

FS3 HPC.Fl_O 22.13 38.693 942.89 96.50 0.0000 11.33 34.091 910.27 49.7 0.4312 1.38415 0.0000457 22.13 0.001 0.0000

FS36 Bleed3.Fl_O 17.15 38.693 942.89 96.50 0.0000 8.78 36.049 924.53 49.3 0.3212 1.38415 0.0000457 17.15 0.001 0.0000

FS4 Burner.Fl_O 17.33 37.801 1667.10 84.39 0.0107 12.08 35.696 1643.30 74.6 0.2940 1.33418 0.0000457 17.15 0.001 0.0130

FS45 HPT.Fl_O 23.17 9.183 1100.94 -14.86 0.0080 54.02 8.342 1072.74 265.4 0.3770 1.36884 0.0000457 22.99 0.001 0.0098

FS49 LPT.Fl_O 23.44 3.309 873.11 -70.33 0.0079 135.06 3.137 860.29 860.2 0.2789 1.38294 0.0000457 23.26 0.001 0.0097

FS5 TEGV.Fl_O 23.44 3.309 873.18 -70.33 0.0079 135.07 3.137 860.36 860.2 0.2789 1.38293 0.0000457 23.26 0.001 0.0097

FS8 Core_Nozz.Fl_O 23.44 3.309 873.26 -70.33 0.0079 135.07 2.947 845.61 613.3 0.4127 1.38293 0.0000457 23.26 0.001 0.0097

FS17 FanDuctLkg.Fl_O 224.46 4.706 468.12 -18.46 0.0000 665.89 3.972 445.95 2606.7 0.4981 1.40077 0.0000285 224.46 0.006 0.0000

FS171 Bleed15.Fl_O 227.05 4.706 468.71 -18.32 0.0000 673.98 3.847 442.46 2481.9 0.5441 1.40077 0.0000287 227.04 0.007 0.0000

FS172 FanDuct.Fl_O 227.05 4.706 468.71 -18.32 0.0000 673.98 3.847 442.46 2481.9 0.5441 1.40077 0.0000287 227.04 0.007 0.0000

FS173 Byp_Nozz.Fl_O 227.05 4.706 468.71 -18.32 0.0000 673.98 2.947 409.94 2006.9 0.8457 1.40077 0.0000287 227.04 0.007 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 732.96 1.121 0.9043 2497.715 1.0367 0.9059 -1259.6 2278.15 54.78

LPC 84.39 1.525 0.8406 2497.715 1.1525 0.8498 -603.5 6.75 3.33

HPC 53.48 6.044 0.8179 8941.539 1.8116 0.8566 -3291.4 60.99 57.61

HPT 12.08 4.116 0.8726 219.375 1.3628 0.8499 3291.4 

LPT 54.02 2.775 0.8451 70.239 1.2589 0.8253 1863.1 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 851.63 1.118 0.9062 2473.899 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 70.85 1.490 0.7766 0.660 0.0000 1.1909 1.0694 1.0825 0.0003

HPC 48.64 5.806 0.8263 8703.164 11.0057 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.030 0.8726 1.318 4.0300 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.335 0.8514 0.790 2.3350 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–93
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2556.78 5625.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8559 733.26 45.24 9.183

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2721 733.26 45.24 3.309

TEGV 0.0000 0.2789 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.09 40.12 13.506

FanDuct 0.0000 0.5441 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 842.78 71.90 26.422

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.09 40.12 13.506

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 942.89 96.50 38.693

Splitter 8.6859 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 712.09 40.12 13.506

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8957.1 1930.0 3291.4 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5843 520.48 -6.01 6.402

LP_Shaft 2330.5 4198.6 1863.1 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6557 942.89 96.50 37.801

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3238 942.89 96.50 21.432

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 942.89 96.50 38.693

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 942.89 96.50 38.693

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 942.89 96.50 38.693

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 468.12 -18.46 4.706

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1667.04 0.9995 0.0230 0.18276 0.01066 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.123 0.9801 1.0000 0.9800 613.40 0.413 573.4 417.8 

Byp_Nozz 1.597 0.9800 1.0000 0.9800 2006.86 0.846 822.9 5807.0

NASA/TM—2013-218094 N–94
************************************************************************************************************************************ 

Date:07/05/13 Time:09:50:32 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 454.76 Stator 1 exit: 461.52 Stator 2 inlet: 470.01 Stator 2 exit: 474.34 

 Stator 3 inlet: 483.09 Stator 3 exit: 487.00 Stator 4 inlet: 495.19 Stator 4 exit: 498.51 

 Stator 5 inlet: 505.23 Stator 5 exit: 508.11 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.40 

Fan Bypass Relative Humidity 1.75 

LPC Inlet Relative Humidity 1.56 

LPC Exit Relative Humidity 0.15 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 707.26 Fan/LPC Inlet Flow Velocity 178.69 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 407.97 Fan/LPC Inlet Static Temperature 447.01 

Additional Water at LPC Exit 0.0000161 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 18.00 257.06 614.3 1.0904 669.79 8.7249 707.26 9.092 0.772 10.000 1657.2 1566.2 1090.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 257.06 4.339 449.68 -22.87 0.0000 810.61 3.088 407.97 2561.5 0.7140 1.40090 0.0000272 257.05 0.007 0.0000

FS1 Inlet.Fl_O 257.06 4.339 449.68 -22.87 0.0000 810.61 3.981 438.72 4168.2 0.3530 1.40090 0.0000272 257.05 0.007 0.0000

FS12 Splitter.Fl_02 230.63 4.337 449.68 -22.87 0.0000 727.62 3.930 437.15 3531.8 0.3780 1.40090 0.0000272 230.62 0.006 0.0000

FS2 Splitter.Fl_01 26.43 4.337 449.68 -22.87 0.0000 83.40 4.248 447.01 830.5 0.1723 1.40090 0.0000272 26.43 0.001 0.0000

FS14 Fan.Fl_O 230.63 4.848 465.79 -19.01 0.0000 662.46 4.102 444.03 2606.7 0.4945 1.40079 0.0000272 230.62 0.006 0.0000

FS23 LPC.Fl_O 26.43 6.557 516.81 -6.78 0.0000 59.13 6.276 510.38 412.6 0.2509 1.40025 0.0000272 26.43 0.001 0.0000

FS24 VaporIN.Fl_O 26.43 6.557 516.86 -6.86 0.0000 59.14 6.276 510.43 412.6 0.2509 1.40025 0.0000433 26.43 0.001 0.0000

FS25 Bleed2.Fl_O 23.79 6.557 516.86 -6.86 0.0000 53.22 6.332 511.71 412.6 0.2241 1.40025 0.0000433 23.79 0.001 0.0000

FS3 HPC.Fl_O 22.64 39.453 935.42 94.66 0.0000 11.32 34.770 903.10 49.7 0.4307 1.38459 0.0000433 22.64 0.001 0.0000

FS36 Bleed3.Fl_O 17.54 39.453 935.42 94.66 0.0000 8.78 36.762 917.23 49.3 0.3209 1.38459 0.0000433 17.54 0.001 0.0000

FS4 Burner.Fl_O 17.73 38.544 1657.22 82.64 0.0106 12.08 36.397 1633.52 74.6 0.2940 1.33469 0.0000433 17.54 0.001 0.0130

FS45 HPT.Fl_O 23.70 9.404 1094.94 -15.66 0.0079 53.81 8.550 1067.13 265.4 0.3751 1.36926 0.0000433 23.51 0.001 0.0097

FS49 LPT.Fl_O 23.98 3.450 872.15 -69.85 0.0078 132.45 3.278 859.87 860.2 0.2730 1.38302 0.0000433 23.79 0.001 0.0096

FS5 TEGV.Fl_O 23.98 3.450 872.23 -69.85 0.0078 132.45 3.278 859.94 860.2 0.2730 1.38301 0.0000433 23.79 0.001 0.0096

FS8 Core_Nozz.Fl_O 23.98 3.450 872.30 -69.85 0.0078 132.46 3.088 845.95 613.4 0.4028 1.38301 0.0000433 23.79 0.001 0.0096

FS17 FanDuctLkg.Fl_O 230.63 4.848 465.79 -19.01 0.0000 662.46 4.102 444.03 2606.7 0.4945 1.40079 0.0000272 230.62 0.006 0.0000

FS171 Bleed15.Fl_O 233.27 4.848 466.37 -18.88 0.0000 670.47 3.976 440.63 2481.9 0.5399 1.40078 0.0000274 233.26 0.006 0.0000

FS172 FanDuct.Fl_O 233.27 4.848 466.37 -18.88 0.0000 670.47 3.976 440.63 2481.9 0.5399 1.40078 0.0000274 233.26 0.006 0.0000

FS173 Byp_Nozz.Fl_O 233.27 4.848 466.37 -18.88 0.0000 670.47 3.088 409.90 2006.9 0.8289 1.40078 0.0000274 233.26 0.006 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 727.62 1.118 0.9040 2472.405 1.0358 0.9055 -1260.0 2678.58 54.68

LPC 83.40 1.512 0.8407 2472.405 1.1493 0.8497 -601.8 6.67 3.26

HPC 53.22 6.017 0.8174 8933.055 1.8098 0.8562 -3334.5 61.04 57.63

HPT 12.08 4.099 0.8721 219.054 1.3617 0.8494 3334.5 

LPT 53.81 2.726 0.8431 69.571 1.2534 0.8234 1861.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 845.43 1.115 0.9058 2448.831 0.0412 0.8607 1.0235 0.9980 0.9905

LPC 69.76 1.479 0.7754 0.653 0.0000 1.1955 1.0683 1.0842 0.0003

HPC 48.41 5.780 0.8259 8694.906 11.0057 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.013 0.8721 1.316 4.0128 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.298 0.8493 0.783 2.2982 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–95
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2561.46 5650.8 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8755 727.65 43.90 9.404

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2783 727.65 43.90 3.450

TEGV 0.0000 0.2730 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 706.68 38.82 13.794

FanDuct 0.0000 0.5399 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 836.18 70.30 26.952

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 706.68 38.82 13.794

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 935.42 94.66 39.453

Splitter 8.7249 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 706.68 38.82 13.794

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8917.4 1963.9 3334.5 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6434 516.86 -6.86 6.557

LP_Shaft 2302.1 4247.7 1861.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7164 935.42 94.66 38.544

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3769 935.42 94.66 21.876

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.42 94.66 39.453

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.42 94.66 39.453

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 935.42 94.66 39.453

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 465.79 -19.01 4.848

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1657.16 0.9995 0.0230 0.18605 0.01061 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.403 559.7 417.1

Byp_Nozz 1.570 0.9800 1.0000 0.9800 2006.86 0.829 806.6 5847.9

NASA/TM—2013-218094 N–96
************************************************************************************************************************************ 

Date:07/05/13 Time:09:50:46 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 10/ 24/ 1/ 8 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 456.41 Stator 1 exit: 462.77 Stator 2 inlet: 470.73 Stator 2 exit: 474.78 

 Stator 3 inlet: 482.99 Stator 3 exit: 486.63 Stator 4 inlet: 494.31 Stator 4 exit: 497.39 

 Stator 5 inlet: 503.67 Stator 5 exit: 506.32 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.00 

Fan Bypass Relative Humidity 2.26 

LPC Inlet Relative Humidity 2.00 

LPC Exit Relative Humidity 0.22 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 667.90 Fan/LPC Inlet Flow Velocity 173.05 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 414.42 Fan/LPC Inlet Static Temperature 449.11 

Additional Water at LPC Exit 0.0000045 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 18.00 278.57 669.4 1.0741 718.95 8.8070 667.90 8.757 0.795 10.000 1650.4 1559.3 1088.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 278.57 4.831 451.61 -22.45 0.0000 790.73 3.578 414.42 2577.4 0.6690 1.40088 0.0000348 278.56 0.010 0.0000

FS1 Inlet.Fl_O 278.57 4.831 451.61 -22.45 0.0000 790.73 4.453 441.21 4168.2 0.3430 1.40088 0.0000348 278.56 0.010 0.0000

FS12 Splitter.Fl_02 250.17 4.829 451.61 -22.45 0.0000 710.46 4.399 439.71 3531.8 0.3674 1.40088 0.0000348 250.16 0.009 0.0000

FS2 Splitter.Fl_01 28.41 4.829 451.61 -22.45 0.0000 80.67 4.736 449.11 830.5 0.1665 1.40088 0.0000348 28.40 0.001 0.0000

FS14 Fan.Fl_O 250.17 5.360 466.77 -18.82 0.0000 650.67 4.571 445.97 2606.7 0.4824 1.40078 0.0000348 250.16 0.009 0.0000

FS23 LPC.Fl_O 28.41 7.122 514.69 -7.33 0.0000 58.39 6.825 508.46 412.6 0.2475 1.40028 0.0000348 28.40 0.001 0.0000

FS24 VaporIN.Fl_O 28.41 7.122 514.73 -7.35 0.0000 58.39 6.825 508.49 412.6 0.2475 1.40028 0.0000393 28.40 0.001 0.0000

FS25 Bleed2.Fl_O 25.57 7.122 514.73 -7.35 0.0000 52.55 6.883 509.74 412.6 0.2211 1.40028 0.0000393 25.56 0.001 0.0000

FS3 HPC.Fl_O 24.33 42.305 928.59 93.00 0.0000 11.31 37.301 896.61 49.7 0.4298 1.38498 0.0000393 24.32 0.001 0.0000

FS36 Bleed3.Fl_O 18.85 42.305 928.59 93.00 0.0000 8.76 39.429 910.58 49.3 0.3203 1.38498 0.0000393 18.85 0.001 0.0000

FS4 Burner.Fl_O 19.05 41.330 1650.37 81.01 0.0106 12.08 39.028 1626.75 74.6 0.2940 1.33504 0.0000393 18.85 0.001 0.0130

FS45 HPT.Fl_O 25.47 10.192 1092.35 -16.13 0.0079 53.29 9.287 1065.22 265.4 0.3708 1.36944 0.0000393 25.26 0.001 0.0097

FS49 LPT.Fl_O 25.76 3.941 881.32 -67.40 0.0078 125.22 3.767 870.32 860.2 0.2568 1.38251 0.0000393 25.56 0.001 0.0096

FS5 TEGV.Fl_O 25.76 3.941 881.39 -67.40 0.0078 125.23 3.767 870.39 860.2 0.2568 1.38251 0.0000393 25.56 0.001 0.0096

FS8 Core_Nozz.Fl_O 25.76 3.941 881.46 -67.39 0.0078 125.23 3.578 858.15 613.4 0.3765 1.38250 0.0000393 25.56 0.001 0.0096

FS17 FanDuctLkg.Fl_O 250.17 5.360 466.77 -18.82 0.0000 650.67 4.571 445.97 2606.7 0.4824 1.40078 0.0000348 250.16 0.009 0.0000

FS171 Bleed15.Fl_O 253.01 5.360 467.31 -18.69 0.0000 658.44 4.440 442.79 2481.9 0.5256 1.40078 0.0000348 253.00 0.009 0.0000

FS172 FanDuct.Fl_O 253.01 5.360 467.31 -18.69 0.0000 658.44 4.440 442.79 2481.9 0.5256 1.40078 0.0000348 253.00 0.009 0.0000 

FS173 Byp_Nozz.Fl_O 253.01 5.360 467.31 -18.69 0.0000 658.44 3.578 416.27 2006.9 0.7821 1.40078 0.0000348 253.00 0.009 0.0000

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.46 1.110 0.9032 2395.702 1.0336 0.9046 -1286.1 5792.75 54.21

LPC 80.67 1.475 0.8416 2395.702 1.1397 0.8501 -607.7 6.41 3.05

HPC 52.55 5.940 0.8161 8911.013 1.8040 0.8550 -3541.9 61.34 57.85

HPT 12.08 4.055 0.8716 218.515 1.3586 0.8490 3541.9 

LPT 53.29 2.586 0.8385 67.637 1.2372 0.8195 1893.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.48 1.108 0.9050 2372.859 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.44 1.445 0.7718 0.633 0.0000 1.2142 1.0674 1.0904 0.0003

HPC 47.80 5.707 0.8246 8673.452 10.9959 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.970 0.8716 1.313 3.9703 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.193 0.8448 0.761 2.1928 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–97
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2577.36 5782.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9408 723.12 42.83 10.192

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2991 723.12 42.83 3.941

TEGV 0.0000 0.2568 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.39 37.81 14.862

FanDuct 0.0000 0.5256 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 830.45 68.92 28.935

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.39 37.81 14.862

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 928.59 93.00 42.305

Splitter 8.8070 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.39 37.81 14.862

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8877.1 2095.5 3541.9 WB17Y Bleed> 0.1000 1.0000 1.0000 2.8406 514.73 -7.35 7.122

LP_Shaft 2235.5 4449.5 1893.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.9190 928.59 93.00 41.330

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.5542 928.59 93.00 23.519

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.59 93.00 42.305

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.59 93.00 42.305

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 928.59 93.00 42.305

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 466.77 -18.82 5.360

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 466.77 -18.82 5.360

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 466.77 -18.82 5.360

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 466.77 -18.82 5.360

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1650.30 0.9995 0.0230 0.19971 0.01059 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.102 0.9801 1.0000 0.9800 613.40 0.376 526.7 421.8 

Byp_Nozz 1.498 0.9800 1.0000 0.9800 2006.86 0.782 766.9 6030.4

NASA/TM—2013-218094 N–98
************************************************************************************************************************************ 

Date:07/05/13 Time:09:51:03 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 465.04 Stator 1 exit: 470.56 Stator 2 inlet: 477.37 Stator 2 exit: 480.66 

 Stator 3 inlet: 487.79 Stator 3 exit: 490.68 Stator 4 inlet: 497.38 Stator 4 exit: 499.77 

 Stator 5 inlet: 505.17 Stator 5 exit: 507.19 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.96 

Fan Bypass Relative Humidity 3.12 

LPC Inlet Relative Humidity 2.83 

LPC Exit Relative Humidity 0.47 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 617.99 Fan/LPC Inlet Flow Velocity 175.00 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 429.58 Fan/LPC Inlet Static Temperature 458.86 

Additional Water at LPC Exit 0.0000076 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 18.00 305.09 728.7 1.0768 784.65 8.3701 617.99 8.197 0.828 10.000 1654.7 1563.0 1093.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 305.09 5.595 461.42 -20.30 0.0000 755.81 4.358 429.58 2596.1 0.6080 1.40081 0.0000681 305.07 0.021 0.0001

FS1 Inlet.Fl_O 305.09 5.595 461.42 -20.30 0.0000 755.81 5.199 451.82 4168.2 0.3256 1.40081 0.0000681 305.07 0.021 0.0001

FS12 Splitter.Fl_02 272.53 5.592 461.42 -20.30 0.0000 675.49 5.147 450.59 3531.8 0.3462 1.40081 0.0000681 272.51 0.019 0.0001

FS2 Splitter.Fl_01 32.56 5.592 461.42 -20.30 0.0000 80.70 5.485 458.86 830.5 0.1666 1.40081 0.0000681 32.56 0.002 0.0001

FS14 Fan.Fl_O 272.53 6.139 475.25 -16.98 0.0000 624.50 5.321 456.19 2606.7 0.4566 1.40070 0.0000681 272.51 0.019 0.0001

FS23 LPC.Fl_O 32.56 7.825 515.83 -7.25 0.0000 60.98 7.468 508.98 412.6 0.2594 1.40026 0.0000681 32.56 0.002 0.0001

FS24 VaporIN.Fl_O 32.56 7.825 515.87 -7.29 0.0000 60.98 7.468 509.02 412.6 0.2594 1.40026 0.0000756 32.56 0.002 0.0001

FS25 Bleed2.Fl_O 27.68 7.825 515.87 -7.29 0.0000 51.84 7.571 511.01 412.6 0.2179 1.40026 0.0000756 27.67 0.002 0.0001

FS3 HPC.Fl_O 26.33 45.861 927.38 92.50 0.0000 11.28 40.463 895.60 49.7 0.4287 1.38505 0.0000756 26.33 0.002 0.0001

FS36 Bleed3.Fl_O 20.41 45.861 927.38 92.50 0.0000 8.74 42.758 909.48 49.3 0.3195 1.38505 0.0000756 20.41 0.002 0.0001

FS4 Burner.Fl_O 20.63 44.805 1654.74 80.41 0.0107 12.08 42.309 1631.07 74.6 0.2940 1.33476 0.0000756 20.41 0.002 0.0131

FS45 HPT.Fl_O 27.57 11.202 1097.92 -16.13 0.0080 52.62 10.234 1071.44 265.4 0.3654 1.36903 0.0000756 27.35 0.002 0.0098

FS49 LPT.Fl_O 27.89 4.717 904.47 -63.05 0.0079 114.77 4.543 895.13 860.2 0.2340 1.38114 0.0000756 27.67 0.002 0.0097

FS5 TEGV.Fl_O 27.89 4.717 904.54 -63.05 0.0079 114.77 4.543 895.20 860.2 0.2340 1.38113 0.0000756 27.67 0.002 0.0097

FS8 Core_Nozz.Fl_O 27.89 4.717 904.62 -63.05 0.0079 114.78 4.358 885.09 613.4 0.3400 1.38113 0.0000756 27.67 0.002 0.0097

FS17 FanDuctLkg.Fl_O 272.53 6.139 475.25 -16.98 0.0000 624.50 5.321 456.19 2606.7 0.4566 1.40070 0.0000681 272.51 0.019 0.0001

FS171 Bleed15.Fl_O 277.42 6.139 475.96 -16.81 0.0000 636.17 5.173 453.22 2481.9 0.5004 1.40070 0.0000682 277.40 0.019 0.0001

FS172 FanDuct.Fl_O 277.42 6.139 475.96 -16.81 0.0000 636.17 5.173 453.22 2481.9 0.5004 1.40070 0.0000682 277.40 0.019 0.0001

FS173 Byp_Nozz.Fl_O 277.42 6.139 475.96 -16.81 0.0000 636.17 4.358 431.52 2006.9 0.7168 1.40070 0.0000682 277.40 0.019 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 675.49 1.098 0.9021 2249.340 1.0300 0.9034 -1278.0 -9299.10 52.72

LPC 80.70 1.399 0.8552 2249.340 1.1179 0.8619 -601.0 5.96 2.63

HPC 51.84 5.861 0.8147 8887.506 1.7977 0.8536 -3812.6 61.60 58.03

HPT 12.08 4.000 0.8718 217.891 1.3544 0.8495 3812.6 

LPT 52.62 2.375 0.8303 64.028 1.2114 0.8124 1879.0 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 784.85 1.095 0.9039 2227.892 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 60.32 1.382 0.7655 0.594 0.0000 1.3379 1.0458 1.1172 0.0003

HPC 47.14 5.632 0.8231 8650.571 10.9889 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.917 0.8718 1.310 3.9166 12.6299 0.9723 1.0000 0.0003

LPT 0.81 2.034 0.8365 0.720 2.0342 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–99
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2596.13 5860.1 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0185 723.08 42.61 11.202

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3238 723.08 42.61 4.717

TEGV 0.0000 0.2340 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.46 37.62 16.193

FanDuct 0.0000 0.5004 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 829.79 68.55 31.408

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.46 37.62 16.193

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 927.38 92.50 45.861

Splitter 8.3701 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 702.46 37.62 16.193

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8863.5 2259.2 3812.6 WB17Y Bleed> 0.1500 1.0000 1.0000 4.8841 515.87 -7.29 7.825

LP_Shaft 2121.6 4651.5 1879.0 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1601 927.38 92.50 44.805

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7651 927.38 92.50 25.584

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.38 92.50 45.861

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.38 92.50 45.861

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 927.38 92.50 45.861

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 475.25 -16.98 6.139

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1654.68 0.9995 0.0230 0.21796 0.01068 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.082 0.9801 1.0000 0.9800 613.40 0.340 482.8 418.6

Byp_Nozz 1.409 0.9800 1.0000 0.9800 2006.86 0.717 715.6 6170.2

NASA/TM—2013-218094 N–100
************************************************************************************************************************************ 

Date:07/05/13 Time:09:51:32 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 20/ 48/ 2/17 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 473.10 Stator 1 exit: 477.17 Stator 2 inlet: 481.78 Stator 2 exit: 483.58 

 Stator 3 inlet: 488.71 Stator 3 exit: 490.11 Stator 4 inlet: 495.03 Stator 4 exit: 496.03 

 Stator 5 inlet: 499.63 Stator 5 exit: 500.34 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.82 

Fan Bypass Relative Humidity 3.94 

LPC Inlet Relative Humidity 3.82 

LPC Exit Relative Humidity 1.20 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 571.13 Fan/LPC Inlet Flow Velocity 194.56 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.36 

Ambient Static Temperature 445.14 Fan/LPC Inlet Static Temperature 469.17 

Additional Water at LPC Exit 0.0000104 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 18.00 330.53 748.0 1.1197 837.49 7.0489 571.13 7.334 0.859 10.000 1665.5 1571.5 1104.9

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 330.53 6.516 472.33 -18.03 0.0000 711.36 5.297 445.14 2594.9 0.5520 1.40072 0.0001274 330.49 0.042 0.0001

FS1 Inlet.Fl_O 330.53 6.516 472.33 -18.03 0.0000 711.36 6.111 463.74 4168.2 0.3040 1.40072 0.0001274 330.49 0.042 0.0001

FS12 Splitter.Fl_02 289.47 6.513 472.33 -18.03 0.0000 623.29 6.078 463.08 3531.8 0.3157 1.40072 0.0001274 289.43 0.037 0.0001

FS2 Splitter.Fl_01 41.07 6.513 472.33 -18.03 0.0000 88.42 6.362 469.17 830.5 0.1832 1.40072 0.0001274 41.06 0.005 0.0001

FS14 Fan.Fl_O 289.47 7.057 484.46 -15.12 0.0000 582.62 6.258 468.09 2606.7 0.4177 1.40061 0.0001274 289.43 0.037 0.0001

FS23 LPC.Fl_O 41.07 8.205 511.58 -8.62 0.0000 73.04 7.654 501.50 412.6 0.3169 1.40031 0.0001274 41.06 0.005 0.0001

FS24 VaporIN.Fl_O 41.07 8.205 511.62 -8.66 0.0000 73.05 7.654 501.54 412.6 0.3169 1.40031 0.0001377 41.06 0.006 0.0001

FS25 Bleed2.Fl_O 28.75 8.205 511.62 -8.66 0.0000 51.13 7.946 506.94 412.6 0.2148 1.40031 0.0001377 28.74 0.004 0.0001

FS3 HPC.Fl_O 27.35 47.789 918.52 89.96 0.0000 11.19 42.268 887.62 49.7 0.4243 1.38555 0.0001377 27.35 0.004 0.0001

FS36 Bleed3.Fl_O 21.20 47.789 918.52 89.96 0.0000 8.67 44.611 901.08 49.3 0.3166 1.38555 0.0001377 21.19 0.003 0.0001

FS4 Burner.Fl_O 21.43 46.689 1665.49 77.57 0.0110 12.09 44.085 1641.70 74.6 0.2942 1.33402 0.0001377 21.19 0.003 0.0135

FS45 HPT.Fl_O 28.64 12.029 1109.28 -17.71 0.0082 51.17 11.052 1084.25 265.4 0.3537 1.36812 0.0001377 28.41 0.004 0.0102

FS49 LPT.Fl_O 28.98 5.626 936.96 -59.42 0.0081 101.74 5.464 929.48 860.2 0.2061 1.37906 0.0001377 28.74 0.004 0.0101

FS5 TEGV.Fl_O 28.98 5.626 937.04 -59.42 0.0081 101.74 5.464 929.55 860.2 0.2061 1.37905 0.0001377 28.74 0.004 0.0101

FS8 Core_Nozz.Fl_O 28.98 5.626 937.11 -59.42 0.0081 101.75 5.297 921.69 613.4 0.2968 1.37905 0.0001377 28.74 0.004 0.0101

FS17 FanDuctLkg.Fl_O 289.47 7.057 484.46 -15.12 0.0000 582.62 6.258 468.09 2606.7 0.4177 1.40061 0.0001274 289.43 0.037 0.0001

FS171 Bleed15.Fl_O 301.79 7.057 485.57 -14.86 0.0000 608.11 6.063 464.94 2481.9 0.4705 1.40060 0.0001278 301.75 0.039 0.0001

FS172 FanDuct.Fl_O 301.79 7.057 485.57 -14.86 0.0000 608.11 6.063 464.94 2481.9 0.4705 1.40060 0.0001278 301.75 0.039 0.0001

FS173 Byp_Nozz.Fl_O 301.79 7.057 485.57 -14.86 0.0000 608.11 5.297 447.31 2006.9 0.6533 1.40060 0.0001278 301.75 0.039 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 623.29 1.083 0.9032 2044.521 1.0257 0.9043 -1190.8 -2764.78 49.88

LPC 88.42 1.260 0.8217 2044.521 1.0831 0.8274 -546.8 6.38 2.41

HPC 51.13 5.824 0.8139 8865.647 1.7953 0.8529 -3913.9 60.72 57.10

HPT 12.09 3.881 0.8732 215.758 1.3457 0.8517 3913.9 

LPT 51.17 2.138 0.8210 58.579 1.1810 0.8047 1737.6 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 724.20 1.082 0.9050 2025.027 0.0425 0.8607 1.0235 0.9980 0.9905

LPC 53.47 1.311 0.7607 0.540 0.0000 1.6538 0.8353 1.0801 0.0003

HPC 46.51 5.597 0.8223 8629.294 11.0519 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.801 0.8732 1.297 3.8014 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.856 0.8271 0.659 1.8560 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–101
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2594.94 5867.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0579 716.45 40.65 12.029

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3363 716.45 40.65 5.626

TEGV 0.0000 0.2061 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.06 35.72 16.914

FanDuct 0.0000 0.4705 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 821.98 66.29 32.747

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.06 35.72 16.914

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 918.52 89.96 47.789

Splitter 7.0489 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 696.06 35.72 16.914

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8805.2 2334.6 3913.9 WB17Y Bleed> 0.3000 1.0000 1.0000 12.3197 511.62 -8.66 8.205

LP_Shaft 1951.0 4677.5 1737.6 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.2822 918.52 89.96 46.689

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.8720 918.52 89.96 26.863

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.52 89.96 47.789

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.52 89.96 47.789

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 918.52 89.96 47.789

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 484.46 -15.12 7.057

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1665.43 0.9995 0.0230 0.23264 0.01098 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.062 0.9801 1.0000 0.9800 613.40 0.297 429.8 387.1

Byp_Nozz 1.332 0.9800 1.0000 0.9800 2006.86 0.653 664.0 6228.2

NASA/TM—2013-218094 N–102
************************************************************************************************************************************ 

Date:07/05/13 Time:09:52:03 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 26/ 54/ 2/23 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 486.26 Stator 1 exit: 489.21 Stator 2 inlet: 491.94 Stator 2 exit: 492.70 

 Stator 3 inlet: 496.02 Stator 3 exit: 496.35 Stator 4 inlet: 499.59 Stator 4 exit: 499.62 

 Stator 5 inlet: 501.46 Stator 5 exit: 501.30 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.85 

Fan Bypass Relative Humidity 4.91 

LPC Inlet Relative Humidity 5.02 

LPC Exit Relative Humidity 2.62 

HPC Relative Humidity 0.01 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 518.26 Fan/LPC Inlet Flow Velocity 204.34 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.74 

Ambient Static Temperature 465.18 Fan/LPC Inlet Static Temperature 484.08 

Additional Water at LPC Exit 0.0000163 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 18.00 368.14 831.4 1.1216 932.52 6.2369 518.26 6.453 0.890 10.000 1698.5 1600.5 1135.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 368.14 7.943 487.56 -15.16 0.0000 660.35 6.740 465.18 2615.9 0.4900 1.40057 0.0002627 368.04 0.097 0.0003

FS1 Inlet.Fl_O 368.14 7.943 487.56 -15.16 0.0000 660.35 7.522 480.02 4168.2 0.2799 1.40057 0.0002627 368.04 0.097 0.0003

FS12 Splitter.Fl_02 317.27 7.939 487.56 -15.16 0.0000 569.39 7.503 479.73 3531.8 0.2854 1.40057 0.0002627 317.18 0.083 0.0003

FS2 Splitter.Fl_01 50.87 7.939 487.56 -15.16 0.0000 91.29 7.743 484.08 830.5 0.1894 1.40057 0.0002627 50.86 0.013 0.0003

FS14 Fan.Fl_O 317.27 8.512 498.38 -12.56 0.0000 536.96 7.712 484.52 2606.7 0.3780 1.40045 0.0002627 317.18 0.083 0.0003

FS23 LPC.Fl_O 50.87 9.077 515.17 -8.54 0.0000 82.08 8.289 501.96 412.6 0.3626 1.40024 0.0002627 50.86 0.013 0.0003

FS24 VaporIN.Fl_O 50.87 9.077 515.22 -8.62 0.0000 82.09 8.288 502.01 412.6 0.3627 1.40024 0.0002790 50.86 0.014 0.0003

FS25 Bleed2.Fl_O 30.52 9.077 515.22 -8.62 0.0000 49.25 8.811 510.86 412.6 0.2065 1.40024 0.0002790 30.51 0.009 0.0003

FS3 HPC.Fl_O 29.04 51.257 917.82 88.98 0.0000 11.08 45.477 887.72 49.7 0.4188 1.38557 0.0002790 29.03 0.008 0.0003

FS36 Bleed3.Fl_O 22.51 51.257 917.82 88.98 0.0000 8.58 47.924 900.79 49.3 0.3129 1.38557 0.0002790 22.50 0.006 0.0003

FS4 Burner.Fl_O 22.77 50.076 1698.52 76.01 0.0115 12.09 47.282 1674.33 74.6 0.2946 1.33205 0.0002790 22.50 0.006 0.0143

FS45 HPT.Fl_O 30.42 13.552 1140.27 -18.07 0.0086 48.92 12.555 1117.14 265.4 0.3361 1.36582 0.0002790 30.16 0.008 0.0108

FS49 LPT.Fl_O 30.78 7.047 987.01 -55.10 0.0085 88.55 6.895 981.14 860.2 0.1785 1.37573 0.0002790 30.51 0.009 0.0107

FS5 TEGV.Fl_O 30.78 7.047 987.08 -55.10 0.0085 88.55 6.895 981.21 860.2 0.1785 1.37572 0.0002790 30.51 0.009 0.0107

FS8 Core_Nozz.Fl_O 30.78 7.047 987.15 -55.10 0.0085 88.56 6.740 975.21 613.4 0.2552 1.37572 0.0002790 30.51 0.009 0.0107

FS17 FanDuctLkg.Fl_O 317.27 8.512 498.38 -12.56 0.0000 536.96 7.712 484.52 2606.7 0.3780 1.40045 0.0002627 317.18 0.083 0.0003

FS171 Bleed15.Fl_O 337.62 8.512 499.40 -12.32 0.0000 571.98 7.477 481.22 2481.9 0.4343 1.40044 0.0002637 337.53 0.089 0.0003

FS172 FanDuct.Fl_O 337.62 8.512 499.40 -12.32 0.0000 571.98 7.477 481.22 2481.9 0.4343 1.40044 0.0002637 337.53 0.089 0.0003

FS173 Byp_Nozz.Fl_O 337.62 8.512 499.40 -12.32 0.0000 571.98 6.740 467.15 2006.9 0.5870 1.40044 0.0002637 337.53 0.089 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 569.39 1.072 0.9054 1848.588 1.0222 0.9063 -1165.6 -1881.76 46.42

LPC 91.29 1.143 0.6892 1848.588 1.0566 0.6951 -476.7 6.97 2.19

HPC 49.25 5.647 0.8099 8804.864 1.7814 0.8491 -4112.6 60.54 56.71

HPT 12.09 3.695 0.8752 212.931 1.3307 0.8549 4112.6 

LPT 48.92 1.923 0.8141 53.076 1.1519 0.7997 1642.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 661.57 1.070 0.9072 1830.961 0.0438 0.8607 1.0235 0.9980 0.9905

LPC 47.03 1.247 0.7558 0.488 0.0000 1.9411 0.5800 0.9119 0.0003

HPC 44.79 5.428 0.8182 8570.132 11.0891 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.621 0.8752 1.280 3.6205 12.6299 0.9723 1.0000 0.0003

LPT 0.75 1.694 0.8201 0.597 1.6942 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–103
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2615.92 5930.0 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.1232 717.88 40.18 13.552

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3571 717.88 40.18 7.047

TEGV 0.0000 0.1785 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.71 35.30 18.357

FanDuct 0.0000 0.4343 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 822.29 65.56 35.228

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.71 35.30 18.357

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 917.82 88.98 51.257

Splitter 6.2369 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 697.71 35.30 18.357

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8775.5 2461.4 4112.6 WB17Y Bleed> 0.4000 1.0000 1.0000 20.3483 515.22 -8.62 9.077

LP_Shaft 1792.3 4812.6 1642.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4850 917.82 88.98 50.076

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 3.0495 917.82 88.98 29.184

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 917.82 88.98 51.257

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 917.82 88.98 51.257

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 917.82 88.98 51.257

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 498.38 -12.56 8.512

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 498.38 -12.56 8.512

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 498.38 -12.56 8.512

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 498.38 -12.56 8.512

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1698.45 0.9995 0.0230 0.25903 0.01151 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.046 0.9801 1.0000 0.9800 613.40 0.255 379.7 363.2

Byp_Nozz 1.263 0.9800 1.0000 0.9800 2006.86 0.587 609.7 6398.1

NASA/TM—2013-218094 N–104
************************************************************************************************************************************ 

Date:07/05/13 Time:09:52:30 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 22/ 50/ 2/19 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 500.26 Stator 1 exit: 502.62 Stator 2 inlet: 504.93 Stator 2 exit: 505.65 

 Stator 3 inlet: 508.35 Stator 3 exit: 508.74 Stator 4 inlet: 511.35 Stator 4 exit: 511.51 

 Stator 5 inlet: 513.10 Stator 5 exit: 513.12 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.53 

Fan Bypass Relative Humidity 5.96 

LPC Inlet Relative Humidity 5.71 

LPC Exit Relative Humidity 3.40 

HPC Relative Humidity 0.01 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 479.99 Fan/LPC Inlet Flow Velocity 173.50 

Ambient Static Pressure 8.15 Fan/LPC Inlet Static Pressure 9.17 

Ambient Static Temperature 481.63 Fan/LPC Inlet Static Temperature 498.31 

Additional Water at LPC Exit 0.0000240 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.446 15435.0 18.00 386.68 641.0 1.3790 884.01 6.7784 479.99 5.288 0.902 10.000 1649.7 1553.9 1125.3

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 386.68 9.342 500.81 -13.05 0.0000 597.73 8.149 481.63 2540.9 0.4460 1.40040 0.0004484 386.51 0.173 0.0004

FS1 Inlet.Fl_O 386.68 9.342 500.81 -13.05 0.0000 597.73 8.941 494.57 4168.2 0.2511 1.40040 0.0004484 386.51 0.173 0.0004

FS12 Splitter.Fl_02 336.97 9.337 500.81 -13.05 0.0000 521.14 8.912 494.17 3531.8 0.2590 1.40040 0.0004484 336.82 0.151 0.0004

FS2 Splitter.Fl_01 49.71 9.337 500.81 -13.05 0.0000 76.88 9.175 498.31 830.5 0.1585 1.40040 0.0004484 49.69 0.022 0.0004

FS14 Fan.Fl_O 336.97 9.813 508.79 -11.14 0.0000 499.81 9.027 496.79 2606.7 0.3474 1.40030 0.0004484 336.82 0.151 0.0004

FS23 LPC.Fl_O 49.71 10.430 523.17 -7.69 0.0000 70.35 9.784 513.68 412.6 0.3037 1.40011 0.0004484 49.69 0.022 0.0004

FS24 VaporIN.Fl_O 49.71 10.430 523.23 -7.81 0.0000 70.35 9.784 513.74 412.6 0.3038 1.40011 0.0004723 49.69 0.023 0.0005

FS25 Bleed2.Fl_O 29.83 10.430 523.23 -7.81 0.0000 42.21 10.208 520.01 412.6 0.1758 1.40011 0.0004723 29.81 0.014 0.0005

FS3 HPC.Fl_O 28.38 49.398 887.55 80.44 0.0000 11.05 43.865 858.56 49.7 0.4171 1.38724 0.0004723 28.37 0.013 0.0005

FS36 Bleed3.Fl_O 22.00 49.398 887.55 80.44 0.0000 8.56 46.206 871.14 49.3 0.3117 1.38724 0.0004723 21.99 0.010 0.0005

FS4 Burner.Fl_O 22.24 48.260 1649.74 67.94 0.0112 12.08 45.573 1626.17 74.6 0.2940 1.33460 0.0004723 21.99 0.010 0.0141

FS45 HPT.Fl_O 29.72 14.273 1129.99 -16.95 0.0083 45.17 13.390 1110.77 265.4 0.3069 1.36663 0.0004723 29.47 0.014 0.0107

FS49 LPT.Fl_O 30.07 8.396 1005.97 -46.64 0.0082 73.31 8.272 1001.92 860.2 0.1469 1.37467 0.0004723 29.81 0.014 0.0106

FS5 TEGV.Fl_O 30.07 8.396 1006.04 -46.64 0.0082 73.31 8.272 1001.99 860.2 0.1469 1.37466 0.0004723 29.81 0.014 0.0106

FS8 Core_Nozz.Fl_O 30.07 8.396 1006.11 -46.64 0.0082 73.32 8.149 997.96 613.4 0.2087 1.37466 0.0004723 29.81 0.014 0.0106

FS17 FanDuctLkg.Fl_O 336.97 9.813 508.79 -11.14 0.0000 499.81 9.027 496.79 2606.7 0.3474 1.40030 0.0004484 336.82 0.151 0.0004

FS171 Bleed15.Fl_O 356.86 9.813 509.59 -10.95 0.0000 529.73 8.814 494.18 2481.9 0.3947 1.40029 0.0004497 356.69 0.160 0.0004

FS172 FanDuct.Fl_O 356.86 9.813 509.59 -10.95 0.0000 529.73 8.814 494.18 2481.9 0.3947 1.40029 0.0004497 356.69 0.160 0.0004

FS173 Byp_Nozz.Fl_O 356.86 9.813 509.59 -10.95 0.0000 529.73 8.149 483.23 2006.9 0.5220 1.40029 0.0004497 356.69 0.160 0.0004

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 521.14 1.051 0.8982 1610.080 1.0159 0.8989 -912.3 -1526.14 44.72

LPC 76.88 1.117 0.7202 1610.080 1.0446 0.7246 -377.2 8.26 1.96

HPC 42.21 4.736 0.7955 8540.497 1.6963 0.8340 -3634.0 68.25 63.03

HPT 12.08 3.381 0.8666 211.191 1.3031 0.8466 3634.0 

LPT 45.17 1.700 0.8004 47.065 1.1197 0.7881 1289.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 605.52 1.050 0.9000 1594.728 0.0442 0.8607 1.0235 0.9980 0.9905

LPC 39.69 1.184 0.7480 0.425 0.0000 1.9368 0.6353 0.9629 0.0003

HPC 38.39 4.560 0.8038 8312.813 10.7602 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.315 0.8666 1.269 3.3152 12.6299 0.9723 1.0000 0.0003

LPT 0.69 1.526 0.8063 0.529 1.5265 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–105
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2540.86 5768.7 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0977 706.47 36.31 14.273

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3490 706.47 36.31 8.396

TEGV 0.0000 0.1469 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.22 31.90 19.003

FanDuct 0.0000 0.3947 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 800.98 59.26 34.590

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.22 31.90 19.003

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 887.55 80.44 49.398

Splitter 6.7784 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 688.22 31.90 19.003

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8577.9 2225.0 3634.0 WB17Y Bleed> 0.4000 1.0000 1.0000 19.8855 523.23 -7.81 10.430

LP_Shaft 1582.1 4280.9 1289.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.4058 887.55 80.44 48.260

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9801 887.55 80.44 28.819

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 887.55 80.44 49.398

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 887.55 80.44 49.398

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 887.55 80.44 49.398

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 508.79 -11.14 9.813

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1649.68 0.9995 0.0230 0.24556 0.01117 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.030 0.9802 1.0000 0.9800 613.40 0.209 314.0 293.5

Byp_Nozz 1.204 0.9800 1.0000 0.9800 2006.86 0.522 551.4 6116.3

NASA/TM—2013-218094 N–106
100μm, ISA +36R 

************************************************************************************************************************************ 

Date:07/05/13 Time:10:02:31 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 483.67 Stator 1 exit: 491.43 Stator 2 inlet: 501.19 Stator 2 exit: 506.18 

 Stator 3 inlet: 516.27 Stator 3 exit: 520.81 Stator 4 inlet: 530.25 Stator 4 exit: 534.11 

 Stator 5 inlet: 541.87 Stator 5 exit: 545.24 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 1.97 

Fan Bypass Relative Humidity 1.41 

LPC Inlet Relative Humidity 1.30 

LPC Exit Relative Humidity 0.13 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 789.49 Fan/LPC Inlet Flow Velocity 192.99 

Ambient Static Pressure 2.85 Fan/LPC Inlet Static Pressure 4.17 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 474.82 

Additional Water at LPC Exit 0.0000145 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.780 39000.0 36.00 252.16 617.4 1.1455 707.23 8.5613 789.49 9.518 0.736 10.000 1759.2 1664.4 1158.2

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 252.16 4.267 477.92 -16.44 0.0000 833.70 2.854 425.97 2543.5 0.7800 1.40068 0.0000851 252.14 0.021 0.0001

FS1 Inlet.Fl_O 252.16 4.267 477.92 -16.44 0.0000 833.70 3.892 465.50 4168.2 0.3649 1.40068 0.0000851 252.14 0.021 0.0001

FS12 Splitter.Fl_02 225.79 4.265 477.92 -16.44 0.0000 746.88 3.839 463.78 3531.8 0.3902 1.40068 0.0000851 225.77 0.019 0.0001

FS2 Splitter.Fl_01 26.37 4.265 477.92 -16.44 0.0000 87.24 4.169 474.82 830.5 0.1806 1.40068 0.0000851 26.37 0.002 0.0001

FS14 Fan.Fl_O 225.79 4.817 496.63 -11.96 0.0000 674.07 4.042 472.33 2606.7 0.5067 1.40049 0.0000851 225.77 0.019 0.0001

FS23 LPC.Fl_O 26.37 6.654 555.02 2.05 0.0000 60.25 6.357 547.83 412.6 0.2561 1.39968 0.0000851 26.37 0.002 0.0001

FS24 VaporIN.Fl_O 26.37 6.654 555.07 1.98 0.0000 60.26 6.357 547.89 412.6 0.2561 1.39967 0.0000996 26.37 0.003 0.0001

FS25 Bleed2.Fl_O 23.74 6.654 555.07 1.98 0.0000 54.23 6.416 549.33 412.6 0.2287 1.39967 0.0000996 23.73 0.002 0.0001

FS3 HPC.Fl_O 22.58 40.610 1006.19 111.88 0.0000 11.38 35.727 971.22 49.7 0.4343 1.38033 0.0000996 22.58 0.002 0.0001

FS36 Bleed3.Fl_O 17.50 40.610 1006.19 111.88 0.0000 8.82 37.808 986.54 49.3 0.3233 1.38033 0.0000996 17.50 0.002 0.0001

FS4 Burner.Fl_O 17.70 39.675 1759.21 98.98 0.0112 12.07 37.468 1734.38 74.6 0.2944 1.32947 0.0000996 17.50 0.002 0.0138

FS45 HPT.Fl_O 23.65 9.522 1162.39 -7.41 0.0084 54.65 8.626 1132.04 265.4 0.3829 1.36457 0.0000996 23.46 0.002 0.0103

FS49 LPT.Fl_O 23.93 3.261 910.13 -69.34 0.0083 142.85 3.070 895.08 860.2 0.2970 1.38054 0.0000996 23.73 0.002 0.0102

FS5 TEGV.Fl_O 23.93 3.261 910.20 -69.34 0.0083 142.86 3.070 895.15 860.2 0.2970 1.38054 0.0000996 23.73 0.002 0.0102

FS8 Core_Nozz.Fl_O 23.93 3.261 910.27 -69.34 0.0083 142.86 2.854 877.34 613.4 0.4435 1.38053 0.0000996 23.73 0.002 0.0102

FS17 FanDuctLkg.Fl_O 225.79 4.817 496.63 -11.96 0.0000 674.07 4.042 472.33 2606.7 0.5067 1.40049 0.0000851 225.77 0.019 0.0001

FS171 Bleed15.Fl_O 228.42 4.817 497.30 -11.80 0.0000 682.41 3.908 468.44 2481.9 0.5546 1.40048 0.0000852 228.40 0.019 0.0001

FS172 FanDuct.Fl_O 228.42 4.817 497.30 -11.80 0.0000 682.41 3.908 468.44 2481.9 0.5546 1.40048 0.0000852 228.40 0.019 0.0001

FS173 Byp_Nozz.Fl_O 228.42 4.817 497.30 -11.80 0.0000 682.41 2.854 428.14 2006.9 0.8978 1.40048 0.0000852 228.40 0.019 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 746.88 1.129 0.9055 2568.019 1.0391 0.9071 -1432.4 1611.24 54.83

LPC 87.24 1.560 0.8406 2568.019 1.1613 0.8503 -690.1 6.97 3.73

HPC 54.23 6.103 0.8187 8965.376 1.8127 0.8573 -3601.3 61.35 58.03

HPT 12.07 4.167 0.8772 221.125 1.3648 0.8551 3601.3 

LPT 54.65 2.920 0.8556 72.303 1.2754 0.8360 2122.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 867.80 1.127 0.9073 2543.533 0.0414 0.8607 1.0235 0.9980 0.9905

LPC 73.90 1.522 0.7799 0.678 0.0000 1.1805 1.0736 1.0778 0.0003

HPC 49.32 5.863 0.8271 8726.365 10.9747 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.079 0.8771 1.329 4.0790 12.6299 0.9723 1.0000 0.0003

LPT 0.84 2.444 0.8620 0.813 2.4438 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–107
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2543.46 6187.5 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8735 782.68 56.93 9.522

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2777 782.68 56.93 3.261

TEGV 0.0000 0.2970 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.07 51.44 14.124

FanDuct 0.0000 0.5546 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 899.55 85.51 27.707

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.07 51.44 14.124

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 1006.19 111.88 40.610

Splitter 8.5613 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 760.07 51.44 14.124

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9274.6 2039.4 3601.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.6373 555.07 1.98 6.654

LP_Shaft 2465.1 4522.2 2122.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.7102 1006.19 111.88 39.675

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3715 1006.19 111.88 22.428

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 1006.19 111.88 40.610

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 1006.19 111.88 40.610

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 1006.19 111.88 40.610

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 496.63 -11.96 4.817

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1759.16 0.9995 0.0230 0.19645 0.01122 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.143 0.9801 1.0000 0.9800 613.40 0.443 627.1 466.5

Byp_Nozz 1.688 0.9800 1.0000 0.9800 2006.86 0.898 892.8 6338.4

NASA/TM—2013-218094 N–108
************************************************************************************************************************************ 

Date:07/05/13 Time:10:02:47 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.90 Stator 1 exit: 484.18 Stator 2 inlet: 493.31 Stator 2 exit: 497.96 

 Stator 3 inlet: 507.40 Stator 3 exit: 511.61 Stator 4 inlet: 520.43 Stator 4 exit: 524.01 

 Stator 5 inlet: 531.25 Stator 5 exit: 534.37 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.46 

Fan Bypass Relative Humidity 1.80 

LPC Inlet Relative Humidity 1.64 

LPC Exit Relative Humidity 0.18 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 738.88 Fan/LPC Inlet Flow Velocity 186.04 

Ambient Static Pressure 2.95 Fan/LPC Inlet Static Pressure 4.11 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 468.59 

Additional Water at LPC Exit 0.0000133 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.730 38334.0 36.00 245.31 606.9 1.1102 673.74 8.6582 738.88 9.232 0.764 10.000 1731.7 1637.5 1141.4

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 245.31 4.201 471.48 -17.97 0.0000 818.12 2.947 425.97 2560.6 0.7300 1.40073 0.0000824 245.29 0.020 0.0001

FS1 Inlet.Fl_O 245.31 4.201 471.48 -17.97 0.0000 818.12 3.847 459.74 4168.2 0.3569 1.40073 0.0000824 245.29 0.020 0.0001

FS12 Splitter.Fl_02 219.91 4.199 471.48 -17.97 0.0000 733.78 3.797 458.09 3531.8 0.3819 1.40073 0.0000824 219.89 0.018 0.0001

FS2 Splitter.Fl_01 25.40 4.199 471.48 -17.97 0.0000 84.75 4.110 468.59 830.5 0.1753 1.40073 0.0000824 25.40 0.002 0.0001

FS14 Fan.Fl_O 219.91 4.711 488.91 -13.79 0.0000 666.03 3.976 465.74 2606.7 0.4982 1.40058 0.0000824 219.89 0.018 0.0001

FS23 LPC.Fl_O 25.40 6.414 543.66 -0.66 0.0000 59.58 6.135 536.79 412.6 0.2530 1.39986 0.0000824 25.40 0.002 0.0001

FS24 VaporIN.Fl_O 25.40 6.414 543.71 -0.72 0.0000 59.58 6.135 536.84 412.6 0.2530 1.39985 0.0000957 25.40 0.002 0.0001

FS25 Bleed2.Fl_O 22.86 6.414 543.71 -0.72 0.0000 53.62 6.190 538.22 412.6 0.2260 1.39985 0.0000957 22.86 0.002 0.0001

FS3 HPC.Fl_O 21.75 38.786 983.85 106.36 0.0000 11.35 34.154 949.83 49.7 0.4325 1.38170 0.0000957 21.75 0.002 0.0001

FS36 Bleed3.Fl_O 16.86 38.786 983.85 106.36 0.0000 8.80 36.126 964.72 49.3 0.3221 1.38170 0.0000957 16.86 0.002 0.0001

FS4 Burner.Fl_O 17.04 37.892 1731.72 93.65 0.0111 12.08 35.783 1707.18 74.6 0.2944 1.33081 0.0000957 16.86 0.002 0.0136

FS45 HPT.Fl_O 22.78 9.210 1145.62 -9.98 0.0083 54.02 8.365 1116.44 265.4 0.3774 1.36571 0.0000957 22.59 0.002 0.0102

FS49 LPT.Fl_O 23.05 3.311 907.82 -68.20 0.0082 135.33 3.138 894.49 860.2 0.2797 1.38074 0.0000957 22.86 0.002 0.0101

FS5 TEGV.Fl_O 23.05 3.311 907.90 -68.20 0.0082 135.33 3.138 894.56 860.2 0.2797 1.38073 0.0000957 22.86 0.002 0.0101

FS8 Core_Nozz.Fl_O 23.05 3.311 907.97 -68.20 0.0082 135.34 2.947 879.20 613.4 0.4141 1.38073 0.0000957 22.86 0.002 0.0101

FS17 FanDuctLkg.Fl_O 219.91 4.711 488.91 -13.79 0.0000 666.03 3.976 465.74 2606.7 0.4982 1.40058 0.0000824 219.89 0.018 0.0001

FS171 Bleed15.Fl_O 222.45 4.711 489.53 -13.64 0.0000 674.15 3.851 462.10 2481.9 0.5444 1.40057 0.0000825 222.43 0.018 0.0001

FS172 FanDuct.Fl_O 222.45 4.711 489.53 -13.64 0.0000 674.15 3.851 462.10 2481.9 0.5444 1.40057 0.0000825 222.43 0.018 0.0001

FS173 Byp_Nozz.Fl_O 222.45 4.711 489.53 -13.64 0.0000 674.15 2.947 428.03 2006.9 0.8467 1.40057 0.0000825 222.43 0.018 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 733.78 1.122 0.9047 2504.141 1.0370 0.9062 -1300.1 2192.51 54.69

LPC 84.75 1.527 0.8409 2504.141 1.1531 0.8501 -622.2 6.78 3.35

HPC 53.62 6.047 0.8179 8945.792 1.8095 0.8566 -3379.3 61.27 57.90 

HPT 12.08 4.114 0.8759 220.099 1.3615 0.8539 3379.3 

LPT 54.02 2.781 0.8500 70.538 1.2600 0.8307 1922.3 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 852.58 1.119 0.9065 2480.264 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 71.13 1.493 0.7769 0.661 0.0000 1.1914 1.0692 1.0824 0.0003

HPC 48.77 5.809 0.8263 8707.303 10.9865 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.028 0.8759 1.323 4.0281 12.6299 0.9723 1.0000 0.0003

LPT 0.83 2.340 0.8563 0.793 2.3398 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–109
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2560.58 5633.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8412 765.65 52.82 9.210

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2675 765.65 52.82 3.311

TEGV 0.0000 0.2797 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.59 47.46 13.536

FanDuct 0.0000 0.5444 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 879.71 80.66 26.485

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.59 47.46 13.536

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 983.85 106.36 38.786

Splitter 8.6582 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 743.59 47.46 13.536

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9159.2 1937.8 3379.3 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5400 543.71 -0.72 6.414

LP_Shaft 2387.5 4228.7 1922.3 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6101 983.85 106.36 37.892

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.2839 983.85 106.36 21.486

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 983.85 106.36 38.786

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 983.85 106.36 38.786

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 983.85 106.36 38.786

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 488.91 -13.79 4.711

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1731.66 0.9995 0.0230 0.18715 0.01110 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.124 0.9801 1.0000 0.9800 613.40 0.414 586.1 419.8

Byp_Nozz 1.599 0.9800 1.0000 0.9800 2006.86 0.847 841.9 5820.6

NASA/TM—2013-218094 N–110
************************************************************************************************************************************ 

Date:07/05/13 Time:10:03:02 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 474.82 Stator 1 exit: 481.90 Stator 2 inlet: 490.79 Stator 2 exit: 495.33 

 Stator 3 inlet: 504.50 Stator 3 exit: 508.60 Stator 4 inlet: 517.19 Stator 4 exit: 520.66 

 Stator 5 inlet: 527.70 Stator 5 exit: 530.72 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 2.63 

Fan Bypass Relative Humidity 1.95 

LPC Inlet Relative Humidity 1.76 

LPC Exit Relative Humidity 0.19 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 722.68 Fan/LPC Inlet Flow Velocity 183.20 

Ambient Static Pressure 3.09 Fan/LPC Inlet Static Pressure 4.25 

Ambient Static Temperature 425.97 Fan/LPC Inlet Static Temperature 466.71 

Additional Water at LPC Exit 0.0000124 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.714 37357.0 36.00 251.85 620.0 1.1044 684.74 8.7044 722.68 9.102 0.772 10.000 1720.8 1627.0 1134.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 251.85 4.339 469.50 -18.42 0.0000 811.52 3.088 425.97 2564.4 0.7140 1.40075 0.0000786 251.83 0.020 0.0001

FS1 Inlet.Fl_O 251.85 4.339 469.50 -18.42 0.0000 811.52 3.980 458.03 4168.2 0.3535 1.40075 0.0000786 251.83 0.020 0.0001

FS12 Splitter.Fl_02 225.90 4.337 469.50 -18.42 0.0000 728.26 3.929 456.41 3531.8 0.3784 1.40075 0.0000786 225.88 0.018 0.0001

FS2 Splitter.Fl_01 25.95 4.337 469.50 -18.42 0.0000 83.67 4.247 466.71 830.5 0.1729 1.40075 0.0000786 25.95 0.002 0.0001

FS14 Fan.Fl_O 225.90 4.852 486.44 -14.36 0.0000 662.58 4.105 463.71 2606.7 0.4946 1.40060 0.0000786 225.88 0.018 0.0001

FS23 LPC.Fl_O 25.95 6.568 539.83 -1.56 0.0000 59.24 6.285 533.09 412.6 0.2514 1.39992 0.0000786 25.95 0.002 0.0001

FS24 VaporIN.Fl_O 25.95 6.568 539.88 -1.62 0.0000 59.25 6.285 533.13 412.6 0.2515 1.39991 0.0000910 25.95 0.002 0.0001

FS25 Bleed2.Fl_O 23.36 6.568 539.88 -1.62 0.0000 53.32 6.341 534.48 412.6 0.2246 1.39991 0.0000910 23.36 0.002 0.0001

FS3 HPC.Fl_O 22.22 39.498 975.76 104.37 0.0000 11.34 34.790 942.05 49.7 0.4320 1.38219 0.0000910 22.22 0.002 0.0001

FS36 Bleed3.Fl_O 17.22 39.498 975.76 104.37 0.0000 8.79 36.794 956.80 49.3 0.3217 1.38219 0.0000910 17.22 0.002 0.0001

FS4 Burner.Fl_O 17.41 38.588 1720.81 91.75 0.0110 12.08 36.439 1696.40 74.6 0.2943 1.33136 0.0000910 17.22 0.002 0.0136

FS45 HPT.Fl_O 23.27 9.422 1139.03 -10.81 0.0082 53.79 8.567 1110.28 265.4 0.3755 1.36616 0.0000910 23.08 0.002 0.0102

FS49 LPT.Fl_O 23.55 3.451 906.72 -67.63 0.0081 132.59 3.278 893.97 860.2 0.2735 1.38083 0.0000910 23.36 0.002 0.0101

FS5 TEGV.Fl_O 23.55 3.451 906.79 -67.63 0.0081 132.59 3.278 894.04 860.2 0.2735 1.38082 0.0000910 23.36 0.002 0.0101

FS8 Core_Nozz.Fl_O 23.55 3.451 906.87 -67.63 0.0081 132.60 3.088 879.50 613.4 0.4037 1.38082 0.0000910 23.36 0.002 0.0101

FS17 FanDuctLkg.Fl_O 225.90 4.852 486.44 -14.36 0.0000 662.58 4.105 463.71 2606.7 0.4946 1.40060 0.0000786 225.88 0.018 0.0001

FS171 Bleed15.Fl_O 228.49 4.852 487.05 -14.22 0.0000 670.61 3.978 460.16 2481.9 0.5401 1.40060 0.0000788 228.47 0.018 0.0001

FS172 FanDuct.Fl_O 228.49 4.852 487.05 -14.22 0.0000 670.61 3.978 460.16 2481.9 0.5401 1.40060 0.0000788 228.47 0.018 0.0001

FS173 Byp_Nozz.Fl_O 228.49 4.852 487.05 -14.22 0.0000 670.61 3.088 427.99 2006.9 0.8297 1.40060 0.0000788 228.47 0.018 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 728.26 1.119 0.9043 2477.354 1.0361 0.9058 -1297.7 2587.07 54.62

LPC 83.67 1.514 0.8409 2477.354 1.1498 0.8499 -619.3 6.69 3.27

HPC 53.32 6.014 0.8173 8935.941 1.8074 0.8561 -3417.7 61.36 57.96

HPT 12.08 4.095 0.8753 219.774 1.3603 0.8532 3417.7 

LPT 53.79 2.730 0.8478 69.838 1.2542 0.8286 1916.9 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 846.16 1.116 0.9061 2453.732 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 69.97 1.481 0.7756 0.654 0.0000 1.1956 1.0683 1.0841 0.0003

HPC 48.50 5.778 0.8258 8697.714 10.9846 1.0995 1.0494 0.9898 0.9733

HPT 0.96 4.010 0.8753 1.321 4.0096 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.302 0.8541 0.786 2.3015 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–111
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2564.42 5656.9 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.8595 759.62 51.38 9.422

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2733 759.62 51.38 3.451

TEGV 0.0000 0.2735 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 737.78 46.08 13.812

FanDuct 0.0000 0.5401 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 872.59 78.94 26.984

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 737.78 46.08 13.812

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 975.76 104.37 39.498

Splitter 8.7044 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 737.78 46.08 13.812

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9116.8 1968.9 3417.7 WB17Y Bleed> 0.1000 1.0000 1.0000 2.5952 539.88 -1.62 6.568

LP_Shaft 2357.0 4271.5 1916.9 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.6669 975.76 104.37 38.588

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.3336 975.76 104.37 21.905

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 975.76 104.37 39.498

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 975.76 104.37 39.498

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 975.76 104.37 39.498

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 486.44 -14.36 4.852

 WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 486.44 -14.36 4.852

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 486.44 -14.36 4.852

 WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 486.44 -14.36 4.852

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1720.76 0.9995 0.0230 0.19021 0.01104 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.117 0.9801 1.0000 0.9800 613.40 0.404 571.6 418.3

Byp_Nozz 1.571 0.9800 1.0000 0.9800 2006.86 0.830 825.0 5858.7

NASA/TM—2013-218094 N–112
************************************************************************************************************************************ 

Date:07/05/13 Time:10:03:18 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 11/ 25/ 1/ 9 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 476.22 Stator 1 exit: 482.85 Stator 2 inlet: 491.16 Stator 2 exit: 495.38 

 Stator 3 inlet: 503.94 Stator 3 exit: 507.74 Stator 4 inlet: 515.74 Stator 4 exit: 518.95 

 Stator 5 inlet: 525.50 Stator 5 exit: 528.27 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 3.24 

Fan Bypass Relative Humidity 2.48 

LPC Inlet Relative Humidity 2.22 

LPC Exit Relative Humidity 0.28 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 682.24 Fan/LPC Inlet Flow Velocity 176.64 

Ambient Static Pressure 3.58 Fan/LPC Inlet Static Pressure 4.74 

Ambient Static Temperature 432.42 Fan/LPC Inlet Static Temperature 468.61 

Additional Water at LPC Exit 0.0000139 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.669 34281.0 36.00 272.65 666.7 1.0955 730.36 8.8119 682.24 8.726 0.795 10.000 1710.2 1616.6 1130.0

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 272.65 4.831 471.21 -18.12 0.0000 790.56 3.578 432.42 2576.9 0.6690 1.40074 0.0000968 272.62 0.026 0.0001

FS1 Inlet.Fl_O 272.65 4.831 471.21 -18.12 0.0000 790.56 4.453 460.37 4168.2 0.3429 1.40074 0.0000968 272.62 0.026 0.0001

FS12 Splitter.Fl_02 244.86 4.829 471.21 -18.12 0.0000 710.34 4.399 458.81 3531.8 0.3673 1.40074 0.0000968 244.84 0.024 0.0001

FS2 Splitter.Fl_01 27.79 4.829 471.21 -18.12 0.0000 80.61 4.736 468.61 830.5 0.1664 1.40074 0.0000968 27.79 0.003 0.0001

FS14 Fan.Fl_O 244.86 5.360 487.02 -14.33 0.0000 650.61 4.570 465.32 2606.7 0.4824 1.40059 0.0000968 244.84 0.024 0.0001

FS23 LPC.Fl_O 27.79 7.120 536.97 -2.35 0.0000 58.36 6.823 530.48 412.6 0.2474 1.39996 0.0000968 27.79 0.003 0.0001

FS24 VaporIN.Fl_O 27.79 7.120 537.03 -2.41 0.0000 58.36 6.823 530.53 412.6 0.2474 1.39996 0.0001107 27.79 0.003 0.0001

FS25 Bleed2.Fl_O 25.01 7.120 537.03 -2.41 0.0000 52.53 6.882 531.83 412.6 0.2210 1.39996 0.0001107 25.01 0.003 0.0001

FS3 HPC.Fl_O 23.80 42.157 966.86 102.06 0.0000 11.33 37.149 933.55 49.7 0.4311 1.38272 0.0001107 23.79 0.003 0.0001

FS36 Bleed3.Fl_O 18.44 42.157 966.86 102.06 0.0000 8.78 39.280 948.11 49.3 0.3212 1.38272 0.0001107 18.44 0.002 0.0001

FS4 Burner.Fl_O 18.64 41.186 1710.22 89.51 0.0110 12.08 38.892 1685.93 74.6 0.2943 1.33188 0.0001107 18.44 0.002 0.0135

FS45 HPT.Fl_O 24.92 10.173 1134.22 -11.56 0.0082 53.24 9.270 1106.26 265.4 0.3708 1.36649 0.0001107 24.71 0.003 0.0102

FS49 LPT.Fl_O 25.21 3.939 915.29 -65.03 0.0081 124.94 3.766 903.97 860.2 0.2564 1.38034 0.0001107 25.01 0.003 0.0100

FS5 TEGV.Fl_O 25.21 3.939 915.36 -65.03 0.0081 124.95 3.766 904.05 860.2 0.2564 1.38034 0.0001107 25.01 0.003 0.0100

FS8 Core_Nozz.Fl_O 25.21 3.939 915.43 -65.03 0.0081 124.95 3.578 891.44 613.4 0.3757 1.38033 0.0001107 25.01 0.003 0.0101

FS17 FanDuctLkg.Fl_O 244.86 5.360 487.02 -14.33 0.0000 650.61 4.570 465.32 2606.7 0.4824 1.40059 0.0000968 244.84 0.024 0.0001

FS171 Bleed15.Fl_O 247.64 5.360 487.58 -14.19 0.0000 658.37 4.439 462.01 2481.9 0.5256 1.40059 0.0000970 247.62 0.024 0.0001

FS172 FanDuct.Fl_O 247.64 5.360 487.58 -14.19 0.0000 658.37 4.439 462.01 2481.9 0.5256 1.40059 0.0000970 247.62 0.024 0.0001

FS173 Byp_Nozz.Fl_O 247.64 5.360 487.58 -14.19 0.0000 658.37 3.578 434.35 2006.9 0.7820 1.40059 0.0000970 247.62 0.024 0.0001

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 710.34 1.110 0.9031 2395.014 1.0335 0.9045 -1312.5 5854.87 54.21

LPC 80.61 1.475 0.8415 2395.014 1.1396 0.8500 -620.0 6.40 3.05

HPC 52.53 5.921 0.8158 8909.678 1.8004 0.8545 -3607.0 61.79 58.29

HPT 12.08 4.049 0.8746 219.224 1.3570 0.8526 3607.0 

LPT 53.24 2.582 0.8427 67.783 1.2370 0.8241 1932.5 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 825.35 1.107 0.9050 2372.178 0.0413 0.8607 1.0235 0.9980 0.9905

LPC 66.41 1.445 0.7718 0.633 0.0000 1.2139 1.0674 1.0903 0.0003

HPC 47.77 5.689 0.8242 8672.152 10.9687 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.964 0.8746 1.318 3.9641 12.6299 0.9723 1.0000 0.0003

LPT 0.82 2.190 0.8489 0.762 2.1901 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–113
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2576.93 5781.4 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9203 753.67 49.82 10.173

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.2926 753.67 49.82 3.939

TEGV 0.0000 0.2564 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.13 44.60 14.828

FanDuct 0.0000 0.5256 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 865.08 76.98 28.843

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.13 44.60 14.828

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 966.86 102.06 42.157

Splitter 8.8119 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 732.13 44.60 14.828

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9066.0 2089.6 3607.0 WB17Y Bleed> 0.1000 1.0000 1.0000 2.7788 537.03 -2.41 7.120

LP_Shaft 2282.8 4446.1 1932.5 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 2.8556 966.86 102.06 41.186

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.4987 966.86 102.06 23.446

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.86 102.06 42.157

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.86 102.06 42.157

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 966.86 102.06 42.157

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 487.02 -14.33 5.360

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1710.15 0.9995 0.0230 0.20288 0.01100 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.101 0.9801 1.0000 0.9800 613.40 0.376 535.4 419.6

Byp_Nozz 1.498 0.9800 1.0000 0.9800 2006.86 0.782 783.2 6028.6

NASA/TM—2013-218094 N–114
************************************************************************************************************************************ 

Date:07/05/13 Time:10:03:34 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 13/ 27/ 1/11 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 484.50 Stator 1 exit: 490.20 Stator 2 inlet: 497.24 Stator 2 exit: 500.63 

 Stator 3 inlet: 507.99 Stator 3 exit: 510.97 Stator 4 inlet: 517.89 Stator 4 exit: 520.35 

 Stator 5 inlet: 525.92 Stator 5 exit: 528.01 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 4.18 

Fan Bypass Relative Humidity 3.37 

LPC Inlet Relative Humidity 3.05 

LPC Exit Relative Humidity 0.57 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 630.80 Fan/LPC Inlet Flow Velocity 177.37 

Ambient Static Pressure 4.36 Fan/LPC Inlet Static Pressure 5.49 

Ambient Static Temperature 447.58 Fan/LPC Inlet Static Temperature 478.12 

Additional Water at LPC Exit 0.0000197 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.608 30029.0 36.00 298.11 709.6 1.1115 788.72 8.4102 630.80 8.108 0.827 10.000 1708.1 1614.2 1131.6

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 298.11 5.595 480.74 -16.28 0.0000 753.83 4.358 447.58 2589.5 0.6080 1.40064 0.0001750 298.05 0.052 0.0002

FS1 Inlet.Fl_O 298.11 5.595 480.74 -16.28 0.0000 753.83 5.201 470.80 4168.2 0.3247 1.40064 0.0001750 298.05 0.052 0.0002

FS12 Splitter.Fl_02 266.43 5.592 480.74 -16.28 0.0000 674.06 5.149 469.52 3531.8 0.3454 1.40064 0.0001750 266.38 0.047 0.0002

FS2 Splitter.Fl_01 31.68 5.592 480.74 -16.28 0.0000 80.15 5.486 478.12 830.5 0.1654 1.40064 0.0001750 31.67 0.006 0.0002

FS14 Fan.Fl_O 266.43 6.130 494.93 -12.88 0.0000 623.91 5.315 475.13 2606.7 0.4561 1.40050 0.0001750 266.38 0.047 0.0002

FS23 LPC.Fl_O 31.68 7.803 536.92 -2.81 0.0000 60.70 7.449 529.86 412.6 0.2582 1.39995 0.0001750 31.67 0.006 0.0002

FS24 VaporIN.Fl_O 31.68 7.803 536.98 -2.91 0.0000 60.71 7.449 529.91 412.6 0.2582 1.39995 0.0001947 31.67 0.006 0.0002

FS25 Bleed2.Fl_O 26.93 7.803 536.98 -2.91 0.0000 51.60 7.551 531.97 412.6 0.2169 1.39995 0.0001947 26.92 0.005 0.0002

FS3 HPC.Fl_O 25.62 45.364 962.26 100.44 0.0000 11.31 39.998 929.23 49.7 0.4301 1.38298 0.0001947 25.62 0.005 0.0002

FS36 Bleed3.Fl_O 19.86 45.364 962.26 100.44 0.0000 8.76 42.281 943.67 49.3 0.3205 1.38298 0.0001947 19.85 0.004 0.0002

FS4 Burner.Fl_O 20.08 44.319 1708.12 87.87 0.0110 12.08 41.850 1683.86 74.6 0.2943 1.33194 0.0001947 19.85 0.004 0.0136

FS45 HPT.Fl_O 26.83 11.108 1135.85 -12.08 0.0082 52.53 10.151 1108.71 265.4 0.3650 1.36636 0.0001947 26.61 0.005 0.0103

FS49 LPT.Fl_O 27.15 4.710 937.20 -60.49 0.0081 113.86 4.539 927.72 860.2 0.2322 1.37901 0.0001947 26.92 0.005 0.0102

FS5 TEGV.Fl_O 27.15 4.710 937.28 -60.49 0.0081 113.86 4.539 927.79 860.2 0.2322 1.37900 0.0001947 26.92 0.005 0.0102

FS8 Core_Nozz.Fl_O 27.15 4.710 937.35 -60.49 0.0081 113.87 4.358 917.55 613.4 0.3371 1.37900 0.0001947 26.92 0.005 0.0102

FS17 FanDuctLkg.Fl_O 266.43 6.130 494.93 -12.88 0.0000 623.91 5.315 475.13 2606.7 0.4561 1.40050 0.0001750 266.38 0.047 0.0002

FS171 Bleed15.Fl_O 271.18 6.130 495.67 -12.71 0.0000 635.51 5.168 472.05 2481.9 0.4998 1.40049 0.0001753 271.13 0.048 0.0002

FS172 FanDuct.Fl_O 271.18 6.130 495.67 -12.71 0.0000 635.51 5.168 472.05 2481.9 0.4998 1.40049 0.0001753 271.13 0.048 0.0002

FS173 Byp_Nozz.Fl_O 271.18 6.130 495.67 -12.71 0.0000 635.51 4.358 449.58 2006.9 0.7153 1.40049 0.0001753 271.13 0.048 0.0002

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 674.06 1.096 0.9014 2238.852 1.0295 0.9027 -1282.9 -8363.19 52.80

LPC 80.15 1.395 0.8549 2238.852 1.1169 0.8616 -604.0 5.98 2.60

HPC 51.60 5.814 0.8138 8879.345 1.7920 0.8527 -3842.0 62.28 58.66

HPT 12.08 3.990 0.8743 218.602 1.3526 0.8525 3842.0 

LPT 52.53 2.358 0.8336 63.955 1.2095 0.8162 1886.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 783.19 1.094 0.9032 2217.505 0.0416 0.8607 1.0235 0.9980 0.9905

LPC 59.97 1.378 0.7652 0.591 0.0000 1.3365 1.0452 1.1172 0.0003

HPC 46.93 5.587 0.8222 8642.628 10.9509 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.907 0.8743 1.314 3.9070 12.6299 0.9723 1.0000 0.0003

LPT 0.80 2.022 0.8398 0.719 2.0217 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–115
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2589.51 5844.6 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 0.9909 751.30 48.77 11.108

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3151 751.30 48.77 4.710

TEGV 0.0000 0.2322 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 729.99 43.60 16.066

FanDuct 0.0000 0.4998 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 861.54 75.64 31.091

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 729.99 43.60 16.066

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 962.26 100.44 45.364

Splitter 8.4102 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 729.99 43.60 16.066

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 9034.7 2233.5 3842.0 WB17Y Bleed> 0.1500 1.0000 1.0000 4.7519 536.98 -2.91 7.803

LP_Shaft 2155.4 4597.7 1886.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.0746 962.26 100.44 44.319

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.6903 962.26 100.44 25.322

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.26 100.44 45.364

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.26 100.44 45.364

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 962.26 100.44 45.364

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 494.93 -12.88 6.130

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 494.93 -12.88 6.130

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 494.93 -12.88 6.130

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 494.93 -12.88 6.130

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1708.06 0.9995 0.0230 0.21909 0.01104 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.081 0.9801 1.0000 0.9800 613.40 0.337 487.2 411.0

Byp_Nozz 1.407 0.9800 1.0000 0.9800 2006.86 0.715 728.9 6143.2

NASA/TM—2013-218094 N–116
************************************************************************************************************************************ 

Date:07/05/13 Time:10:04:05 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 23/ 51/ 2/20 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 492.28 Stator 1 exit: 496.44 Stator 2 inlet: 501.16 Stator 2 exit: 503.02 

 Stator 3 inlet: 508.27 Stator 3 exit: 509.71 Stator 4 inlet: 514.75 Stator 4 exit: 515.78 

 Stator 5 inlet: 519.46 Stator 5 exit: 520.21 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 5.01 

Fan Bypass Relative Humidity 4.21 

LPC Inlet Relative Humidity 4.03 

LPC Exit Relative Humidity 1.37 

HPC Relative Humidity 0.00 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 582.56 Fan/LPC Inlet Flow Velocity 195.59 

Ambient Static Pressure 5.30 Fan/LPC Inlet Static Pressure 6.37 

Ambient Static Temperature 463.14 Fan/LPC Inlet Static Temperature 488.23 

Additional Water at LPC Exit 0.0000233 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.552 25666.0 36.00 322.27 709.8 1.1734 832.84 7.1190 582.56 7.194 0.857 10.000 1712.9 1616.9 1139.7

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 322.27 6.516 491.41 -14.47 0.0000 707.46 5.297 463.14 2581.0 0.5520 1.40052 0.0003043 322.17 0.098 0.0003

FS1 Inlet.Fl_O 322.27 6.516 491.41 -14.47 0.0000 707.46 6.116 482.59 4168.2 0.3022 1.40052 0.0003043 322.17 0.098 0.0003

FS12 Splitter.Fl_02 282.57 6.513 491.41 -14.47 0.0000 620.64 6.082 481.88 3531.8 0.3143 1.40052 0.0003043 282.49 0.086 0.0003

FS2 Splitter.Fl_01 39.69 6.513 491.41 -14.47 0.0000 87.18 6.366 488.23 830.5 0.1805 1.40052 0.0003043 39.68 0.012 0.0003

FS14 Fan.Fl_O 282.57 7.039 503.65 -11.54 0.0000 581.38 6.246 486.72 2606.7 0.4167 1.40039 0.0003043 282.49 0.086 0.0003

FS23 LPC.Fl_O 39.69 8.180 531.59 -4.83 0.0000 72.19 7.644 521.39 412.6 0.3127 1.40001 0.0003043 39.68 0.012 0.0003

FS24 VaporIN.Fl_O 39.69 8.180 531.66 -4.95 0.0000 72.20 7.644 521.45 412.6 0.3128 1.40001 0.0003276 39.68 0.013 0.0003

FS25 Bleed2.Fl_O 27.79 8.180 531.66 -4.95 0.0000 50.54 7.927 526.91 412.6 0.2122 1.40001 0.0003276 27.78 0.009 0.0003

FS3 HPC.Fl_O 26.44 46.874 949.54 96.54 0.0000 11.22 41.433 917.55 49.7 0.4257 1.38371 0.0003276 26.43 0.009 0.0003

FS36 Bleed3.Fl_O 20.49 46.874 949.54 96.54 0.0000 8.69 43.743 931.50 49.3 0.3175 1.38371 0.0003276 20.48 0.007 0.0003

FS4 Burner.Fl_O 20.72 45.795 1712.91 83.72 0.0113 12.08 43.242 1688.59 74.6 0.2944 1.33152 0.0003276 20.48 0.007 0.0141

FS45 HPT.Fl_O 27.69 11.865 1144.17 -14.29 0.0084 50.94 10.911 1118.73 265.4 0.3522 1.36567 0.0003276 27.45 0.009 0.0106

FS49 LPT.Fl_O 28.02 5.615 969.12 -56.84 0.0083 100.23 5.459 961.64 860.2 0.2030 1.37693 0.0003276 27.78 0.009 0.0105

FS5 TEGV.Fl_O 28.02 5.615 969.19 -56.84 0.0083 100.24 5.459 961.71 860.2 0.2030 1.37692 0.0003276 27.78 0.009 0.0105

FS8 Core_Nozz.Fl_O 28.02 5.615 969.26 -56.84 0.0083 100.24 5.297 953.89 613.4 0.2922 1.37692 0.0003276 27.78 0.009 0.0105

FS17 FanDuctLkg.Fl_O 282.57 7.039 503.65 -11.54 0.0000 581.38 6.246 486.72 2606.7 0.4167 1.40039 0.0003043 282.49 0.086 0.0003

FS171 Bleed15.Fl_O 294.48 7.039 504.78 -11.27 0.0000 606.56 6.054 483.49 2481.9 0.4690 1.40037 0.0003053 294.39 0.090 0.0003

FS172 FanDuct.Fl_O 294.48 7.039 504.78 -11.27 0.0000 606.56 6.054 483.49 2481.9 0.4690 1.40037 0.0003053 294.39 0.090 0.0003

FS173 Byp_Nozz.Fl_O 294.48 7.039 504.78 -11.27 0.0000 606.56 5.297 465.36 2006.9 0.6503 1.40037 0.0003053 294.39 0.090 0.0003

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 620.64 1.081 0.9017 2025.350 1.0249 0.9027 -1172.9 -2596.18 50.01

LPC 87.18 1.256 0.8233 2025.350 1.0818 0.8289 -541.3 6.43 2.41

HPC 50.54 5.730 0.8121 8845.465 1.7860 0.8511 -3893.2 61.73 58.01

HPT 12.08 3.860 0.8752 216.383 1.3429 0.8541 3893.2 

LPT 50.94 2.113 0.8233 58.282 1.1777 0.8074 1714.2 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 721.12 1.079 0.9035 2006.039 0.0424 0.8607 1.0235 0.9980 0.9905

LPC 52.83 1.304 0.7603 0.535 0.0000 1.6504 0.8407 1.0829 0.0003

HPC 45.97 5.507 0.8205 8609.651 10.9984 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.780 0.8752 1.300 3.7803 12.6299 0.9723 1.0000 0.0003

LPT 0.78 1.837 0.8294 0.656 1.8372 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–117
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2580.98 5835.2 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0225 742.18 45.79 11.865

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3251 742.18 45.79 5.615

TEGV 0.0000 0.2030 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.24 40.72 16.693

FanDuct 0.0000 0.4690 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 850.52 72.18 32.170

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.24 40.72 16.693

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 949.54 96.54 46.874

Splitter 7.1190 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 721.24 40.72 16.693

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8955.5 2283.2 3893.2 WB17Y Bleed> 0.3000 1.0000 1.0000 11.9082 531.66 -4.95 8.180

LP_Shaft 1971.4 4566.9 1714.2 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.1726 949.54 96.54 45.795

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.7761 949.54 96.54 26.387

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.54 96.54 46.874

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.54 96.54 46.874

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 949.54 96.54 46.874

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 503.65 -11.54 7.039

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1712.85 0.9995 0.0230 0.23134 0.01129 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.060 0.9801 1.0000 0.9800 613.40 0.292 430.1 374.5

Byp_Nozz 1.329 0.9800 1.0000 0.9800 2006.86 0.650 674.2 6170.4

NASA/TM—2013-218094 N–118
************************************************************************************************************************************ 

Date:07/05/13 Time:10:04:28 Model: Turbofan Engine - COMDES ON converge = 1 CASE: 0 

Version:NPSS_1.6.5 - Rev: -> Gas Package: Janaf iter/pass/Jacb/Broy= 27/ 41/ 1/25 Run by: Philip C Jorgenson PC: 10 

Temperature Stator 1 inlet: 505.22 Stator 1 exit: 508.18 Stator 2 inlet: 510.96 Stator 2 exit: 511.75 

 Stator 3 inlet: 515.11 Stator 3 exit: 515.47 Stator 4 inlet: 518.74 Stator 4 exit: 518.80 

 Stator 5 inlet: 520.69 Stator 5 exit: 520.56 Unblocked Percent Blockage: 0.00 

 

Ambient Relative Humidity 10.00 

Fan Face Relative Humidity 6.01 

Fan Bypass Relative Humidity 5.19 

LPC Inlet Relative Humidity 5.20 

LPC Exit Relative Humidity 2.84 

HPC Relative Humidity 0.01 

Drop Diameter 0.0001000 Inlet Length 40.00 

Ambient Flow Velocity 528.20 Fan/LPC Inlet Flow Velocity 203.17 

Ambient Static Pressure 6.74 Fan/LPC Inlet Static Pressure 7.75 

Ambient Static Temperature 483.18 Fan/LPC Inlet Static Temperature 502.97 

Additional Water at LPC Exit 0.0000304 

 

 SUMMARY OUTPUT DATA 

 MN alt dTamb W Fn TSFC Wfuel BPR VTAS OPR EPR PowerSet T4 T41 T49 

0.490 20047.0 36.00 357.70 762.3 1.1971 912.54 6.3407 528.20 6.254 0.888 10.000 1736.5 1637.1 1165.8

 

 FLOW STATION DATA 

 W Pt Tt ht FAR Wc Ps Ts Aphy MN gamt WAR Wair WH2O H2O frac

FS0 Ambient.Fl_O 357.70 7.943 506.41 -12.46 0.0000 653.92 6.740 483.18 2590.9 0.4900 1.40031 0.0005787 357.49 0.207 0.0006

FS1 Inlet.Fl_O 357.70 7.943 506.41 -12.46 0.0000 653.92 7.531 498.75 4168.2 0.2770 1.40031 0.0005787 357.49 0.207 0.0006

FS12 Splitter.Fl_02 308.97 7.939 506.41 -12.46 0.0000 565.13 7.509 498.41 3531.8 0.2831 1.40031 0.0005787 308.79 0.179 0.0006

FS2 Splitter.Fl_01 48.73 7.939 506.41 -12.46 0.0000 89.13 7.752 502.97 830.5 0.1847 1.40031 0.0005787 48.70 0.028 0.0006

FS14 Fan.Fl_O 308.97 8.480 517.06 -9.90 0.0000 534.64 7.690 502.82 2606.7 0.3761 1.40018 0.0005787 308.79 0.179 0.0006

FS23 LPC.Fl_O 48.73 9.053 534.25 -5.78 0.0000 80.28 8.304 521.24 412.6 0.3534 1.39993 0.0005787 48.70 0.028 0.0006

FS24 VaporIN.Fl_O 48.73 9.053 534.33 -5.94 0.0000 80.29 8.304 521.30 412.6 0.3534 1.39993 0.0006090 48.70 0.030 0.0006

FS25 Bleed2.Fl_O 29.24 9.053 534.33 -5.94 0.0000 48.17 8.800 530.01 412.6 0.2018 1.39993 0.0006090 29.22 0.018 0.0006

FS3 HPC.Fl_O 27.82 49.677 943.46 93.44 0.0000 11.10 44.047 912.44 49.7 0.4202 1.38403 0.0006090 27.80 0.017 0.0006

FS36 Bleed3.Fl_O 21.56 49.677 943.46 93.44 0.0000 8.60 46.432 925.92 49.3 0.3138 1.38403 0.0006090 21.55 0.013 0.0006

FS4 Burner.Fl_O 21.81 48.533 1736.55 80.13 0.0118 12.09 45.826 1711.94 74.6 0.2947 1.33006 0.0006090 21.55 0.013 0.0149

FS45 HPT.Fl_O 29.15 13.281 1170.56 -15.61 0.0088 48.45 12.324 1147.41 265.4 0.3327 1.36370 0.0006090 28.88 0.018 0.0113

FS49 LPT.Fl_O 29.49 7.031 1017.45 -52.74 0.0087 86.34 6.886 1011.73 860.2 0.1740 1.37363 0.0006090 29.22 0.018 0.0112

FS5 TEGV.Fl_O 29.49 7.031 1017.52 -52.73 0.0087 86.34 6.886 1011.80 860.2 0.1740 1.37362 0.0006090 29.22 0.018 0.0112

FS8 Core_Nozz.Fl_O 29.49 7.031 1017.59 -52.73 0.0087 86.34 6.740 1005.97 613.4 0.2485 1.37362 0.0006090 29.22 0.018 0.0112

FS17 FanDuctLkg.Fl_O 308.97 8.480 517.06 -9.90 0.0000 534.64 7.690 502.82 2606.7 0.3761 1.40018 0.0005787 308.79 0.179 0.0006

FS171 Bleed15.Fl_O 328.46 8.480 518.08 -9.67 0.0000 568.93 7.461 499.47 2481.9 0.4314 1.40016 0.0005805 328.27 0.191 0.0006

FS172 FanDuct.Fl_O 328.46 8.480 518.08 -9.67 0.0000 568.93 7.461 499.47 2481.9 0.4314 1.40016 0.0005805 328.27 0.191 0.0006

FS173 Byp_Nozz.Fl_O 328.46 8.480 518.08 -9.67 0.0000 568.93 6.740 485.17 2006.9 0.5821 1.40016 0.0005805 328.27 0.191 0.0006

TURBOMACHINERY PERFORMANCE DATA 

 Wc PR eff Nc TR efPoly pwr SMN SMW

Fan 565.13 1.068 0.9035 1815.354 1.0210 0.9044 -1117.1 -1833.16 46.56

LPC 89.13 1.140 0.6953 1815.354 1.0550 0.7009 -460.7 7.12 2.04

HPC 48.17 5.487 0.8076 8765.201 1.7657 0.8467 -4011.0 62.14 58.11

HPT 12.09 3.654 0.8765 213.490 1.3265 0.8566 4011.0 

LPT 48.45 1.889 0.8151 52.429 1.1472 0.8013 1577.8 

TURBOMACHINERY MAP DATA 

 WcMap PRmap effMap NcMap R/Parm s_WcDes s_PRdes s_effDes s_NcDes

Fan 656.62 1.067 0.9053 1798.045 0.0437 0.8607 1.0235 0.9980 0.9905

LPC 46.01 1.238 0.7547 0.479 0.0000 1.9370 0.5887 0.9213 0.0003

HPC 43.81 5.276 0.8160 8531.527 11.0083 1.0995 1.0494 0.9898 0.9733

HPT 0.96 3.581 0.8765 1.283 3.5806 12.6299 0.9723 1.0000 0.0003

LPT 0.74 1.669 0.8212 0.590 1.6687 65.2590 0.7521 0.9926 0.0005

NASA/TM—2013-218094 N–119
===INLETS==== eRam Afs Fram 

Inlet 1.0000 2590.89 5872.3 BLEEDS - interstg Wb/Win BldWk BldP W Tt ht Pt

 HPT_COOLC HPC.C> 0.0368 0.5000 0.2200 1.0759 740.40 43.75 13.281

====DUCTS==== dPnorm MN Aphy LPT_COOLA HPC.C> 0.0117 0.5000 0.4500 0.3421 740.40 43.75 7.031

TEGV 0.0000 0.1740 860.21 WB2X HPC.B> 0.0000 0.4500 0.2200 0.0000 719.90 38.78 17.990

FanDuct 0.0000 0.4314 2481.93 WB2Y HPC.B> 0.0000 0.7600 0.6200 0.0000 846.48 69.59 34.240

 WBA2X HPC.B> 0.0000 0.4500 0.2200 0.0000 719.90 38.78 17.990

==SPLITTERS== BPR dP/P 1 dP/P 2 WBLKG HPC.l> 0.0000 1.0000 1.0000 0.0000 943.46 93.44 49.677

Splitter 6.3407 0.0005 0.0005 WBW2X HPC.B> 0.0000 0.4500 0.2200 0.0000 719.90 38.78 17.990

 

===SHAFTS==== Nmech trq in pwr in BLEEDS - output Wb/Win hscale Pscale W Tt ht Pt

HP_Shaft 8896.5 2367.9 4011.0 WB17Y Bleed> 0.4000 1.0000 1.0000 19.4917 534.33 -5.94 9.053

LP_Shaft 1793.8 4619.9 1577.8 HPT_COOLA Bleed> 0.1142 1.0000 1.0000 3.3383 943.46 93.44 48.533

 HPT_COOLB Bleed> 0.0999 1.0000 1.0000 2.9211 943.46 93.44 28.369

WB3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.46 93.44 49.677

WBA3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.46 93.44 49.677

WBW3X Bleed> 0.0000 1.0000 1.0000 0.0000 943.46 93.44 49.677

WBFDLKG FanDu> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

WB15X Bleed> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

 WB15Y Bleed> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

WB17X Bleed> 0.0000 1.0000 1.0000 0.0000 517.06 -9.90 8.480

===BURNERS=== TtOut eff dPnorm Wfuel FAR 

Burner 1736.49 0.9995 0.0230 0.25348 0.01176 

 

===NOZZLES=== PR Cfg CdTh Cv Ath MNth Vact Fg

Core_Nozz 1.043 0.9801 1.0000 0.9800 613.40 0.249 375.3 344.0

Byp_Nozz 1.258 0.9800 1.0000 0.9800 2006.86 0.582 616.2 6290.6

NASA/TM—2013-218094 N–120
Appendix O: Compressor code analysis for the descent conditions 

 10μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.240 EfDer = 0.956 SH = 0.214612E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.744 2408.660 4.265 457.732 1.000 1.000 0.980

 W Kg/sec = 12.156 Wdry = 26.738 WH2O = 0.006 lbm/sec H2O = 0.085g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.597 2564.035 1.381 0.248 53.355 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64855.586 20982.740 3.280 831.557 253.504 619.754 2.445

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 187.18 -0.06 187.18 0.18 0.45 461.59

 MEAN 17.06 0.00 -0.02 187.18 -0.06 187.18 0.18 0.39

 HUB 12.51 0.00 -0.02 187.18 -0.06 187.18 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.66 50.47 16.19 433.63 472.37 4.17 454.91 448.87 8.21

 MEAN 62.44 47.20 15.24 358.60 404.57 4.17 454.91 448.87 8.21

 HUB 54.56 38.62 15.94 262.95 322.83 4.17 454.91 448.87 8.21

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 389.28 297.92 250.56 1051.54 0.37 7.29 6.52 16.04

 MEAN 18.04 394.34 301.76 253.85 1048.49 0.38 7.43 6.80 12.53

 HUB 15.00 427.66 340.75 258.42 1044.73 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 433.63 284.96 135.71 0.27 6147.47 0.92 0.88

 MEAN 379.11 265.38 77.35 0.25 5443.65 0.92 0.88 0.88 1.75

 HUB 315.29 259.67 25.46 0.25 5112.08 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 478.51 1.05 466.32 463.43 7.41

 MEAN 4.83 1.13 4.39 476.13 1.04 463.63 461.98 8.22

 HUB 4.80 1.12 4.28 475.01 1.04 460.31 461.41 9.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.93 28.44 24.20 4.24 0.93 0.57 1.80

 MEAN 49.93 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 52.82 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 406.0086 301.1738 272.2817 1048.1010 0.3874 -0.0366 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8427 4.3724 463.3001 462.3284 8.6491 47.8843 35.4000 -12.4843

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 270.2627 66.1145 262.0512 1056.4054 0.2558 0.5100 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8312 4.6189 470.6782 461.9947 554.9116 0.0348 0.6023

 

NASA/TM—2013-218094 O–1
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 269.1270 0.0000 269.1270 1056.4429 0.2547 0.4815 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5988 470.7275 462.1384 0.0000 0.0600 0.0839 0.4669

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8187 4.8083 1.1275 476.5477 18.8174 169.0224 1.3103

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 117078.594 0.623 176.943 280533.250 0.389583E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.778 EfDer = 0.960 SH = 0.595457E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.744 2408.660 4.808 476.548 1.000 1.000 0.980

 W Kg/sec = 12.156 Wdry = 26.728 WH2O = 0.016 lbm/sec H2O = 0.253g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.369 2512.930 1.381 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60548.652 20979.604 2.573 590.487 229.471 468.502 2.042

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 246.09 -0.08 246.09 0.23 0.47 450.64

 MEAN 18.08 0.00 -0.02 246.09 -0.08 246.09 0.23 0.43

 HUB 15.21 0.00 -0.02 246.09 -0.08 246.09 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.33 46.36 13.97 431.95 497.21 4.63 471.68 462.80 11.67

 MEAN 57.08 42.30 14.78 380.00 452.79 4.63 471.68 462.80 11.67

 HUB 52.42 37.84 14.58 319.71 403.52 4.63 471.68 462.80 11.67

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 358.12 247.20 259.13 1070.41 0.33 2.33 2.04 9.02

 MEAN 18.01 358.06 244.35 261.73 1067.99 0.34 2.40 2.13 7.35

 HUB 15.22 379.84 272.51 264.62 1065.61 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 429.22 316.67 182.02 0.30 5049.51 0.92 0.88

 MEAN 378.56 294.13 134.21 0.28 4402.19 0.92 0.88 0.88 1.70

 HUB 319.98 268.84 47.47 0.25 4149.65 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 493.59 1.04 483.29 473.25 8.09

 MEAN 5.30 1.10 4.91 491.41 1.03 481.11 472.04 8.74

 HUB 5.27 1.10 4.84 490.55 1.03 478.97 471.67 9.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.65 35.09 31.50 3.59 0.93 0.54 1.40

 MEAN 43.03 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 45.84 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 383.2183 245.0318 294.6450 1066.8044 0.3592 -0.1086 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3149 4.8671 480.0613 472.4241 9.1520 39.7475 30.6000 -9.1475

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 285.0870 60.4405 278.6065 1072.6350 0.2658 0.3611 2.4513

 

NASA/TM—2013-218094 O–2
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3089 5.0579 485.3262 472.0436 491.5697 0.0245 0.4582

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 295.4939 0.0000 295.4939 1072.0868 0.2756 0.3513 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0244 484.8412 472.1378 0.0000 0.0600 0.0636 0.2792

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8354 5.2930 1.1008 491.8503 15.3037 190.5325 1.4770

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 95325.922 0.517 144.068 254758.500 0.679828E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.786 EfDer = 0.975 SH = 0.798744E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.744 2408.660 5.293 491.850 1.000 1.000 0.980

 W Kg/sec = 12.156 Wdry = 26.722 WH2O = 0.021 lbm/sec H2O = 0.362g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.327 2473.530 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56775.223 20977.928 2.575 545.479 211.811 424.468 2.004

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.80 -0.09 249.80 0.23 0.46 433.21

 MEAN 17.74 0.00 -0.02 249.80 -0.09 249.80 0.23 0.42

 HUB 15.05 0.00 -0.02 249.80 -0.09 249.80 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.37 46.36 13.01 421.86 490.35 5.10 486.84 472.35 9.01

 MEAN 56.19 43.40 12.79 372.85 448.87 5.10 486.84 472.35 9.01

 HUB 51.71 38.84 12.87 316.34 403.15 5.10 486.84 472.35 9.01

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 350.15 231.17 262.99 1085.93 0.32 2.26 1.98 8.75

 MEAN 17.51 352.03 231.42 265.27 1083.86 0.32 2.34 2.07 6.78

 HUB 14.85 375.76 263.59 267.80 1081.84 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 416.40 321.67 185.22 0.30 4581.29 0.92 0.89 

 MEAN 367.98 298.36 136.56 0.28 4052.96 0.92 0.89 0.89 1.65

 HUB 312.14 272.17 48.55 0.25 3915.61 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.85 1.11 5.45 507.30 1.03 497.47 481.05 6.66

 MEAN 5.79 1.09 5.38 505.52 1.03 495.58 480.16 7.09

 HUB 5.77 1.09 5.31 505.06 1.03 493.73 480.04 7.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.32 35.16 31.50 3.66 0.93 0.51 1.40

 MEAN 41.10 27.24 23.50 3.74 0.94 0.49 1.62

 HUB 44.55 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 378.3560 232.9422 298.1463 1082.6388 0.3495 -0.1164 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7972 5.3338 494.4763 480.5306 7.4195 38.0006 31.5000 -6.5006

 

NASA/TM—2013-218094 O–3
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 293.4095 64.0053 286.3433 1087.6357 0.2698 0.3096 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7935 5.5116 499.0538 480.1858 451.3937 0.0190 0.4329

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 298.3670 0.0000 298.3670 1087.3688 0.2744 0.3360 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4895 498.8187 480.2715 0.0000 0.0600 0.0507 0.2570

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8559 5.7802 1.0920 505.9591 14.1098 195.9743 1.5192

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87958.031 0.507 132.932 253168.688 0.905756E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.193 EfDer = 0.985 SH = 0.105344E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.744 2408.660 5.780 505.959 1.000 1.000 0.980

 W Kg/sec = 12.156 Wdry = 26.716 WH2O = 0.028 lbm/sec H2O = 0.508g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.174 2438.798 1.380 0.249 53.382 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53450.363 20975.826 2.609 513.330 196.754 395.845 2.012

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 249.90 -0.09 249.90 0.23 0.44 409.89

 MEAN 16.97 0.00 -0.02 249.90 -0.09 249.90 0.23 0.40

 HUB 14.32 0.00 -0.02 249.90 -0.09 249.90 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.32 46.36 11.96 404.84 475.83 5.58 500.95 480.49 7.39

 MEAN 54.99 43.80 11.19 356.72 435.61 5.58 500.95 480.49 7.39

 HUB 50.31 37.84 12.47 301.00 391.28 5.58 500.95 480.49 7.39

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 337.14 211.79 262.31 1099.81 0.31 2.16 1.89 8.34

 MEAN 16.57 338.98 212.16 264.37 1097.95 0.31 2.24 1.97 6.35

 HUB 13.89 361.21 243.69 266.62 1096.12 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 396.85 321.02 185.05 0.29 4000.33 0.92 0.90

 MEAN 348.37 297.40 136.22 0.27 3517.77 0.92 0.90 0.90 1.61

 HUB 291.96 270.95 48.27 0.25 3386.12 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.30 1.09 5.91 519.44 1.03 510.33 487.58 5.80

 MEAN 6.24 1.08 5.84 517.81 1.02 508.60 486.82 6.12

 HUB 6.22 1.08 5.77 517.37 1.02 506.91 486.72 6.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.92 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.75 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.43 10.26 6.50 3.76 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 359.9688 213.3527 289.9279 1097.0830 0.3281 -0.0923 2.1803

 

NASA/TM—2013-218094 O–4
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2475 5.8046 507.8225 487.1318 6.3249 36.3487 32.4000 -3.9487

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 291.1619 65.2991 283.7451 1100.9513 0.2645 0.2723 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2456 5.9532 511.4133 486.8549 432.2457 0.0147 0.4113

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 288.8419 0.0000 288.8419 1101.0579 0.2623 0.3219 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9472 511.5213 486.9202 0.0000 0.0600 0.0419 0.2576

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8693 6.2344 1.0786 518.2069 12.2486 211.2859 1.6379

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76425.938 0.485 115.504 259031.453 0.118223E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.734 EfDer = 0.993 SH = 0.136107E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.744 2408.660 6.234 518.207 1.000 1.000 0.980

 W Kg/sec = 12.156 Wdry = 26.707 WH2O = 0.036 lbm/sec H2O = 0.693g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.028 2409.806 1.380 0.249 53.392 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 50615.797 20973.285 2.760 509.668 184.650 384.739 2.084

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 238.34 -0.08 238.34 0.22 0.41 385.25

 MEAN 15.91 0.00 -0.02 238.34 -0.08 238.34 0.22 0.37

 HUB 13.07 0.00 -0.02 238.34 -0.08 238.34 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.25 47.36 10.89 385.08 452.94 6.04 513.66 487.15 6.41

 MEAN 54.53 44.80 9.73 334.48 410.78 6.04 513.66 487.15 6.41

 HUB 49.06 38.84 10.22 274.73 363.77 6.04 513.66 487.15 6.41

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 320.12 198.98 250.77 1112.26 0.29 2.05 1.78 7.43

 MEAN 15.50 319.12 194.78 252.78 1110.34 0.29 2.13 1.86 5.75

 HUB 12.59 335.70 218.42 254.92 1108.44 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 377.09 307.58 178.11 0.28 3571.26 0.92 0.91

 MEAN 325.75 284.69 130.97 0.26 3019.99 0.92 0.91 0.91 1.60

 HUB 264.64 259.07 46.21 0.23 2751.03 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.08 6.35 530.23 1.02 522.02 493.15 5.26

 MEAN 6.65 1.07 6.28 528.37 1.02 520.22 492.32 5.55

 HUB 6.61 1.06 6.21 527.47 1.02 518.44 492.00 5.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.43 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.62 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.59 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

NASA/TM—2013-218094 O–5
 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 349.4442 198.3558 287.6913 1108.9216 0.3151 -0.1723 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6535 6.2170 518.9138 492.6297 5.8049 34.5853 33.0000 -1.5853

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.0095 67.1373 286.2414 1111.9659 0.2644 0.1545 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6515 6.3404 521.7697 492.3937 410.5396 0.0253 0.3869

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.0030 0.0000 286.0030 1112.3533 0.2571 0.3102 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3524 522.1417 492.4530 0.0000 0.0600 0.0375 0.1863

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8786 6.6469 1.0662 528.6895 10.4832 230.8788 1.7898

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65480.563 0.460 98.962 271607.625 0.151203E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1550 Tt4 = 528.6895 T1 = 457.7317

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 442269.06 668.4084 86.5971 1.5586 0.8388 15.2402 1.1550 37.3740

NASA/TM—2013-218094 O–6
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.330 EfDer = 0.956 SH = 0.191796E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.782 2333.126 4.199 451.558 1.000 1.000 0.980

 W Kg/sec = 11.719 Wdry = 25.777 WH2O = 0.005 lbm/sec H2O = 0.076g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.209 2500.551 1.381 0.248 53.355 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62582.313 20228.230 3.373 831.557 246.508 619.754 2.514

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 180.62 -0.06 180.62 0.18 0.44 450.16

 MEAN 17.06 0.00 -0.02 180.62 -0.06 180.62 0.18 0.38

 HUB 12.51 0.00 -0.02 180.62 -0.06 180.62 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.73 50.47 16.26 420.03 457.28 4.11 448.94 444.44 9.69

 MEAN 62.53 47.20 15.33 347.35 391.56 4.11 448.94 444.44 9.69

 HUB 54.66 38.62 16.04 254.71 312.30 4.11 448.94 444.44 9.69

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 377.02 288.81 242.35 1043.98 0.36 7.29 6.52 16.04

 MEAN 18.04 381.78 292.49 245.37 1041.11 0.37 7.43 6.80 12.53

 HUB 15.00 413.71 329.97 249.55 1037.56 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 420.03 275.60 131.23 0.26 5959.35 0.92 0.87

 MEAN 367.22 256.50 74.73 0.25 5276.36 0.92 0.87 0.87 1.75

 HUB 305.41 250.76 24.57 0.24 4950.36 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 471.07 1.04 459.64 458.77 8.66

 MEAN 4.73 1.13 4.32 468.83 1.04 457.11 457.32 9.58

 HUB 4.70 1.12 4.22 467.77 1.04 454.00 456.73 10.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.00 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 50.01 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.90 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 393.0114 291.9187 263.1376 1040.7445 0.3776 -0.0367 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7392 4.3004 456.8067 457.6585 10.0526 47.9683 35.4000 -12.5683

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 261.6801 64.0149 253.7293 1048.5807 0.2496 0.5108 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7287 4.5307 463.7181 457.3573 554.9116 0.0342 0.6026

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 260.5527 0.0000 260.5527 1048.6171 0.2485 0.4811 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5115 463.7655 457.4875 0.0000 0.0600 0.0844 0.4665

NASA/TM—2013-218094 O–7
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8177 4.7068 1.1209 469.2217 17.6647 168.6554 1.3074

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 109889.438 0.623 160.104 273014.438 0.336867E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.785 EfDer = 0.960 SH = 0.508275E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.782 2333.126 4.707 469.221 1.000 1.000 0.980

 W Kg/sec = 11.719 Wdry = 25.769 WH2O = 0.013 lbm/sec H2O = 0.215g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.584 2453.055 1.381 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58633.895 20225.719 2.633 590.487 224.230 468.502 2.089 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.31 -0.08 238.31 0.23 0.46 439.90

 MEAN 18.08 0.00 -0.02 238.31 -0.08 238.31 0.23 0.42

 HUB 15.21 0.00 -0.02 238.31 -0.08 238.31 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.34 46.36 13.98 418.41 481.58 4.54 464.66 458.08 13.41

 MEAN 57.09 42.30 14.79 368.08 438.56 4.54 464.66 458.08 13.41

 HUB 52.43 37.84 14.59 309.68 390.83 4.54 464.66 458.08 13.41

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 347.07 239.12 251.56 1061.80 0.33 2.33 2.04 9.02

 MEAN 18.01 347.02 236.50 253.95 1059.52 0.33 2.40 2.13 7.35

 HUB 15.22 368.10 263.92 256.61 1057.28 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.76 307.38 176.64 0.29 4884.46 0.92 0.88

 MEAN 366.69 285.38 130.19 0.27 4260.77 0.92 0.88 0.88 1.69

 HUB 309.95 260.71 46.03 0.25 4018.83 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.24 1.11 4.87 485.20 1.03 475.52 468.43 9.38

 MEAN 5.17 1.10 4.80 483.16 1.03 473.48 467.24 10.12

 HUB 5.14 1.09 4.73 482.37 1.03 471.48 466.86 10.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.55 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.96 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.80 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.3845 237.1601 285.7997 1058.3921 0.3509 -0.1088 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1781 4.7608 472.4966 467.6041 10.5873 39.6863 30.6000 -9.0863

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 276.9044 58.7057 270.6099 1063.8838 0.2603 0.3593 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1729 4.9380 477.4153 467.2632 491.5697 0.0238 0.4564

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 286.9464 0.0000 286.9464 1063.3647 0.2698 0.3495 0.5911

NASA/TM—2013-218094 O–8
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9066 476.9606 467.3498 0.0000 0.0600 0.0633 0.2771

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8354 5.1578 1.0958 483.5723 14.3518 190.6260 1.4777

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89366.453 0.517 130.203 248163.141 0.578376E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.707 EfDer = 0.976 SH = 0.677741E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.782 2333.126 5.158 483.572 1.000 1.000 0.980

 W Kg/sec = 11.719 Wdry = 25.764 WH2O = 0.017 lbm/sec H2O = 0.305g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.948 2416.382 1.381 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55158.109 20224.373 2.626 545.479 207.755 424.468 2.043

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 242.68 -0.08 242.68 0.23 0.45 423.20

 MEAN 17.74 0.00 -0.02 242.68 -0.08 242.68 0.23 0.41

 HUB 15.05 0.00 -0.02 242.68 -0.08 242.68 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.30 46.36 12.94 408.63 475.34 4.98 478.84 467.54 10.44

 MEAN 56.11 43.40 12.71 361.16 435.19 4.98 478.84 467.54 10.44

 HUB 51.63 38.84 12.79 306.42 390.95 4.98 478.84 467.54 10.44

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.59 223.05 256.07 1076.42 0.32 2.26 1.98 8.75

 MEAN 17.51 341.55 223.60 258.18 1074.48 0.32 2.34 2.07 6.78

 HUB 14.85 364.62 255.11 260.51 1072.58 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 403.34 313.17 180.29 0.29 4420.24 0.92 0.89

 MEAN 356.44 290.35 132.84 0.27 3916.01 0.92 0.89 0.89 1.64

 HUB 302.35 264.76 47.24 0.25 3789.61 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.67 1.10 5.30 498.02 1.03 488.76 476.16 7.79

 MEAN 5.61 1.09 5.24 496.37 1.03 487.01 475.28 8.27

 HUB 5.60 1.09 5.17 495.96 1.03 485.29 475.17 8.78

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.06 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.90 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.40 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 367.1684 225.0708 290.0961 1073.3124 0.3421 -0.1173 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6251 5.1932 485.9640 475.6424 8.6547 37.8061 31.5000 -6.3061

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 285.8308 62.3521 278.9471 1078.0068 0.2651 0.3050 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6219 5.3573 490.2264 475.3325 451.3937 0.0183 0.4290

 

NASA/TM—2013-218094 O–9
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 290.6150 0.0000 290.6150 1077.7537 0.2696 0.3324 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3368 490.0052 475.4128 0.0000 0.0600 0.0499 0.2525

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8568 5.6095 1.0876 496.7825 13.2111 196.6385 1.5243

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 82319.156 0.506 119.936 246917.047 0.767381E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.034 EfDer = 0.986 SH = 0.891603E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.782 2333.126 5.610 496.782 1.000 1.000 0.980

 W Kg/sec = 11.719 Wdry = 25.759 WH2O = 0.023 lbm/sec H2O = 0.425g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.120 2384.038 1.380 0.249 53.377 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52081.703 20222.672 2.651 513.330 193.646 395.845 2.044

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 243.50 -0.08 243.50 0.23 0.43 400.69

 MEAN 16.97 0.00 -0.02 243.50 -0.08 243.50 0.23 0.39

 HUB 14.32 0.00 -0.02 243.50 -0.08 243.50 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.17 46.36 11.81 392.14 461.66 5.42 492.03 475.61 8.65

 MEAN 54.83 43.80 11.03 345.53 422.78 5.42 492.03 475.61 8.65

 HUB 50.14 37.84 12.30 291.56 379.93 5.42 492.03 475.61 8.65

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.28 203.77 256.10 1089.49 0.30 2.16 1.89 8.34

 MEAN 16.57 329.25 204.55 258.00 1087.75 0.30 2.24 1.97 6.35

 HUB 13.89 351.00 235.72 260.07 1086.04 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.40 313.40 180.63 0.29 3848.80 0.92 0.90

 MEAN 337.45 290.22 132.90 0.27 3391.54 0.92 0.90 0.90 1.60

 HUB 282.81 264.30 47.08 0.24 3275.40 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.09 1.09 5.72 509.35 1.03 500.76 482.62 6.84

 MEAN 6.03 1.07 5.66 507.86 1.02 499.16 481.88 7.20

 HUB 6.02 1.07 5.60 507.48 1.02 497.60 481.79 7.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.51 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.41 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.19 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.7738 205.6961 282.8972 1086.9200 0.3218 -0.0933 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0409 5.6282 498.4197 482.1828 7.4403 36.0211 32.4000 -3.6211

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 284.3873 63.7798 277.1431 1090.5367 0.2608 0.2652 2.2705

 

NASA/TM—2013-218094 O–10
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0393 5.7641 501.7449 481.9337 432.2457 0.0142 0.4055

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 282.1004 0.0000 282.1004 1090.6412 0.2587 0.3162 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7587 501.8489 481.9960 0.0000 0.0600 0.0411 0.2509

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8705 6.0290 1.0748 508.2299 11.4481 212.6206 1.6482

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71389.609 0.483 104.012 252918.344 0.100019E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.502 EfDer = 0.994 SH = 0.115124E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.782 2333.126 6.029 508.230 1.000 1.000 0.980

 W Kg/sec = 11.719 Wdry = 25.752 WH2O = 0.030 lbm/sec H2O = 0.578g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.224 2357.036 1.380 0.249 53.386 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49449.102 20220.605 2.796 509.668 182.268 384.739 2.111

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 232.85 -0.08 232.85 0.21 0.40 376.81

 MEAN 15.91 0.00 -0.02 232.85 -0.08 232.85 0.21 0.37

 HUB 13.07 0.00 -0.02 232.85 -0.08 232.85 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.03 47.36 10.67 373.00 439.78 5.84 503.88 482.21 7.56

 MEAN 54.30 44.80 9.50 323.99 399.05 5.84 503.88 482.21 7.56

 HUB 48.82 38.84 9.98 266.11 353.66 5.84 503.88 482.21 7.56

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 310.98 190.99 245.42 1101.22 0.28 2.05 1.78 7.43

 MEAN 15.50 310.29 187.43 247.28 1099.42 0.28 2.13 1.86 5.75

 HUB 12.59 326.68 211.17 249.26 1097.65 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 365.26 301.01 174.28 0.27 3427.77 0.92 0.91

 MEAN 315.54 278.49 128.10 0.25 2906.05 0.92 0.91 0.91 1.58

 HUB 256.34 253.32 45.17 0.23 2659.63 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.48 1.07 6.13 519.41 1.02 511.67 488.13 6.24

 MEAN 6.41 1.06 6.07 517.71 1.02 510.00 487.31 6.57

 HUB 6.38 1.06 6.00 516.91 1.02 508.36 487.01 6.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.89 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.16 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.27 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 340.0004 190.8709 281.3691 1098.0603 0.3096 -0.1740 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4142 6.0073 508.7502 487.6142 6.8787 34.1516 33.0000 -1.1516

 

NASA/TM—2013-218094 O–11
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 287.7949 65.7182 280.1911 1100.8879 0.2614 0.1444 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4126 6.1191 511.3761 487.4025 410.5396 0.0246 0.3796

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 279.9675 0.0000 279.9675 1101.2639 0.2542 0.3026 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1304 511.7323 487.4581 0.0000 0.0600 0.0371 0.1764

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8794 6.4082 1.0629 518.0114 9.7821 232.9534 1.8058

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 61056.477 0.458 88.957 265466.188 0.127893E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1472 Tt4 = 518.0114 T1 = 451.5583

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 414021.16 603.2117 84.2089 1.5260 0.8394 15.3298 1.1472 37.3740

NASA/TM—2013-218094 O–12
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.368 EfDer = 0.955 SH = 0.175383E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.378 2304.370 4.337 449.669 1.000 1.000 0.980

 W Kg/sec = 11.990 Wdry = 26.373 WH2O = 0.005 lbm/sec H2O = 0.072g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.240 2474.914 1.381 0.248 53.354 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61710.008 20695.666 3.413 831.557 243.671 619.754 2.543

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 178.10 -0.06 178.10 0.17 0.44 445.55

 MEAN 17.06 0.00 -0.02 178.10 -0.06 178.10 0.17 0.38

 HUB 12.51 0.00 -0.02 178.10 -0.06 178.10 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.77 50.47 16.30 414.86 451.53 4.25 447.12 443.20 10.02

 MEAN 62.57 47.20 15.37 343.07 386.60 4.25 447.12 443.20 10.02

 HUB 54.71 38.62 16.09 251.57 308.28 4.25 447.12 443.20 10.02

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 372.34 285.35 239.20 1041.62 0.36 7.29 6.52 16.04

 MEAN 18.04 376.96 288.93 242.11 1038.81 0.36 7.43 6.80 12.53

 HUB 15.00 408.38 325.86 246.15 1035.35 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 414.86 272.01 129.51 0.26 5887.94 0.92 0.87

 MEAN 362.69 253.10 73.76 0.24 5212.21 0.92 0.87 0.87 1.75

 HUB 301.64 247.33 24.22 0.24 4888.73 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 468.71 1.04 457.56 457.47 8.94

 MEAN 4.87 1.12 4.46 466.52 1.04 455.10 456.01 9.88

 HUB 4.84 1.12 4.35 465.48 1.04 452.07 455.41 11.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.03 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 50.04 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.93 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 388.0224 288.3696 259.6234 1038.4562 0.3737 -0.0366 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8828 4.4396 454.8003 456.3411 10.3587 48.0028 35.4000 -12.6028

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 258.3804 63.2077 250.5298 1046.1115 0.2470 0.5112 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8723 4.6724 461.5367 456.0638 554.9116 0.0339 0.6027

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.2556 0.0000 257.2556 1046.1479 0.2459 0.4810 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6528 461.5833 456.1828 0.0000 0.0600 0.0846 0.4664

NASA/TM—2013-218094 O–13
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8173 4.8500 1.1183 466.9026 17.2349 168.5029 1.3062

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 107209.781 0.623 159.809 280117.344 0.304491E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.791 EfDer = 0.960 SH = 0.457444E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.378 2304.370 4.850 466.902 1.000 1.000 0.980

 W Kg/sec = 11.990 Wdry = 26.365 WH2O = 0.012 lbm/sec H2O = 0.201g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.851 2428.830 1.381 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57897.367 20693.375 2.659 590.487 222.078 468.502 2.110

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 235.32 -0.08 235.32 0.22 0.45 435.56

 MEAN 18.08 0.00 -0.02 235.32 -0.08 235.32 0.22 0.41

 HUB 15.21 0.00 -0.02 235.32 -0.08 235.32 0.22 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.35 46.36 13.99 413.25 475.62 4.68 462.45 456.73 13.77

 MEAN 57.09 42.30 14.79 363.54 433.12 4.68 462.45 456.73 13.77

 HUB 52.43 37.84 14.59 305.86 385.98 4.68 462.45 456.73 13.77

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 342.84 236.05 248.64 1059.02 0.32 2.33 2.04 9.02

 MEAN 18.01 342.79 233.51 250.96 1056.80 0.32 2.40 2.13 7.35

 HUB 15.22 363.62 260.66 253.53 1054.61 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.63 303.81 174.59 0.29 4821.77 0.92 0.88

 MEAN 362.17 282.01 128.66 0.27 4207.00 0.92 0.88 0.88 1.69

 HUB 306.13 257.57 45.46 0.24 3969.27 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.11 5.01 482.48 1.03 473.04 467.08 9.69

 MEAN 5.32 1.10 4.95 480.49 1.03 471.05 465.88 10.44

 HUB 5.29 1.09 4.88 479.73 1.03 469.10 465.50 11.23

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.51 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.94 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.79 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.8518 234.1671 282.3934 1055.7008 0.3475 -0.1089 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3256 4.9043 470.0909 466.2411 10.9158 39.6663 30.6000 -9.0663

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 273.7515 58.0373 267.5286 1061.0630 0.2580 0.3587 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3204 5.0829 474.8811 465.9273 491.5697 0.0235 0.4557

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 283.6528 0.0000 283.6528 1060.5558 0.2675 0.3488 0.5911

NASA/TM—2013-218094 O–14
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0512 474.4378 466.0071 0.0000 0.0600 0.0632 0.2763

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8354 5.3052 1.0938 480.8996 13.9981 190.6464 1.4779

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87150.813 0.517 129.908 254713.828 0.519962E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.679 EfDer = 0.976 SH = 0.608754E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.378 2304.370 5.305 480.899 1.000 1.000 0.980

 W Kg/sec = 11.990 Wdry = 26.361 WH2O = 0.016 lbm/sec H2O = 0.284g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.375 2393.222 1.381 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54534.988 20692.145 2.647 545.479 206.070 424.468 2.060

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 239.94 -0.08 239.94 0.23 0.44 419.15

 MEAN 17.74 0.00 -0.02 239.94 -0.08 239.94 0.23 0.40

 HUB 15.05 0.00 -0.02 239.94 -0.08 239.94 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.27 46.36 12.91 403.60 469.60 5.12 476.28 466.18 10.79

 MEAN 56.08 43.40 12.68 356.71 429.97 5.12 476.28 466.18 10.79

 HUB 51.60 38.84 12.76 302.65 386.29 5.12 476.28 466.18 10.79

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.57 219.98 253.40 1073.31 0.31 2.26 1.98 8.75

 MEAN 17.51 337.53 220.63 255.44 1071.42 0.32 2.34 2.07 6.78

 HUB 14.85 360.36 251.90 257.70 1069.57 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.37 309.90 178.39 0.29 4359.48 0.92 0.89

 MEAN 352.05 287.27 131.42 0.27 3863.87 0.92 0.89 0.89 1.64

 HUB 298.62 261.90 46.73 0.24 3741.91 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.83 1.10 5.45 494.98 1.03 485.94 474.81 8.08

 MEAN 5.76 1.09 5.39 493.38 1.03 484.23 473.93 8.57

 HUB 5.75 1.08 5.32 492.98 1.03 482.56 473.81 9.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.96 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 40.82 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.35 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 362.8775 222.0737 286.9901 1070.2742 0.3391 -0.1175 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7761 5.3400 483.2073 474.2818 8.9654 37.7328 31.5000 -6.2328

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 282.9053 61.7139 276.0921 1074.8530 0.2632 0.3033 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7729 5.5050 487.3528 473.9959 451.3937 0.0180 0.4275

 

NASA/TM—2013-218094 O–15
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 287.6229 0.0000 287.6229 1074.6051 0.2677 0.3310 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4843 487.1368 474.0705 0.0000 0.0600 0.0496 0.2508

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8571 5.7604 1.0858 493.7767 12.8780 196.8805 1.5262

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 80226.555 0.506 119.587 253557.313 0.688955E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.974 EfDer = 0.986 SH = 0.800359E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.378 2304.370 5.760 493.777 1.000 1.000 0.980

 W Kg/sec = 11.990 Wdry = 26.356 WH2O = 0.021 lbm/sec H2O = 0.394g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.675 2361.810 1.380 0.249 53.374 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51553.586 20690.590 2.669 513.330 192.334 395.845 2.058

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.03 -0.08 241.03 0.22 0.42 396.95

 MEAN 16.97 0.00 -0.02 241.03 -0.08 241.03 0.22 0.39

 HUB 14.32 0.00 -0.02 241.03 -0.08 241.03 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.11 46.36 11.75 387.31 456.25 5.57 489.12 474.26 8.97

 MEAN 54.77 43.80 10.97 341.27 417.87 5.57 489.12 474.26 8.97

 HUB 50.08 37.84 12.24 287.97 375.59 5.57 489.12 474.26 8.97

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.52 200.74 253.71 1086.07 0.30 2.16 1.89 8.34

 MEAN 16.57 325.53 201.66 255.54 1084.38 0.30 2.24 1.97 6.35

 HUB 13.89 347.09 232.68 257.55 1082.72 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 379.67 310.45 178.93 0.29 3791.58 0.92 0.90

 MEAN 333.29 287.45 131.63 0.27 3343.74 0.92 0.90 0.90 1.59

 HUB 279.32 261.74 46.64 0.24 3233.15 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.24 1.08 5.87 506.01 1.02 497.61 481.27 7.12

 MEAN 6.18 1.07 5.81 504.57 1.02 496.06 480.53 7.49

 HUB 6.17 1.07 5.75 504.21 1.02 494.54 480.44 7.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.35 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.28 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.10 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 345.8736 202.7965 280.1823 1083.5630 0.3192 -0.0936 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1943 5.7776 495.3322 480.8232 7.7438 35.8971 32.4000 -3.4971

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 281.7692 63.1926 274.5916 1087.0845 0.2592 0.2624 2.2705

 

NASA/TM—2013-218094 O–16
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1928 5.9140 498.5596 480.5932 432.2457 0.0139 0.4033

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 279.4955 0.0000 279.4955 1087.1882 0.2571 0.3141 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9085 498.6621 480.6514 0.0000 0.0600 0.0408 0.2483

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8709 6.1825 1.0733 504.9276 11.1516 213.1304 1.6522

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 69521.039 0.482 103.629 259834.391 0.897768E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.414 EfDer = 0.994 SH = 0.103351E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.378 2304.370 6.182 504.927 1.000 1.000 0.980

 W Kg/sec = 11.990 Wdry = 26.350 WH2O = 0.027 lbm/sec H2O = 0.536g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.879 2335.585 1.380 0.249 53.382 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48998.496 20688.689 2.812 509.668 181.245 384.739 2.123

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 230.73 -0.08 230.73 0.21 0.40 373.38

 MEAN 15.91 0.00 -0.02 230.73 -0.08 230.73 0.21 0.36

 HUB 13.07 0.00 -0.02 230.73 -0.08 230.73 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.95 47.36 10.59 368.40 434.76 5.99 500.66 480.85 7.89

 MEAN 54.21 44.80 9.41 320.00 394.57 5.99 500.66 480.85 7.89

 HUB 48.73 38.84 9.89 262.83 349.80 5.99 500.66 480.85 7.89

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 307.49 187.96 243.36 1097.53 0.28 2.05 1.78 7.43

 MEAN 15.50 306.92 184.66 245.15 1095.78 0.28 2.13 1.86 5.75

 HUB 12.59 323.21 208.37 247.07 1094.06 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 360.76 298.47 172.80 0.27 3373.45 0.92 0.91

 MEAN 311.65 276.09 126.99 0.25 2863.01 0.92 0.91 0.91 1.58

 HUB 253.18 251.10 44.81 0.23 2624.43 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.63 1.07 6.29 515.80 1.02 508.22 486.77 6.53

 MEAN 6.56 1.06 6.22 514.16 1.02 506.61 485.95 6.87

 HUB 6.53 1.06 6.15 513.39 1.02 505.01 485.65 7.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.68 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 36.99 27.38 23.50 3.88 0.94 0.44 1.64

 HUB 40.14 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 336.3929 188.0433 278.9263 1094.4376 0.3074 -0.1748 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5693 6.1583 505.3803 486.2452 7.1879 33.9866 33.0000 -0.9866

 

NASA/TM—2013-218094 O–17
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 285.3913 65.1693 277.8510 1097.1840 0.2601 0.1405 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5678 6.2701 507.9221 486.0497 410.5396 0.0243 0.3769

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 277.6338 0.0000 277.6338 1097.5552 0.2530 0.2997 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2815 508.2723 486.1017 0.0000 0.0600 0.0369 0.1725

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8797 6.5633 1.0616 514.4495 9.5225 233.7643 1.8121

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59413.910 0.457 88.563 272833.688 0.114827E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1441 Tt4 = 514.4495 T1 = 449.6691 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 403522.09 601.4967 83.2403 1.5133 0.8396 15.3681 1.1441 37.3740

NASA/TM—2013-218094 O–18
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.425 EfDer = 0.955 SH = 0.169925E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.353 2237.630 4.829 451.603 1.000 1.000 0.980

 W Kg/sec = 12.888 Wdry = 28.348 WH2O = 0.005 lbm/sec H2O = 0.078g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.540 2398.087 1.381 0.248 53.354 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59777.527 22245.760 3.527 831.557 235.769 619.754 2.629

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.53 -0.06 172.53 0.17 0.42 431.72

 MEAN 17.06 0.00 -0.02 172.53 -0.06 172.53 0.17 0.36

 HUB 12.51 0.00 -0.02 172.53 -0.06 172.53 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.82 50.47 16.35 402.84 438.29 4.74 449.21 445.17 9.75

 MEAN 62.62 47.20 15.42 333.13 375.21 4.74 449.21 445.17 9.75

 HUB 54.77 38.62 16.15 244.28 299.11 4.74 449.21 445.17 9.75

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 361.60 277.08 232.34 1043.28 0.35 7.29 6.52 16.04

 MEAN 18.04 366.01 280.62 234.99 1040.65 0.35 7.43 6.80 12.53

 HUB 15.00 396.32 316.42 238.65 1037.40 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.84 264.20 125.77 0.25 5717.31 0.92 0.87

 MEAN 352.19 245.64 71.57 0.24 5062.31 0.92 0.87 0.87 1.75

 HUB 292.91 239.80 23.51 0.23 4746.98 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 469.55 1.04 459.04 458.72 8.88

 MEAN 5.39 1.12 4.95 467.50 1.04 456.73 457.33 9.75

 HUB 5.35 1.11 4.85 466.51 1.03 453.88 456.74 10.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.02 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 50.06 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.98 -5.63 -9.30 3.67 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 376.7172 280.0765 251.9385 1040.3147 0.3621 -0.0368 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3972 4.9354 456.4458 457.6358 10.2047 48.0275 35.4000 -12.6275

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 251.2896 61.4731 243.6545 1047.4988 0.2399 0.5110 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3868 5.1780 462.7773 457.3915 554.9116 0.0329 0.6018

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 250.1552 0.0000 250.1552 1047.5355 0.2388 0.4798 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1570 462.8229 457.4998 0.0000 0.0600 0.0848 0.4652

NASA/TM—2013-218094 O–19
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8166 5.3630 1.1107 467.8524 16.2505 168.2937 1.3046

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 101093.602 0.623 161.978 299815.500 0.289880E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.747 EfDer = 0.960 SH = 0.430148E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.353 2237.630 5.363 467.852 1.000 1.000 0.980

 W Kg/sec = 12.888 Wdry = 28.341 WH2O = 0.012 lbm/sec H2O = 0.209g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.809 2356.091 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56315.379 22243.490 2.733 590.487 216.098 468.502 2.168

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 228.89 -0.08 228.89 0.22 0.44 422.51

 MEAN 18.08 0.00 -0.02 228.89 -0.08 228.89 0.22 0.40

 HUB 15.21 0.00 -0.02 228.89 -0.08 228.89 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.30 46.36 13.94 401.28 462.04 5.19 463.64 458.01 13.58

 MEAN 57.05 42.30 14.75 353.01 420.79 5.19 463.64 458.01 13.58

 HUB 52.39 37.84 14.55 297.01 375.03 5.19 463.64 458.01 13.58

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 333.23 228.50 242.54 1059.61 0.31 2.33 2.04 9.02

 MEAN 18.01 333.28 226.32 244.65 1057.53 0.32 2.40 2.13 7.35

 HUB 15.22 353.59 253.01 247.00 1055.49 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.74 296.32 170.24 0.28 4667.65 0.92 0.88

 MEAN 351.68 274.90 125.36 0.26 4077.41 0.92 0.88 0.88 1.69

 HUB 297.26 250.93 44.25 0.24 3852.81 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.92 1.10 5.53 482.50 1.03 473.58 467.90 9.81

 MEAN 5.85 1.09 5.46 480.64 1.03 471.72 466.75 10.51

 HUB 5.82 1.08 5.39 479.94 1.03 469.90 466.39 11.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.29 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.77 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.69 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 356.7161 226.9539 275.2059 1056.4901 0.3376 -0.1095 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8561 5.4174 470.8056 467.0911 10.9652 39.5114 30.6000 -8.9114

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 267.2122 56.6509 261.1380 1061.5082 0.2517 0.3551 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8511 5.6020 475.2909 466.8144 491.5697 0.0225 0.4522

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 276.7988 0.0000 276.7988 1061.0292 0.2609 0.3456 0.5911

NASA/TM—2013-218094 O–20
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5690 474.8719 466.8867 0.0000 0.0600 0.0623 0.2725

 

 STAGE EXIT CONDITIONS, STAGE 2 

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8361 5.8351 1.0880 481.0253 13.1740 191.0792 1.4812

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 82019.906 0.516 131.417 272980.156 0.487043E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.535 EfDer = 0.977 SH = 0.567048E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.353 2237.630 5.835 481.025 1.000 1.000 0.980

 W Kg/sec = 12.888 Wdry = 28.337 WH2O = 0.016 lbm/sec H2O = 0.291g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.785 2323.606 1.381 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53244.418 22242.293 2.708 545.479 201.410 424.468 2.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 234.26 -0.08 234.26 0.22 0.43 406.95

 MEAN 17.74 0.00 -0.02 234.26 -0.08 234.26 0.22 0.39

 HUB 15.05 0.00 -0.02 234.26 -0.08 234.26 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.14 46.36 12.78 391.91 456.66 5.64 476.62 467.05 10.91

 MEAN 55.93 43.40 12.53 346.38 418.23 5.64 476.62 467.05 10.91

 HUB 51.45 38.84 12.61 293.88 375.89 5.64 476.62 467.05 10.91

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 326.49 212.29 248.06 1072.99 0.30 2.26 1.98 8.75

 MEAN 17.51 328.57 213.31 249.92 1071.24 0.31 2.34 2.07 6.78

 HUB 14.85 351.00 244.36 251.97 1069.52 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.83 303.31 174.54 0.28 4206.99 0.92 0.89

 MEAN 341.85 281.04 128.54 0.26 3735.71 0.92 0.89 0.89 1.63

 HUB 289.98 256.07 45.61 0.24 3629.98 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 494.22 1.03 485.66 475.32 8.34

 MEAN 6.31 1.08 5.92 492.74 1.02 484.07 474.48 8.81

 HUB 6.30 1.08 5.85 492.41 1.02 482.52 474.38 9.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.56 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.48 27.22 23.50 3.72 0.94 0.48 1.62

 HUB 44.12 10.26 6.50 3.76 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.3975 214.7070 280.6968 1070.1414 0.3302 -0.1186 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3210 5.8671 483.0947 474.8139 9.1972 37.4126 31.5000 -5.9126

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 277.1002 60.4475 270.4267 1074.4080 0.2579 0.2962 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3181 6.0362 486.9563 474.5618 451.3937 0.0171 0.4215

 

NASA/TM—2013-218094 O–21
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 281.6672 0.0000 281.6672 1074.1730 0.2622 0.3254 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0148 486.7515 474.6295 0.0000 0.0600 0.0483 0.2440

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8585 6.3052 1.0806 493.1197 12.0953 198.0078 1.5349

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75345.914 0.504 120.724 272160.906 0.638634E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.734 EfDer = 0.988 SH = 0.737451E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.353 2237.630 6.305 493.120 1.000 1.000 0.980

 W Kg/sec = 12.888 Wdry = 28.332 WH2O = 0.021 lbm/sec H2O = 0.399g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.452 2294.935 1.380 0.249 53.372 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50508.223 22240.803 2.720 513.330 188.745 395.845 2.097

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 236.14 -0.08 236.14 0.22 0.41 385.71

 MEAN 16.97 0.00 -0.02 236.14 -0.08 236.14 0.22 0.38

 HUB 14.32 0.00 -0.02 236.14 -0.08 236.14 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.88 46.36 11.52 376.09 444.15 6.10 488.65 474.80 9.24

 MEAN 54.53 43.80 10.73 331.39 406.98 6.10 488.65 474.80 9.24

 HUB 49.83 37.84 11.99 279.63 366.06 6.10 488.65 474.80 9.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 315.15 193.00 249.14 1084.93 0.29 2.16 1.89 8.34

 MEAN 16.57 317.36 194.45 250.82 1083.37 0.29 2.24 1.97 6.35

 HUB 13.89 338.65 225.51 252.65 1081.83 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 368.67 304.84 175.67 0.28 3645.46 0.92 0.90 

 MEAN 323.64 282.13 129.19 0.26 3224.17 0.92 0.90 0.90 1.58

 HUB 271.23 256.75 45.72 0.24 3133.49 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.80 1.08 6.42 504.54 1.02 496.57 481.52 7.45

 MEAN 6.74 1.07 6.35 503.22 1.02 495.14 480.82 7.81

 HUB 6.73 1.07 6.29 502.94 1.02 493.74 480.76 8.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.76 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 37.79 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.75 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 337.3957 195.5433 274.9521 1082.5789 0.3117 -0.0949 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7506 6.3168 494.4354 481.1064 8.0645 35.4201 32.4000 -3.0201

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 276.8431 62.0878 269.7910 1085.8379 0.2550 0.2522 2.2705

 

NASA/TM—2013-218094 O–22
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7493 6.4549 497.4192 480.9043 432.2457 0.0133 0.3951

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 274.5850 0.0000 274.5850 1085.9397 0.2529 0.3060 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4495 497.5192 480.9568 0.0000 0.0600 0.0397 0.2387

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8724 6.7387 1.0687 503.5673 10.4483 215.1280 1.6677

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65127.602 0.479 104.351 279291.375 0.823268E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.087 EfDer = 0.995 SH = 0.942405E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.353 2237.630 6.739 503.567 1.000 1.000 0.980

 W Kg/sec = 12.888 Wdry = 28.326 WH2O = 0.027 lbm/sec H2O = 0.534g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.942 2271.003 1.380 0.249 53.379 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48154.203 22239.012 2.855 509.668 178.491 384.739 2.156

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 226.75 -0.08 226.75 0.21 0.39 363.06

 MEAN 15.91 0.00 -0.02 226.75 -0.08 226.75 0.21 0.35

 HUB 13.07 0.00 -0.02 226.75 -0.08 226.75 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.64 47.36 10.28 357.73 423.61 6.54 499.44 481.14 8.22

 MEAN 53.89 44.80 9.09 310.73 384.73 6.54 499.44 481.14 8.22

 HUB 48.39 38.84 9.55 255.22 341.46 6.54 499.44 481.14 8.22

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.82 180.14 239.67 1095.65 0.27 2.05 1.78 7.43

 MEAN 15.50 299.62 177.60 241.31 1094.04 0.27 2.13 1.86 5.75

 HUB 12.59 315.87 201.74 243.06 1092.44 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 350.31 293.94 170.17 0.27 3233.16 0.92 0.91

 MEAN 302.62 271.77 125.02 0.25 2753.62 0.92 0.91 0.91 1.56

 HUB 245.85 247.03 44.11 0.23 2540.88 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.20 1.07 6.84 513.69 1.02 506.48 486.81 6.90

 MEAN 7.13 1.06 6.77 512.19 1.02 504.99 486.04 7.23

 HUB 7.10 1.05 6.70 511.52 1.02 503.52 485.77 7.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.93 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.35 27.39 23.50 3.89 0.93 0.43 1.64

 HUB 39.69 10.29 6.50 3.79 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.7094 180.8565 274.4828 1092.7347 0.3008 -0.1771 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1336 6.7054 503.8060 486.3181 7.5603 33.3809 33.0000 -0.3809

 

NASA/TM—2013-218094 O–23
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 281.1361 64.1977 273.7082 1095.2523 0.2567 0.1262 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1323 6.8172 506.1318 486.1482 410.5396 0.0236 0.3670

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 273.5056 0.0000 273.5056 1095.6130 0.2496 0.2891 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8292 506.4712 486.1943 0.0000 0.0600 0.0366 0.1586

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8805 7.1274 1.0577 512.4675 8.9008 236.7589 1.8353

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55522.234 0.452 88.961 293635.563 0.104265E-02

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1348 Tt4 = 512.4675 T1 = 451.6031

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 379109.25 607.4313 80.5399 1.4761 0.8406 15.4249 1.1348 37.3740

NASA/TM—2013-218094 O–24
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.912 EfDer = 0.967 SH = 0.244170E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.504 2123.850 5.592 461.412 1.000 1.000 0.980

 W Kg/sec = 14.774 Wdry = 32.496 WH2O = 0.008 lbm/sec H2O = 0.126g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.582 2251.828 1.381 0.249 53.356 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60458.672 25501.412 3.525 831.557 235.907 619.754 2.627

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.49 -0.06 174.49 0.17 0.40 405.39

 MEAN 17.06 0.00 -0.02 174.49 -0.06 174.49 0.17 0.35

 HUB 12.51 0.00 -0.02 174.49 -0.06 174.49 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.47 50.47 15.00 382.36 420.35 5.49 458.96 453.27 10.13

 MEAN 61.11 47.20 13.91 316.19 361.20 5.49 458.96 453.27 10.13

 HUB 53.04 38.62 14.42 231.86 290.23 5.49 458.96 453.27 10.13

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 347.58 254.95 236.25 1052.67 0.33 7.29 6.52 16.04

 MEAN 18.04 354.36 262.02 238.56 1050.44 0.34 7.43 6.80 12.53

 HUB 15.00 387.03 302.14 241.87 1047.59 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 382.36 268.42 127.41 0.25 5260.78 0.92 0.88 

 MEAN 334.28 249.26 72.26 0.24 4726.90 0.92 0.88 0.88 1.66

 HUB 278.01 243.07 24.13 0.23 4532.81 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.23 1.11 5.78 477.08 1.03 467.37 464.75 9.40

 MEAN 6.16 1.10 5.70 475.49 1.03 465.40 463.73 10.14

 HUB 6.14 1.10 5.59 474.92 1.03 462.88 463.46 11.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.18 28.34 24.20 4.14 0.93 0.53 1.80

 MEAN 47.68 16.85 12.70 4.15 0.95 0.48 2.22

 HUB 51.32 -5.70 -9.30 3.60 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.967 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.8208 261.5152 255.8020 1050.0638 0.3484 -0.0422 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1686 5.6781 465.0784 464.0234 10.5709 45.6327 35.4000 -10.2327

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.3596 62.7134 248.5705 1056.2172 0.2427 0.4696 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1608 5.9166 470.5505 463.7760 554.9116 0.0261 0.5587

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 254.9372 0.0000 254.9372 1056.2693 0.2414 0.4501 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8989 470.6090 463.8860 0.0000 0.0600 0.0698 0.4331

NASA/TM—2013-218094 O–25
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8349 6.1396 1.0979 475.8306 14.4195 175.6598 1.3617

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89738.500 0.614 164.832 338130.094 0.376798E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.864 EfDer = 0.975 SH = 0.523496E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.504 2123.850 6.140 475.830 1.000 1.000 0.980

 W Kg/sec = 14.774 Wdry = 32.486 WH2O = 0.017 lbm/sec H2O = 0.286g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.537 2217.460 1.381 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57386.191 25498.615 2.706 590.487 218.248 468.502 2.147

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.24 -0.08 233.24 0.22 0.42 397.65

 MEAN 18.08 0.00 -0.02 233.24 -0.08 233.24 0.22 0.39

 HUB 15.21 0.00 -0.02 233.24 -0.08 233.24 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.52 46.36 12.16 380.88 446.69 5.94 471.46 464.38 13.28

 MEAN 55.16 42.30 12.86 335.06 408.32 5.94 471.46 464.38 13.28

 HUB 50.40 37.84 12.56 281.90 365.95 5.94 471.46 464.38 13.28

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.75 204.36 248.51 1066.67 0.30 2.33 2.04 9.02

 MEAN 18.01 324.03 205.79 250.30 1064.99 0.30 2.40 2.13 7.35

 HUB 15.22 346.24 237.13 252.29 1063.34 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.47 303.43 174.10 0.28 4174.74 0.92 0.89

 MEAN 333.80 281.13 128.01 0.26 3707.68 0.92 0.89 0.89 1.59

 HUB 282.14 256.27 45.01 0.24 3611.11 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.09 6.27 488.26 1.03 479.94 472.58 10.20

 MEAN 6.61 1.08 6.21 486.87 1.02 478.43 471.75 10.76

 HUB 6.60 1.08 6.14 486.58 1.02 476.95 471.66 11.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.43 35.01 31.50 3.51 0.93 0.48 1.40

 MEAN 39.43 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.23 10.12 6.50 3.62 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 349.1423 206.3652 281.6270 1063.8708 0.3282 -0.1230 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6248 6.1548 477.4464 472.0849 11.2365 36.2325 30.6000 -5.6325

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.5397 58.2044 268.2989 1068.0228 0.2571 0.2902 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6220 6.3285 481.1819 471.8335 491.5697 0.0166 0.3980

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.1866 0.0000 284.1866 1067.5334 0.2662 0.2995 0.5911

NASA/TM—2013-218094 O–26
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2956 480.7492 471.9128 0.0000 0.0600 0.0473 0.2124

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8562 6.6090 1.0765 487.2327 11.4030 203.9495 1.5810

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71024.398 0.496 130.458 309125.125 0.581941E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.430 EfDer = 0.989 SH = 0.660620E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.504 2123.850 6.609 487.233 1.000 1.000 0.980

 W Kg/sec = 14.774 Wdry = 32.482 WH2O = 0.021 lbm/sec H2O = 0.378g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.068 2191.360 1.380 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 54642.625 25497.240 2.658 545.479 205.183 424.468 2.069

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.42 -0.08 240.42 0.22 0.41 383.79

 MEAN 17.74 0.00 -0.02 240.42 -0.08 240.42 0.22 0.38

 HUB 15.05 0.00 -0.02 240.42 -0.08 240.42 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.13 46.36 10.77 371.98 442.98 6.38 482.59 472.04 11.14

 MEAN 53.83 43.40 10.43 328.77 407.36 6.38 482.59 472.04 11.14

 HUB 49.25 38.84 10.41 278.94 368.31 6.38 482.59 472.04 11.14

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 317.09 187.10 256.00 1077.95 0.29 2.26 1.98 8.75

 MEAN 17.51 321.27 192.08 257.53 1076.59 0.30 2.34 2.07 6.78

 HUB 14.85 345.42 228.29 259.23 1075.25 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 367.16 312.98 180.06 0.29 3708.18 0.92 0.91

 MEAN 324.47 289.56 132.39 0.27 3364.16 0.92 0.91 0.91 1.53

 HUB 275.23 263.44 46.94 0.25 3391.42 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.11 1.08 6.70 498.26 1.02 490.19 478.89 8.96

 MEAN 7.07 1.07 6.65 497.24 1.02 488.96 478.33 9.35

 HUB 7.07 1.07 6.59 497.32 1.02 487.75 478.48 9.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.16 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.72 27.21 23.50 3.71 0.94 0.43 1.62

 HUB 41.37 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 348.0034 193.3425 289.3527 1075.3994 0.3236 -0.1334 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0788 6.5899 487.8904 478.6639 9.7638 33.7504 31.5000 -2.2504

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.7636 62.5555 279.8574 1078.8304 0.2658 0.2194 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0774 6.7427 491.0097 478.4434 451.3937 0.0133 0.3626

 

NASA/TM—2013-218094 O–27
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.3587 0.0000 291.3587 1078.5887 0.2701 0.2696 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7217 490.7966 478.5121 0.0000 0.0600 0.0383 0.1713

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 7.0664 1.0692 497.6079 10.3759 213.5297 1.6553

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64661.250 0.480 118.770 309313.969 0.729612E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.393 EfDer = 0.997 SH = 0.821724E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.504 2123.850 7.066 497.608 1.000 1.000 0.980

 W Kg/sec = 14.774 Wdry = 32.477 WH2O = 0.027 lbm/sec H2O = 0.493g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.227 2168.395 1.380 0.249 53.375 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52211.523 25495.625 2.647 513.330 193.956 395.845 2.041 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.11 -0.08 244.11 0.23 0.40 364.44

 MEAN 16.97 0.00 -0.02 244.11 -0.08 244.11 0.23 0.37

 HUB 14.32 0.00 -0.02 244.11 -0.08 244.11 0.23 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.64 46.36 9.28 356.97 432.52 6.82 492.83 478.64 9.72

 MEAN 52.19 43.80 8.39 314.54 398.21 6.82 492.83 478.64 9.72

 HUB 47.40 37.84 9.56 265.41 360.66 6.82 492.83 478.64 9.72

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 308.29 167.25 258.98 1087.95 0.28 2.16 1.89 8.34

 MEAN 16.57 312.57 173.02 260.31 1086.78 0.29 2.24 1.97 6.35

 HUB 13.89 335.57 209.93 261.79 1085.63 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.92 316.92 182.67 0.29 3159.37 0.92 0.91

 MEAN 307.18 292.85 134.16 0.27 2869.00 0.92 0.91 0.91 1.48

 HUB 257.44 266.06 47.51 0.25 2917.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.52 1.06 7.12 507.00 1.02 499.38 484.17 8.18

 MEAN 7.48 1.06 7.06 506.14 1.02 498.30 483.72 8.47

 HUB 7.48 1.06 7.01 506.28 1.02 497.25 483.90 8.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.86 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.61 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.73 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 334.3180 173.9904 285.4748 1085.9031 0.3079 -0.1076 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4882 7.0182 497.5096 484.0155 8.7538 31.3614 32.4000 1.0386

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.4975 64.7016 281.1486 1088.3962 0.2651 0.1673 2.2705

 

NASA/TM—2013-218094 O–28
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4873 7.1352 499.7982 483.8500 432.2457 0.0122 0.3319

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.0848 0.0000 286.0848 1088.5114 0.2628 0.2397 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1309 499.9095 483.8945 0.0000 0.0600 0.0370 0.1571

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 7.4767 1.0581 506.4726 8.8652 234.7666 1.8199

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55279.379 0.451 101.537 318470.906 0.900529E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.536 EfDer = 1.000 SH = 0.100744E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.504 2123.850 7.477 506.472 1.000 1.000 0.980

 W Kg/sec = 14.774 Wdry = 32.471 WH2O = 0.033 lbm/sec H2O = 0.629g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.148 2149.335 1.380 0.249 53.381 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50127.609 25493.766 2.756 509.668 184.963 384.739 2.080

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.05 -0.08 236.05 0.22 0.38 343.61

 MEAN 15.91 0.00 -0.02 236.05 -0.08 236.05 0.22 0.35

 HUB 13.07 0.00 -0.02 236.05 -0.08 236.05 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.20 47.36 7.84 339.54 413.60 7.24 502.01 484.02 8.81

 MEAN 51.34 44.80 6.54 294.93 377.82 7.24 502.01 484.02 8.81

 HUB 45.75 38.84 6.91 242.24 338.29 7.24 502.01 484.02 8.81

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.42 154.13 250.85 1096.98 0.27 2.05 1.78 7.43

 MEAN 15.50 296.70 156.34 252.17 1095.76 0.27 2.13 1.86 5.75

 HUB 12.59 315.16 187.12 253.59 1094.57 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 332.50 307.80 178.37 0.28 2766.64 0.92 0.91

 MEAN 287.23 284.12 130.90 0.26 2424.13 0.92 0.91 0.91 1.46

 HUB 233.34 257.77 46.22 0.24 2356.93 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.89 1.05 7.51 514.69 1.02 507.74 488.67 7.66

 MEAN 7.84 1.05 7.45 513.67 1.01 506.62 488.16 7.94

 HUB 7.83 1.05 7.39 513.48 1.01 505.51 488.13 8.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.57 35.41 31.50 3.91 0.93 0.39 1.40

 MEAN 31.80 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.42 10.33 6.50 3.83 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.1992 159.2029 287.0003 1094.3400 0.2999 -0.1961 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8419 7.3740 505.3148 488.4469 8.3167 29.0177 33.0000 3.9823

 

NASA/TM—2013-218094 O–29
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.0388 67.3724 287.2435 1096.1312 0.2692 0.0204 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8391 7.4595 506.9713 488.3180 410.5396 0.0270 0.3010

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.0033 0.0000 287.0033 1096.5316 0.2617 0.2134 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4738 507.3462 488.3485 0.0000 0.0600 0.0420 0.0564

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8743 7.8332 1.0477 513.9473 7.4751 261.2956 2.0255

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46641.816 0.422 85.672 335748.313 0.109649E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1139 Tt4 = 513.9473 T1 = 461.4120

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 327345.34 601.2687 80.5820 1.4007 0.8545 13.9123 1.1139 37.3740

NASA/TM—2013-218094 O–30
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.080 EfDer = 0.995 SH = 0.342180E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.014 1953.041 6.513 472.322 1.000 1.000 0.980

 W Kg/sec = 18.643 Wdry = 41.000 WH2O = 0.014 lbm/sec H2O = 0.201g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.335 2046.675 1.381 0.249 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 67255.000 32177.367 3.215 831.557 258.626 619.754 2.396

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 194.11 -0.07 194.11 0.18 0.38 368.45

 MEAN 17.06 0.00 -0.02 194.11 -0.07 194.11 0.18 0.33

 HUB 12.51 0.00 -0.02 194.11 -0.07 194.11 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.10 50.47 10.63 351.61 401.69 6.36 469.30 461.97 10.25

 MEAN 56.28 47.20 9.08 290.76 349.66 6.36 469.30 461.97 10.25

 HUB 47.69 38.62 9.07 213.21 288.39 6.36 469.30 461.97 10.25

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 337.85 208.89 265.53 1061.12 0.32 7.29 6.52 16.04

 MEAN 18.04 350.56 226.75 267.35 1059.66 0.33 7.43 6.80 12.53

 HUB 15.00 391.35 282.88 270.43 1057.41 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.61 301.46 142.72 0.28 4310.70 0.92 0.91

 MEAN 307.40 279.25 80.65 0.26 4090.83 0.92 0.91 0.91 1.41

 HUB 255.65 271.80 27.22 0.26 4243.98 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.09 6.59 484.13 1.02 474.96 470.43 10.12

 MEAN 7.04 1.08 6.53 483.52 1.02 473.65 470.09 10.62

 HUB 7.06 1.08 6.43 483.94 1.02 471.64 470.52 11.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.19 28.26 24.20 4.06 0.93 0.39 1.80

 MEAN 40.30 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.29 -5.75 -9.30 3.55 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.4524 226.3109 286.9474 1059.0752 0.3451 -0.0599 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0486 6.4983 473.1380 470.4045 11.0908 38.2623 35.4000 -2.8623

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 289.8214 70.8991 281.0155 1063.5159 0.2725 0.3335 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0461 6.6964 477.1183 470.1959 554.9116 0.0146 0.4341

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 287.7052 0.0000 287.7052 1063.6150 0.2705 0.3460 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6887 477.2167 470.3002 0.0000 0.0600 0.0394 0.3192

NASA/TM—2013-218094 O–31
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8758 7.0328 1.0798 483.8639 11.5424 201.2482 1.5601

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71866.430 0.581 166.568 420407.688 0.476328E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.238 EfDer = 1.000 SH = 0.611441E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.014 1953.041 7.033 483.864 1.000 1.000 0.980

 W Kg/sec = 18.643 Wdry = 40.989 WH2O = 0.025 lbm/sec H2O = 0.373g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.799 2022.124 1.381 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64678.055 32173.967 2.435 590.487 242.457 468.502 1.932 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 262.88 -0.09 262.88 0.25 0.41 362.62

 MEAN 18.08 0.00 -0.02 262.88 -0.09 262.88 0.25 0.38

 HUB 15.21 0.00 -0.02 262.88 -0.09 262.88 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.12 46.36 6.76 350.24 437.99 6.74 478.32 470.72 13.06

 MEAN 49.54 42.30 7.24 308.12 405.09 6.74 478.32 470.72 13.06

 HUB 44.61 37.84 6.77 259.23 369.26 6.74 478.32 470.72 13.06

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 320.22 149.42 283.22 1071.10 0.30 2.33 2.04 9.02

 MEAN 18.01 326.87 161.29 284.30 1070.28 0.31 2.40 2.13 7.35

 HUB 15.22 353.40 208.22 285.55 1069.47 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 348.03 345.92 198.61 0.32 3052.96 0.92 0.91

 MEAN 306.95 319.44 145.66 0.30 2906.53 0.92 0.91 0.91 1.38

 HUB 259.45 290.11 51.24 0.27 3171.08 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.44 1.06 7.00 492.22 1.02 483.99 476.17 11.09

 MEAN 7.42 1.06 6.96 491.82 1.02 483.24 475.95 11.39

 HUB 7.46 1.06 6.92 492.54 1.02 482.51 476.51 11.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.81 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.57 27.13 23.50 3.63 0.93 0.33 1.63

 HUB 36.10 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.0593 161.7465 320.5645 1068.7174 0.3360 -0.1646 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4380 6.8862 481.8437 476.3370 12.0332 26.7740 30.6000 3.8260

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 314.8015 66.7402 307.6455 1071.3690 0.2938 0.0940 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4356 7.0088 484.2371 476.1564 491.5697 0.0150 0.2535

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 326.0359 0.0000 326.0359 1070.7240 0.3045 0.1457 0.5911

NASA/TM—2013-218094 O–32
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9666 483.6595 476.2452 0.0000 0.0600 0.0416 0.0058

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8709 7.4229 1.0555 492.1900 8.3267 251.9809 1.9533

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 51883.652 0.428 120.253 387527.969 0.663734E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.329 EfDer = 0.994 SH = 0.729517E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.014 1953.041 7.423 492.190 1.000 1.000 0.980

 W Kg/sec = 18.643 Wdry = 40.984 WH2O = 0.030 lbm/sec H2O = 0.461g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.120 2004.948 1.380 0.249 53.372 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62481.402 32172.475 2.354 545.479 231.705 424.468 1.832

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 274.90 -0.09 274.90 0.26 0.41 351.14

 MEAN 17.74 0.00 -0.02 274.90 -0.09 274.90 0.26 0.38

 HUB 15.05 0.00 -0.02 274.90 -0.09 274.90 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.22 46.36 4.86 342.06 438.91 7.10 486.13 476.27 11.79

 MEAN 47.73 43.40 4.33 302.33 408.69 7.10 486.13 476.27 11.79

 HUB 43.03 38.84 4.19 256.50 376.05 7.10 486.13 476.27 11.79

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 323.13 128.30 296.57 1078.55 0.30 2.26 1.98 8.75

 MEAN 17.51 330.62 144.82 297.22 1078.10 0.31 2.34 2.07 6.78

 HUB 14.85 358.05 198.39 298.06 1077.66 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.63 363.00 209.33 0.34 2543.61 0.92 0.91

 MEAN 298.37 334.54 153.56 0.31 2536.93 0.92 0.91 0.91 1.32

 HUB 253.10 303.04 54.70 0.28 2947.55 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.78 1.05 7.31 499.15 1.01 490.77 480.63 10.42

 MEAN 7.77 1.05 7.29 499.13 1.01 490.36 480.65 10.56

 HUB 7.83 1.06 7.26 500.25 1.02 489.97 481.42 10.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.39 35.22 31.50 3.72 0.93 0.28 1.40

 MEAN 25.98 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.65 10.40 6.50 3.90 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.1683 145.7675 334.8130 1076.3820 0.3393 -0.1772 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7887 7.2002 488.8108 481.0508 11.1963 23.5269 31.5000 7.9731

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 334.4847 72.9656 326.4292 1078.2778 0.3102 -0.0016 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7832 7.2875 490.5329 480.9088 451.3937 0.0209 0.2116

 

NASA/TM—2013-218094 O–33
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 340.3156 0.0000 340.3156 1077.9268 0.3157 0.0902 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2532 490.2175 480.9674 0.0000 0.0600 0.0575 -0.0694

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8395 7.7647 1.0461 499.5078 7.3181 272.7612 2.1144

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45618.555 0.400 105.732 390251.938 0.785547E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.743 EfDer = 0.973 SH = 0.856501E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.014 1953.041 7.765 499.508 1.000 1.000 0.980

 W Kg/sec = 18.643 Wdry = 40.979 WH2O = 0.035 lbm/sec H2O = 0.557g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.197 1990.207 1.380 0.249 53.376 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60724.617 32170.867 2.300 513.330 223.163 395.845 1.774

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 283.91 -0.10 283.91 0.26 0.40 334.49

 MEAN 16.97 0.00 -0.02 283.91 -0.10 283.91 0.26 0.37

 HUB 14.32 0.00 -0.02 283.91 -0.10 283.91 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.15 46.36 2.79 328.26 434.07 7.41 493.04 480.95 10.90

 MEAN 45.54 43.80 1.74 289.24 405.36 7.41 493.04 480.95 10.90

 HUB 40.70 37.84 2.86 244.06 374.46 7.41 493.04 480.95 10.90

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.12 105.00 305.58 1084.86 0.30 2.16 1.89 8.34

 MEAN 16.57 329.94 123.60 305.91 1084.66 0.30 2.24 1.97 6.35

 HUB 13.89 355.46 180.06 306.47 1084.48 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.78 374.66 216.78 0.35 1984.32 0.92 0.89

 MEAN 282.48 344.71 158.88 0.32 2050.21 0.92 0.89 0.89 1.26

 HUB 236.73 311.67 56.67 0.29 2502.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.04 1.04 7.57 504.93 1.01 496.56 484.24 10.01

 MEAN 8.05 1.04 7.56 505.11 1.01 496.38 484.37 10.06

 HUB 8.11 1.04 7.54 506.35 1.01 496.22 485.18 10.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.96 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 22.00 27.45 23.50 3.95 0.91 0.24 1.62

 HUB 30.44 10.48 6.50 3.98 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.5332 124.2963 336.2982 1083.3134 0.3310 -0.1447 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0632 7.4820 495.1564 484.7242 10.5341 20.2844 32.4000 12.1156

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 342.7377 76.8660 334.0071 1084.2859 0.3161 -0.0636 2.2705

 

NASA/TM—2013-218094 O–34
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0535 7.5218 496.0447 484.6446 432.2457 0.0289 0.1753

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 340.5098 0.0000 340.5098 1084.4166 0.3140 0.0366 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.5033 496.1669 484.6472 0.0000 0.0600 0.0815 -0.0997

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7693 8.0265 1.0337 505.4637 5.9562 313.7013 2.4318

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37145.453 0.359 86.094 404292.250 0.915382E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.656 EfDer = 0.939 SH = 0.992727E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.014 1953.041 8.027 505.464 1.000 1.000 0.980

 W Kg/sec = 18.643 Wdry = 40.973 WH2O = 0.041 lbm/sec H2O = 0.661g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.150 1978.447 1.380 0.249 53.380 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59363.680 32169.146 2.347 509.668 217.188 384.739 1.771

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 279.54 -0.10 279.54 0.26 0.39 316.29

 MEAN 15.91 0.00 -0.02 279.54 -0.10 279.54 0.26 0.36

 HUB 13.07 0.00 -0.02 279.54 -0.10 279.54 0.26 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.17 47.36 0.81 312.24 419.16 7.67 499.20 484.60 10.26

 MEAN 44.14 44.80 -0.66 271.21 389.55 7.67 499.20 484.60 10.26

 HUB 38.56 38.84 -0.28 222.76 357.50 7.67 499.20 484.60 10.26

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.63 89.73 301.57 1090.68 0.29 2.05 1.78 7.43

 MEAN 15.50 319.94 105.98 301.88 1090.48 0.29 2.13 1.86 5.75

 HUB 12.59 341.30 158.15 302.45 1090.28 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 305.76 370.96 216.03 0.34 1611.54 0.92 0.86

 MEAN 264.13 340.80 158.15 0.31 1644.00 0.92 0.86 0.86 1.23

 HUB 214.58 307.67 56.43 0.28 1992.39 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.25 1.03 7.79 509.87 1.01 501.93 487.21 9.66

 MEAN 8.25 1.03 7.78 509.96 1.01 501.75 487.28 9.72

 HUB 8.30 1.03 7.76 510.91 1.01 501.57 487.89 9.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.57 35.62 31.50 4.12 0.93 0.19 1.40

 MEAN 19.34 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.61 10.57 6.50 4.07 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.939 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.4062 107.9253 344.9153 1088.3212 0.3321 -0.2495 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2562 7.6574 499.7746 487.6631 10.3958 17.3751 33.0000 15.6249

 

NASA/TM—2013-218094 O–35
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 358.3401 81.8273 348.8723 1088.5165 0.3292 -0.2755 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2295 7.6424 499.9515 487.6195 410.5396 0.0746 0.1434

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 348.6070 0.0000 348.6070 1089.1161 0.3201 0.0033 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6593 500.5032 487.5972 0.0000 0.0600 0.1048 -0.2410

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6771 8.2148 1.0235 510.2430 4.7794 365.7110 2.8350

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 29820.438 0.319 69.116 428339.313 0.105550E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0803 Tt4 = 510.2430 T1 = 472.3221

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 236334.52 547.7629 88.3348 1.2613 0.8226 9.0799 1.0803 37.3740

NASA/TM—2013-218094 O–36
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.449 EfDer = 0.998 SH = 0.542941E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.820 1794.389 7.939 487.554 1.000 1.000 0.980

 W Kg/sec = 23.100 Wdry = 50.793 WH2O = 0.028 lbm/sec H2O = 0.376g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 91.228 1850.813 1.381 0.249 53.366 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70660.625 39867.703 3.113 831.557 267.138 619.754 2.320

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 203.94 -0.07 203.94 0.19 0.36 333.19

 MEAN 17.06 0.00 -0.02 203.94 -0.07 203.94 0.19 0.31

 HUB 12.51 0.00 -0.02 203.94 -0.07 203.94 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.74 50.47 7.27 323.05 382.09 7.74 484.22 473.62 10.37

 MEAN 52.65 47.20 5.45 267.14 336.15 7.74 484.22 473.62 10.37

 HUB 43.86 38.62 5.24 195.89 282.83 7.74 484.22 473.62 10.37

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.83 171.26 281.87 1075.19 0.31 7.29 6.52 16.04

 MEAN 18.04 344.71 196.74 283.05 1074.34 0.32 7.43 6.80 12.53

 HUB 15.00 388.51 263.34 285.64 1072.61 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 323.05 320.14 151.78 0.30 3534.65 0.92 0.91

 MEAN 282.43 295.74 85.69 0.28 3549.61 0.92 0.91 0.91 1.27

 HUB 234.88 287.05 28.46 0.27 3951.01 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.90 496.44 1.02 487.71 479.78 10.65

 MEAN 8.43 1.06 7.86 496.48 1.02 486.94 479.87 10.93

 HUB 8.49 1.07 7.76 497.49 1.02 485.37 480.68 11.52

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.28 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 34.80 16.84 12.70 4.14 0.92 0.26 2.22

 HUB 42.67 -5.69 -9.30 3.61 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.8792 196.3583 303.9736 1073.6146 0.3371 -0.0742 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4436 7.8133 486.2925 480.1810 11.3960 32.8613 35.4000 2.5387

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 309.0550 75.6043 299.6648 1076.7456 0.2870 0.2247 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4412 7.9781 489.1367 479.9964 554.9116 0.0140 0.3464

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 306.7444 0.0000 306.7444 1076.8635 0.2848 0.2495 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9706 489.2512 480.0911 0.0000 0.0600 0.0388 0.2124

NASA/TM—2013-218094 O–37
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8718 8.4261 1.0613 496.8008 9.2467 223.6732 1.7339

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57622.586 0.552 165.487 509240.844 0.693042E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.016 EfDer = 0.986 SH = 0.835903E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.820 1794.389 8.426 496.801 1.000 1.000 0.980

 W Kg/sec = 23.100 Wdry = 50.778 WH2O = 0.042 lbm/sec H2O = 0.594g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.769 1833.511 1.380 0.249 53.375 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68910.070 39863.113 2.324 590.487 254.123 468.502 1.844

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 280.08 -0.10 280.08 0.26 0.40 328.80

 MEAN 18.08 0.00 -0.02 280.08 -0.10 280.08 0.26 0.37

 HUB 15.21 0.00 -0.02 280.08 -0.10 280.08 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.97 46.36 2.61 321.79 426.68 8.05 490.51 480.47 12.80

 MEAN 45.32 42.30 3.02 283.09 398.29 8.05 490.51 480.47 12.80

 HUB 40.39 37.84 2.55 238.17 367.72 8.05 490.51 480.47 12.80

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.85 104.92 305.33 1081.86 0.30 2.33 2.04 9.02

 MEAN 18.01 330.06 124.77 305.57 1081.73 0.31 2.40 2.13 7.35

 HUB 15.22 356.50 182.84 306.04 1081.61 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.76 373.34 214.84 0.35 2144.40 0.92 0.90

 MEAN 282.02 343.66 157.25 0.32 2248.81 0.92 0.90 0.90 1.25

 HUB 238.38 311.04 55.54 0.29 2784.82 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.21 502.19 1.01 493.83 483.87 11.79

 MEAN 8.74 1.04 8.20 502.45 1.01 493.71 484.06 11.83

 HUB 8.82 1.05 8.19 503.79 1.01 493.60 484.96 11.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.96 35.13 31.50 3.63 0.93 0.21 1.40

 MEAN 22.21 27.23 23.50 3.73 0.91 0.23 1.63

 HUB 30.86 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 367.0581 125.1181 345.0756 1079.8490 0.3399 -0.1951 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7591 8.0948 492.0063 484.4808 12.5806 19.9297 30.6000 10.6703

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 340.8462 72.2618 333.0981 1081.4829 0.3152 -0.0482 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7499 8.1755 493.4941 484.3387 491.5697 0.0264 0.1587

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 353.6906 0.0000 353.6906 1080.6954 0.3273 0.0205 0.5911

NASA/TM—2013-218094 O–38
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1085 492.7791 484.4313 0.0000 0.0600 0.0724 -0.1674

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7948 8.7240 1.0354 502.8094 6.0089 305.0031 2.3644

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37474.766 0.367 107.624 472324.219 0.889674E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.359 EfDer = 0.944 SH = 0.954542E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.820 1794.389 8.724 502.809 1.000 1.000 0.980

 W Kg/sec = 23.100 Wdry = 50.772 WH2O = 0.049 lbm/sec H2O = 0.691g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.311 1822.523 1.380 0.249 53.379 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67629.586 39861.254 2.209 545.479 246.947 424.468 1.719

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 297.56 -0.10 297.56 0.27 0.40 319.19

 MEAN 17.74 0.00 -0.02 297.56 -0.10 297.56 0.27 0.38

 HUB 15.05 0.00 -0.02 297.56 -0.10 297.56 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.57 46.36 0.21 314.28 432.87 8.28 495.71 484.35 12.22

 MEAN 43.04 43.40 -0.36 277.77 407.12 8.28 495.71 484.35 12.22

 HUB 38.39 38.84 -0.45 235.67 379.64 8.28 495.71 484.35 12.22

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 334.89 79.56 325.31 1086.15 0.31 2.26 1.98 8.75

 MEAN 17.51 341.61 105.23 325.00 1086.48 0.31 2.34 2.07 6.78

 HUB 14.85 367.74 172.00 325.04 1086.81 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 310.20 398.77 230.64 0.37 1578.16 0.92 0.86

 MEAN 274.13 366.27 168.91 0.34 1844.03 0.92 0.86 0.86 1.19

 HUB 232.54 330.63 60.53 0.30 2555.77 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.94 1.02 8.38 506.77 1.01 497.78 486.83 11.70

 MEAN 8.98 1.03 8.39 507.44 1.01 498.08 487.23 11.58

 HUB 9.08 1.04 8.40 509.23 1.01 498.38 488.36 11.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.74 35.34 31.50 3.84 0.93 0.14 1.40

 MEAN 17.94 27.46 23.50 3.96 0.90 0.18 1.62

 HUB 27.89 10.55 6.50 4.05 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.944 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 381.8990 105.9202 366.9165 1084.3282 0.3522 -0.2096 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9934 8.2640 496.1217 487.6974 12.3948 16.1022 31.5000 15.3978

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 368.8958 80.4721 360.0115 1085.1864 0.3399 -0.1537 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9758 8.2951 496.9042 487.6047 451.3937 0.0390 0.1143

 

NASA/TM—2013-218094 O–39
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 376.3284 0.0000 376.3284 1084.6997 0.3469 -0.0438 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2320 496.4605 487.6504 0.0000 0.0600 0.1033 -0.2569

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6682 8.9365 1.0244 507.8116 5.0022 346.5993 2.6868

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31208.926 0.324 89.629 478236.031 0.100794E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.446 EfDer = 0.884 SH = 0.107327E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.820 1794.389 8.936 507.811 1.000 1.000 0.980

 W Kg/sec = 23.100 Wdry = 50.766 WH2O = 0.055 lbm/sec H2O = 0.785g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.714 1813.524 1.380 0.249 53.383 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66921.813 39859.391 2.119 513.330 242.289 395.845 1.634

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 312.88 -0.11 312.88 0.29 0.40 304.80

 MEAN 16.97 0.00 -0.02 312.88 -0.11 312.88 0.29 0.38

 HUB 14.32 0.00 -0.02 312.88 -0.11 312.88 0.29 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.96 46.36 -2.40 301.59 434.65 8.45 499.97 487.48 11.85

 MEAN 40.35 43.80 -3.45 265.74 410.58 8.45 499.97 487.48 11.85

 HUB 35.64 37.84 -2.20 224.24 385.00 8.45 499.97 487.48 11.85

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.40 52.20 341.44 1089.33 0.32 2.16 1.89 8.34

 MEAN 16.57 350.31 81.46 340.71 1090.03 0.32 2.24 1.97 6.35

 HUB 13.89 373.50 153.48 340.50 1090.70 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.64 419.34 243.45 0.38 987.53 0.92 0.81

 MEAN 259.53 384.44 178.07 0.35 1351.86 0.92 0.81 0.81 1.13

 HUB 217.50 346.47 64.02 0.32 2133.42 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.07 1.01 8.46 510.29 1.00 500.73 489.07 11.81

 MEAN 9.11 1.02 8.49 511.20 1.01 501.37 489.58 11.56

 HUB 9.22 1.03 8.51 513.16 1.01 501.99 490.76 11.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.69 35.49 31.50 3.99 0.93 0.08 1.40

 MEAN 13.45 27.59 23.50 4.09 0.89 0.12 1.62

 HUB 24.26 10.65 6.50 4.15 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.884 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 384.2975 81.9135 375.4660 1088.2290 0.3531 -0.1722 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1253 8.3815 499.7201 490.0020 12.2265 12.3071 32.4000 20.0929

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 385.1968 86.3884 375.3847 1088.1716 0.3540 -0.2072 2.2705

 

NASA/TM—2013-218094 O–40
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0996 8.3545 499.6647 489.9867 432.2457 0.0499 0.0784

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 383.6946 0.0000 383.6946 1088.2726 0.3526 -0.0938 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3117 499.7575 489.9464 0.0000 0.0600 0.1318 -0.2737

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4594 9.0469 1.0124 511.5529 3.7413 428.5756 3.3223

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23350.693 0.267 67.061 498208.938 0.112517E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.314 EfDer = 0.821 SH = 0.119229E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.820 1794.389 9.047 511.553 1.000 1.000 0.980

 W Kg/sec = 23.100 Wdry = 50.760 WH2O = 0.061 lbm/sec H2O = 0.876g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.006 1806.880 1.380 0.249 53.387 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66588.977 39857.523 2.122 509.668 240.231 384.739 1.602

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 313.56 -0.11 313.56 0.29 0.39 288.86

 MEAN 15.91 0.00 -0.02 313.56 -0.11 313.56 0.29 0.37

 HUB 13.07 0.00 -0.02 313.56 -0.11 313.56 0.29 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.47 47.36 -4.89 286.87 425.06 8.55 503.68 489.71 11.55

 MEAN 38.49 44.80 -6.31 249.18 400.58 8.55 503.68 489.71 11.55

 HUB 33.15 38.84 -5.69 204.66 374.50 8.55 503.68 489.71 11.55

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 344.43 34.06 342.74 1092.41 0.32 2.05 1.78 7.43

 MEAN 15.50 347.62 62.27 342.00 1093.18 0.32 2.13 1.86 5.75

 HUB 12.59 366.57 132.35 341.85 1093.92 0.34 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.92 422.39 246.87 0.39 612.96 0.92 0.75

 MEAN 242.68 386.67 180.41 0.35 966.70 0.92 0.75 0.75 1.10

 HUB 197.15 347.93 64.80 0.32 1667.72 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.12 1.01 8.52 513.09 1.00 503.59 490.76 11.81

 MEAN 9.16 1.01 8.55 513.98 1.00 504.30 491.24 11.54

 HUB 9.25 1.02 8.57 515.74 1.01 504.97 492.25 11.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.67 35.76 31.50 4.26 0.93 0.03 1.40

 MEAN 10.32 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.16 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.821 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 397.4363 63.4080 392.3456 1090.2694 0.3645 -0.2850 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1662 8.3729 501.6172 491.7422 12.5802 9.1803 33.0000 23.8197

 

NASA/TM—2013-218094 O–41
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 411.2380 93.9066 400.3727 1089.3030 0.3775 -0.4474 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.1073 8.2653 500.7232 491.7842 410.5396 0.1134 0.0517

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 399.8345 0.0000 399.8345 1090.1110 0.3668 -0.1026 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2916 501.4642 491.7085 0.0000 0.0600 0.1452 -0.4059

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2308 9.0872 1.0045 514.2682 2.7152 543.5432 4.2135

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 16953.031 0.215 48.688 530332.563 0.124600E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0548 Tt4 = 514.2682 T1 = 487.5544 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 166610.00 478.4884 91.2278 1.1446 0.6913 5.4493 1.0548 37.3740

NASA/TM—2013-218094 O–42
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.537 EfDer = 1.000 SH = 0.823303E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.642 1584.377 9.337 500.812 1.000 1.000 0.980

 W Kg/sec = 22.565 Wdry = 49.601 WH2O = 0.041 lbm/sec H2O = 0.656g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.794 1612.425 1.380 0.249 53.375 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59969.203 38939.055 3.697 831.557 224.917 619.754 2.755

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.08 -0.06 173.08 0.16 0.31 290.28

 MEAN 17.06 0.00 -0.02 173.08 -0.06 173.08 0.16 0.27

 HUB 12.51 0.00 -0.02 173.08 -0.06 173.08 0.16 0.23

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.76 50.47 8.29 285.24 333.69 9.18 498.41 483.36 10.50

 MEAN 53.74 47.20 6.54 235.88 292.62 9.18 498.41 483.36 10.50

 HUB 44.99 38.62 6.37 172.97 244.73 9.18 498.41 483.36 10.50

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 286.20 156.41 239.67 1090.09 0.26 7.29 6.52 16.04

 MEAN 18.04 298.47 176.77 240.49 1089.37 0.27 7.43 6.80 12.53

 HUB 15.00 335.08 231.62 242.14 1088.03 0.31 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 285.24 272.10 128.83 0.25 3227.99 0.92 0.91

 MEAN 249.37 251.21 72.60 0.23 3189.28 0.92 0.91 0.91 1.31

 HUB 207.39 243.35 24.22 0.22 3475.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.34 507.97 1.01 501.40 488.20 10.86

 MEAN 9.78 1.05 9.29 507.88 1.01 500.74 488.21 11.09

 HUB 9.82 1.05 9.21 508.52 1.02 499.51 488.74 11.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.13 28.26 24.20 4.06 0.93 0.31 1.80

 MEAN 36.32 16.80 12.70 4.10 0.93 0.28 2.22

 HUB 43.73 -5.71 -9.30 3.59 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 312.4840 176.4285 257.9133 1088.8652 0.2870 -0.0698 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7928 9.2560 500.2964 488.4541 11.4533 34.3745 35.4000 1.0255

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 263.0504 64.3502 255.0580 1091.3395 0.2410 0.2523 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7921 9.4094 502.5770 488.2944 554.9116 0.0114 0.3666

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.0158 0.0000 261.0158 1091.4249 0.2392 0.2729 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4025 502.6628 488.4116 0.0000 0.0600 0.0370 0.2389

NASA/TM—2013-218094 O–43
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8769 9.7788 1.0473 508.1227 7.3110 216.8008 1.6806

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45612.816 0.561 127.959 484956.094 0.102433E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 4.013 EfDer = 0.993 SH = 0.121576E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.642 1584.377 9.779 508.122 1.000 1.000 0.980

 W Kg/sec = 22.565 Wdry = 49.582 WH2O = 0.060 lbm/sec H2O = 0.989g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.860 1600.783 1.380 0.249 53.388 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58761.895 38933.047 2.729 590.487 216.373 468.502 2.165

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.83 -0.08 238.83 0.22 0.34 287.06

 MEAN 18.08 0.00 -0.02 238.83 -0.08 238.83 0.22 0.32

 HUB 15.21 0.00 -0.02 238.83 -0.08 238.83 0.22 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.96 46.36 3.60 284.13 371.24 9.46 503.55 488.88 13.10

 MEAN 46.31 42.30 4.01 249.96 345.77 9.46 503.55 488.88 13.10

 HUB 41.38 37.84 3.54 210.30 318.28 9.46 503.55 488.88 13.10

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 279.08 99.02 260.93 1095.40 0.25 2.33 2.04 9.02

 MEAN 18.01 285.32 114.85 261.19 1095.20 0.26 2.40 2.13 7.35

 HUB 15.22 308.31 163.20 261.58 1095.01 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.33 318.88 183.31 0.29 2023.72 0.92 0.91

 MEAN 249.01 293.63 134.16 0.27 2069.91 0.92 0.91 0.91 1.27

 HUB 210.48 265.82 47.28 0.24 2485.60 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.07 1.03 9.63 512.60 1.01 506.37 491.63 12.32

 MEAN 10.07 1.03 9.62 512.71 1.01 506.19 491.71 12.38

 HUB 10.13 1.04 9.60 513.63 1.01 506.01 492.33 12.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 20.78 35.09 31.50 3.59 0.93 0.24 1.40

 MEAN 23.74 27.19 23.50 3.69 0.92 0.25 1.63

 HUB 31.96 10.25 6.50 3.75 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 315.7834 115.1715 294.0317 1093.9001 0.2887 -0.1851 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0861 9.5270 504.9942 492.0417 12.9125 21.3902 30.6000 9.2098

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 290.7225 61.6352 284.1138 1095.2186 0.2654 -0.0157 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0815 9.6063 506.2113 491.9185 491.5697 0.0198 0.1775

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 301.0327 0.0000 301.0327 1094.6866 0.2750 0.0458 0.5911

NASA/TM—2013-218094 O–44
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5527 505.7231 492.0096 0.0000 0.0600 0.0640 -0.1282

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8202 10.0604 1.0288 512.9789 4.8564 291.4474 2.2593

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30329.250 0.380 85.083 449351.781 0.128708E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.552 EfDer = 0.958 SH = 0.137285E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.642 1584.377 10.060 512.979 1.000 1.000 0.980

 W Kg/sec = 22.565 Wdry = 49.574 WH2O = 0.068 lbm/sec H2O = 1.135g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.135 1593.188 1.379 0.250 53.393 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57840.891 38930.637 2.581 545.479 211.343 424.468 2.008

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 254.49 -0.09 254.49 0.23 0.34 279.03

 MEAN 17.74 0.00 -0.02 254.49 -0.09 254.49 0.23 0.32

 HUB 15.05 0.00 -0.02 254.49 -0.09 254.49 0.23 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.49 46.36 1.13 277.49 376.58 9.70 507.80 492.01 12.90

 MEAN 43.95 43.40 0.55 245.26 353.49 9.70 507.80 492.01 12.90

 HUB 39.28 38.84 0.44 208.09 328.79 9.70 507.80 492.01 12.90

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 288.70 76.83 278.29 1098.94 0.26 2.26 1.98 8.75

 MEAN 17.51 294.87 97.71 278.21 1099.08 0.27 2.34 2.07 6.78

 HUB 14.85 317.96 153.75 278.32 1099.22 0.29 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 273.90 341.00 197.07 0.31 1523.82 0.92 0.88

 MEAN 242.05 313.42 144.34 0.29 1712.11 0.92 0.88 0.88 1.21

 HUB 205.32 283.06 51.57 0.26 2284.45 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.27 1.02 9.80 516.35 1.01 509.68 494.08 12.46

 MEAN 10.30 1.02 9.80 516.77 1.01 509.81 494.33 12.40

 HUB 10.38 1.03 9.80 518.03 1.01 509.94 495.13 12.34

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 15.43 35.30 31.50 3.80 0.93 0.17 1.40

 MEAN 19.35 27.42 23.50 3.92 0.90 0.20 1.62

 HUB 28.92 10.50 6.50 4.00 0.90 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 328.0626 98.3504 312.9733 1097.5906 0.2989 -0.1991 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3123 9.7011 508.4381 494.6931 12.9880 17.4451 31.5000 14.0549

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 314.5309 68.6128 306.9560 1098.3434 0.2864 -0.1200 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.3019 9.7397 509.1341 494.6129 451.3937 0.0302 0.1317

 

NASA/TM—2013-218094 O–45
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 320.2190 0.0000 320.2190 1098.0294 0.2916 -0.0208 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6884 508.8453 494.6620 0.0000 0.0600 0.0943 -0.2194

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7122 10.2688 1.0207 517.0515 4.0727 329.8331 2.5568

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25447.469 0.339 71.388 455441.313 0.144226E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.562 EfDer = 0.903 SH = 0.152706E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.642 1584.377 10.269 517.051 1.000 1.000 0.980

 W Kg/sec = 22.565 Wdry = 49.566 WH2O = 0.076 lbm/sec H2O = 1.275g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.950 1586.901 1.379 0.250 53.398 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57273.742 38928.273 2.469 513.330 207.894 395.845 1.904

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 267.77 -0.09 267.77 0.24 0.34 266.71

 MEAN 16.97 0.00 -0.02 267.77 -0.09 267.77 0.24 0.32

 HUB 14.32 0.00 -0.02 267.77 -0.09 267.77 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.85 46.36 -1.51 266.29 377.71 9.86 511.31 494.59 12.80

 MEAN 41.24 43.80 -2.56 234.64 356.09 9.86 511.32 494.59 12.80

 HUB 36.49 37.84 -1.35 197.99 333.08 9.86 511.31 494.59 12.80

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 296.61 53.19 291.80 1101.66 0.27 2.16 1.89 8.34

 MEAN 16.57 301.46 77.00 291.46 1102.06 0.27 2.24 1.97 6.35

 HUB 13.89 322.19 137.43 291.40 1102.45 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 261.04 358.26 207.85 0.33 1005.93 0.92 0.83

 MEAN 229.16 328.78 152.15 0.30 1277.80 0.92 0.83 0.83 1.15

 HUB 192.05 296.48 54.62 0.27 1910.24 0.92 0.83

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.40 1.01 9.90 519.28 1.00 512.24 495.98 12.69

 MEAN 10.44 1.02 9.92 519.88 1.01 512.61 496.32 12.55

 HUB 10.52 1.02 9.93 521.28 1.01 512.97 497.16 12.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.33 35.46 31.50 3.96 0.93 0.10 1.40

 MEAN 14.80 27.57 23.50 4.07 0.89 0.14 1.62

 HUB 25.25 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.903 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 329.4253 77.4360 320.1947 1100.8204 0.2993 -0.1637 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4494 9.8287 511.4630 496.6493 13.0327 13.5954 32.4000 18.8046

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 327.8424 73.5255 319.4912 1100.9120 0.2978 -0.1752 2.2705

 

NASA/TM—2013-218094 O–46
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4331 9.8193 511.5463 496.6337 432.2457 0.0400 0.0948

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 326.1107 0.0000 326.1107 1101.0088 0.2962 -0.0746 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7824 511.6371 496.6114 0.0000 0.0600 0.1248 -0.2433

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5278 10.3873 1.0115 520.1440 3.0926 403.3354 3.1266

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 19332.834 0.284 54.235 474748.969 0.159379E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.427 EfDer = 0.841 SH = 0.167966E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.642 1584.377 10.387 520.144 1.000 1.000 0.980

 W Kg/sec = 22.565 Wdry = 49.559 WH2O = 0.083 lbm/sec H2O = 1.410g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.351 1582.177 1.379 0.250 53.403 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 56960.273 38925.930 2.472 509.668 206.157 384.739 1.866

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 268.22 -0.09 268.22 0.24 0.33 252.94

 MEAN 15.91 0.00 -0.02 268.22 -0.09 268.22 0.24 0.31

 HUB 13.07 0.00 -0.02 268.22 -0.09 268.22 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.37 47.36 -3.99 253.30 368.98 9.98 514.39 496.48 12.73

 MEAN 39.37 44.80 -5.43 220.02 346.97 9.98 514.39 496.48 12.73

 HUB 33.98 38.84 -4.86 180.71 323.47 9.98 514.39 496.48 12.73

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.92 37.52 292.52 1104.26 0.27 2.05 1.78 7.43

 MEAN 15.50 298.33 60.30 292.17 1104.70 0.27 2.13 1.86 5.75

 HUB 12.59 315.40 118.86 292.14 1105.14 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 248.04 360.40 210.53 0.33 674.76 0.92 0.77

 MEAN 214.27 330.26 153.97 0.30 936.04 0.92 0.77 0.77 1.12

 HUB 174.07 297.31 55.21 0.27 1497.72 0.92 0.77

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.47 1.01 9.97 521.64 1.00 514.68 497.46 12.83

 MEAN 10.50 1.01 9.99 522.21 1.00 515.10 497.77 12.66

 HUB 10.57 1.02 10.00 523.46 1.01 515.50 498.49 12.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.31 35.74 31.50 4.24 0.93 0.06 1.40

 MEAN 11.66 27.79 23.50 4.29 0.88 0.10 1.64

 HUB 22.14 10.70 6.50 4.20 0.88 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.841 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.1004 61.4099 333.4934 1102.7032 0.3075 -0.2723 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.5054 9.8480 513.2406 498.1666 13.4117 10.4336 33.0000 22.5664

 

NASA/TM—2013-218094 O–47
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 347.8167 79.4242 338.6270 1102.1924 0.3156 -0.3972 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4665 9.7783 512.7618 498.1964 410.5396 0.0936 0.0667

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 338.7001 0.0000 338.7001 1102.7310 0.3071 -0.0896 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7891 513.2623 498.1414 0.0000 0.0600 0.1421 -0.3767

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3218 10.4410 1.0052 522.4345 2.2909 503.5690 3.9036

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14327.912 0.233 40.194 505919.219 0.174478E-02

 

Melt Ratio at Stator LE, Throat, TE

0.14793E-01 0.15037E-01 0.15746E-01

 trTOT = 1.0432 Tt4 = 522.4345 T1 = 500.8120

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 135050.28 378.8593 76.7937 1.1182 0.7226 6.5369 1.0432 37.3740

NASA/TM—2013-218094 O–48
10μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.246 EfDer = 0.956 SH = 0.445243E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.253 2469.930 4.265 477.913 1.000 1.000 0.980

 W Kg/sec = 11.933 Wdry = 26.241 WH2O = 0.012 lbm/sec H2O = 0.169g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.862 2573.149 1.381 0.249 53.363 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66489.250 20595.410 3.270 831.557 254.318 619.754 2.437

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 191.90 -0.07 191.90 0.18 0.46 463.23

 MEAN 17.06 0.00 -0.02 191.90 -0.07 191.90 0.18 0.39

 HUB 12.51 0.00 -0.02 191.90 -0.07 191.90 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.66 50.47 16.19 444.66 484.36 4.17 474.95 461.74 6.80

 MEAN 62.45 47.20 15.25 367.72 414.84 4.17 474.95 461.74 6.80

 HUB 54.57 38.62 15.95 269.64 331.01 4.17 474.95 461.74 6.80

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 399.15 305.59 256.78 1074.49 0.37 7.29 6.52 16.04

 MEAN 18.04 404.31 309.48 260.18 1071.35 0.38 7.43 6.80 12.53

 HUB 15.00 438.47 349.41 264.90 1067.48 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 444.66 292.03 139.07 0.27 6305.71 0.92 0.88

 MEAN 388.75 271.99 79.28 0.25 5582.85 0.92 0.88 0.88 1.75

 HUB 323.31 266.18 26.09 0.25 5241.95 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.92 1.15 4.47 499.75 1.05 486.95 475.02 6.13

 MEAN 4.84 1.13 4.39 497.25 1.04 484.11 473.76 6.76

 HUB 4.80 1.13 4.28 496.07 1.04 480.62 473.33 7.64

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.96 28.44 24.20 4.24 0.93 0.57 1.80

 MEAN 49.95 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 52.83 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 416.2867 308.8750 279.0893 1070.9380 0.3887 -0.0366 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8469 4.3732 483.7738 474.1170 7.0938 47.9001 35.4000 -12.5001

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 276.9406 67.7481 268.5262 1079.4784 0.2566 0.5104 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8352 4.6217 491.5297 473.6330 554.9116 0.0350 0.6028

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 275.7862 0.0000 275.7862 1079.5156 0.2555 0.4818 1.3089

NASA/TM—2013-218094 O–49
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6015 491.5814 473.8375 0.0000 0.0600 0.0840 0.4673

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8183 4.8122 1.1284 497.6864 19.7746 168.9491 1.3097

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 123162.047 0.623 182.717 266568.250 0.772750E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.793 EfDer = 0.960 SH = 0.114390E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.253 2469.930 4.812 497.686 1.000 1.000 0.980

 W Kg/sec = 11.933 Wdry = 26.222 WH2O = 0.030 lbm/sec H2O = 0.466g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.554 2521.535 1.380 0.249 53.385 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62053.270 20589.756 2.566 590.487 230.090 468.502 2.036

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 252.20 -0.09 252.20 0.23 0.47 452.18

 MEAN 18.08 0.00 -0.02 252.20 -0.09 252.20 0.23 0.43

 HUB 15.21 0.00 -0.02 252.20 -0.09 252.20 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.35 46.36 13.99 442.94 509.78 4.64 492.59 474.76 9.28

 MEAN 57.09 42.30 14.79 389.66 464.23 4.64 492.59 474.76 9.28

 HUB 52.44 37.84 14.60 327.84 413.69 4.64 492.59 474.76 9.28

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 367.18 253.67 265.46 1093.83 0.34 2.33 2.04 9.02

 MEAN 18.01 367.07 250.67 268.15 1091.35 0.34 2.40 2.13 7.35

 HUB 15.22 389.35 279.43 271.14 1088.90 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 440.14 324.41 186.47 0.30 5181.63 0.92 0.88

 MEAN 388.19 301.36 137.52 0.28 4516.06 0.92 0.88 0.88 1.70

 HUB 328.12 275.47 48.69 0.25 4255.10 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.12 4.99 515.59 1.04 504.78 484.18 6.57

 MEAN 5.31 1.10 4.92 513.29 1.03 502.49 483.11 7.06

 HUB 5.28 1.10 4.84 512.39 1.03 500.24 482.84 7.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.70 35.09 31.50 3.59 0.93 0.54 1.40

 MEAN 43.07 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 45.86 10.18 6.50 3.68 0.95 0.51 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 392.8447 251.3700 301.8942 1090.1259 0.3604 -0.1085 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3227 4.8719 501.3894 483.5150 7.3765 39.7822 30.6000 -9.1822

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 292.0391 61.9144 285.4005 1096.1195 0.2664 0.3619 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3167 5.0643 506.9218 482.9950 491.5697 0.0246 0.4589

 

NASA/TM—2013-218094 O–50
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 302.7122 0.0000 302.7122 1095.5566 0.2763 0.3519 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0305 506.4135 483.1243 0.0000 0.0600 0.0638 0.2799

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8351 5.3006 1.1015 513.7553 16.0700 190.4094 1.4760

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 100284.547 0.518 148.777 242152.328 0.129402E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.812 EfDer = 0.975 SH = 0.149847E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.253 2469.930 5.301 513.755 1.000 1.000 0.980

 W Kg/sec = 11.933 Wdry = 26.213 WH2O = 0.039 lbm/sec H2O = 0.651g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.457 2481.788 1.379 0.250 53.397 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58162.883 20586.879 2.570 545.479 212.287 424.468 2.000

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 255.90 -0.09 255.90 0.23 0.46 434.66

 MEAN 17.74 0.00 -0.02 255.90 -0.09 255.90 0.23 0.42

 HUB 15.05 0.00 -0.02 255.90 -0.09 255.90 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.40 46.36 13.04 432.59 502.69 5.11 508.51 483.39 7.22

 MEAN 56.21 43.40 12.81 382.34 460.15 5.11 508.51 483.39 7.22

 HUB 51.74 38.84 12.90 324.39 413.25 5.11 508.51 483.39 7.22

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 358.95 237.30 269.32 1109.76 0.32 2.26 1.98 8.75

 MEAN 17.51 360.86 237.50 271.68 1107.63 0.33 2.34 2.07 6.78

 HUB 14.85 385.10 270.31 274.29 1105.55 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.99 329.42 189.69 0.30 4702.59 0.92 0.89

 MEAN 377.34 305.56 139.84 0.28 4159.41 0.92 0.89 0.89 1.65

 HUB 320.08 278.77 49.77 0.25 4015.44 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.86 1.11 5.46 529.98 1.03 519.67 491.32 5.43

 MEAN 5.80 1.09 5.39 528.11 1.03 517.68 490.53 5.75

 HUB 5.78 1.09 5.32 527.61 1.03 515.74 490.47 6.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.38 35.16 31.50 3.66 0.93 0.51 1.40

 MEAN 41.16 27.24 23.50 3.74 0.94 0.49 1.62

 HUB 44.58 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 387.8134 239.0609 305.3671 1106.3734 0.3505 -0.1164 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8092 5.3424 516.5319 490.9244 5.9997 38.0561 31.5000 -6.5561

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 300.4559 65.5424 293.2200 1111.5109 0.2703 0.3107 2.3726

 

NASA/TM—2013-218094 O–51
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8053 5.5219 521.3440 490.4623 451.3937 0.0191 0.4339

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 305.5421 0.0000 305.5421 1111.2351 0.2750 0.3369 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4996 521.0978 490.5746 0.0000 0.0600 0.0510 0.2581

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8555 5.7918 1.0927 528.5681 14.8135 195.7673 1.5176

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92559.828 0.508 137.317 240673.438 0.167903E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.229 EfDer = 0.985 SH = 0.192205E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.253 2469.930 5.792 528.568 1.000 1.000 0.980

 W Kg/sec = 11.933 Wdry = 26.202 WH2O = 0.050 lbm/sec H2O = 0.888g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.261 2446.766 1.379 0.250 53.411 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54737.297 20583.441 2.604 513.330 197.117 395.845 2.008

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 255.91 -0.09 255.91 0.23 0.44 411.23

 MEAN 16.97 0.00 -0.02 255.91 -0.09 255.91 0.23 0.40

 HUB 14.32 0.00 -0.02 255.91 -0.09 255.91 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.35 46.36 11.99 415.13 487.75 5.59 523.33 490.84 5.92

 MEAN 55.03 43.80 11.23 365.79 446.49 5.59 523.33 490.84 5.92

 HUB 50.35 37.84 12.51 308.66 401.02 5.59 523.33 490.84 5.92

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.57 217.49 268.54 1123.99 0.31 2.16 1.89 8.34

 MEAN 16.57 347.40 217.77 270.67 1122.07 0.31 2.24 1.97 6.35

 HUB 13.89 370.12 249.92 272.99 1120.19 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.94 328.65 189.45 0.29 4107.90 0.92 0.90

 MEAN 357.24 304.49 139.47 0.27 3610.81 0.92 0.90 0.90 1.61

 HUB 299.39 277.44 49.46 0.25 3472.70 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.32 1.09 5.92 542.72 1.03 533.18 497.36 4.71

 MEAN 6.25 1.08 5.86 541.01 1.02 531.36 496.68 4.95

 HUB 6.23 1.08 5.79 540.54 1.02 529.58 496.64 5.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.00 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.82 27.26 23.50 3.76 0.94 0.47 1.62

 HUB 42.47 10.27 6.50 3.77 0.94 0.47 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 368.8883 218.9958 296.8492 1121.1815 0.3290 -0.0921 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2634 5.8174 530.5490 497.0092 5.1019 36.4175 32.4000 -4.0175

 

NASA/TM—2013-218094 O–52
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 298.0639 66.8470 290.4713 1125.1581 0.2649 0.2738 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2614 5.9676 534.3242 496.6453 432.2457 0.0148 0.4125

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 295.6942 0.0000 295.6942 1125.2633 0.2628 0.3230 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9615 534.4364 496.7211 0.0000 0.0600 0.0421 0.2589

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8689 6.2501 1.0791 541.4225 12.8559 210.9852 1.6355

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 80444.711 0.486 119.344 246274.500 0.212805E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.13875E-02 0.14485E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.779 EfDer = 0.992 SH = 0.238938E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.253 2469.930 6.250 541.422 1.000 1.000 0.980

 W Kg/sec = 11.933 Wdry = 26.190 WH2O = 0.063 lbm/sec H2O = 1.166g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.082 2417.546 1.378 0.250 53.426 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51817.965 20579.645 2.756 509.668 184.927 384.739 2.080

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 244.00 -0.08 244.00 0.22 0.41 386.49

 MEAN 15.91 0.00 -0.02 244.00 -0.08 244.00 0.22 0.37

 HUB 13.07 0.00 -0.02 244.00 -0.08 244.00 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.29 47.36 10.93 394.87 464.25 6.05 536.67 496.95 5.07

 MEAN 54.58 44.80 9.78 342.99 421.00 6.05 536.67 496.95 5.07

 HUB 49.11 38.84 10.27 281.71 372.76 6.05 536.67 496.95 5.07

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 328.10 204.39 256.65 1136.74 0.29 2.05 1.78 7.43

 MEAN 15.50 327.01 199.98 258.73 1134.76 0.29 2.13 1.86 5.75

 HUB 12.59 343.91 224.02 260.94 1132.81 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.68 314.80 182.29 0.28 3668.34 0.92 0.91

 MEAN 334.04 291.39 134.06 0.26 3100.61 0.92 0.91 0.91 1.60

 HUB 271.37 265.20 47.35 0.23 2821.47 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.75 1.08 6.37 554.04 1.02 545.45 502.48 4.16

 MEAN 6.67 1.07 6.30 552.09 1.02 543.55 501.73 4.37

 HUB 6.63 1.06 6.22 551.13 1.02 541.69 501.46 4.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.53 35.38 31.50 3.88 0.93 0.48 1.40

 MEAN 37.70 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.65 10.29 6.50 3.79 0.94 0.44 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 358.0349 203.6507 294.4748 1133.3076 0.3159 -0.1720 2.0437

 

NASA/TM—2013-218094 O–53
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6731 6.2336 542.1899 502.0566 4.5533 34.6667 33.0000 -1.6667

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 300.9044 68.7118 292.9542 1136.4375 0.2648 0.1560 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6711 6.3584 545.1926 501.7478 410.5396 0.0254 0.3882

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 292.7007 0.0000 292.7007 1136.8260 0.2575 0.3116 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3706 545.5765 501.7802 0.0000 0.0600 0.0376 0.1881

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8790 6.6664 1.0666 552.4117 10.9982 230.5111 1.7869

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68924.781 0.461 102.254 258253.188 0.257040E-02

 

Melt Ratio at Stator LE, Throat, TE

0.11292E+00 0.13291E+00 0.19475E+00

 trTOT = 1.1559 Tt4 = 552.4117 T1 = 477.9130

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 465375.94 690.4097 86.8619 1.5632 0.8383 15.2459 1.1559 37.3740

NASA/TM—2013-218094 O–54
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.343 EfDer = 0.956 SH = 0.406892E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.295 2391.942 4.199 471.469 1.000 1.000 0.980

 W Kg/sec = 11.498 Wdry = 25.285 WH2O = 0.010 lbm/sec H2O = 0.155g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.424 2508.875 1.381 0.249 53.361 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 64124.238 19844.852 3.364 831.557 247.172 619.754 2.507

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 185.07 -0.06 185.07 0.18 0.44 451.66

 MEAN 17.06 0.00 -0.02 185.07 -0.06 185.07 0.18 0.38

 HUB 12.51 0.00 -0.02 185.07 -0.06 185.07 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.75 50.47 16.28 430.62 468.77 4.11 468.72 457.91 8.08

 MEAN 62.54 47.20 15.34 356.11 401.38 4.11 468.72 457.91 8.08

 HUB 54.68 38.62 16.06 261.13 320.11 4.11 468.72 457.91 8.08

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 386.47 296.19 248.25 1066.77 0.36 7.29 6.52 16.04

 MEAN 18.04 391.30 299.89 251.36 1063.81 0.37 7.43 6.80 12.53

 HUB 15.00 424.03 338.27 255.67 1060.17 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 430.62 282.31 134.43 0.26 6111.73 0.92 0.87

 MEAN 376.48 262.77 76.58 0.25 5409.96 0.92 0.87 0.87 1.75

 HUB 313.10 256.91 25.17 0.24 5074.91 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.81 1.14 4.40 491.97 1.04 479.97 470.99 7.25

 MEAN 4.73 1.13 4.32 489.62 1.04 477.31 469.73 7.98

 HUB 4.70 1.12 4.22 488.49 1.04 474.05 469.28 8.98

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.03 28.44 24.20 4.24 0.93 0.57 1.80

 MEAN 50.03 16.95 12.70 4.25 0.95 0.52 2.22

 HUB 52.92 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 402.8125 299.3102 269.5762 1063.4277 0.3788 -0.0366 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7428 4.3012 476.9947 470.0779 8.3533 47.9920 35.4000 -12.5919

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 268.0155 65.5648 259.8723 1071.4825 0.2501 0.5113 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7321 4.5332 484.2565 469.6273 554.9116 0.0343 0.6031

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 266.8700 0.0000 266.8700 1071.5186 0.2491 0.4815 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5138 484.3062 469.8202 0.0000 0.0600 0.0846 0.4670

NASA/TM—2013-218094 O–55
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8172 4.7101 1.1217 490.0243 18.5562 168.5572 1.3066

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 115546.492 0.623 165.170 259255.203 0.689339E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.807 EfDer = 0.960 SH = 0.100984E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.295 2391.942 4.710 490.024 1.000 1.000 0.980

 W Kg/sec = 11.498 Wdry = 25.270 WH2O = 0.026 lbm/sec H2O = 0.410g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.732 2460.934 1.380 0.249 53.381 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60061.340 19840.150 2.627 590.487 224.734 468.502 2.085 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 244.11 -0.08 244.11 0.23 0.46 441.31

 MEAN 18.08 0.00 -0.02 244.11 -0.08 244.11 0.23 0.42

 HUB 15.21 0.00 -0.02 244.11 -0.08 244.11 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.36 46.36 14.00 428.95 493.62 4.55 485.25 470.68 10.85

 MEAN 57.11 42.30 14.81 377.36 449.50 4.55 485.25 470.68 10.85

 HUB 52.45 37.84 14.61 317.49 400.55 4.55 485.25 470.68 10.85

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 355.73 245.34 257.59 1085.02 0.33 2.33 2.04 9.02

 MEAN 18.01 355.65 242.59 260.06 1082.68 0.33 2.40 2.13 7.35

 HUB 15.22 377.24 270.63 262.81 1080.38 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.24 314.77 180.90 0.29 5011.55 0.92 0.88

 MEAN 375.93 292.26 133.34 0.27 4370.56 0.92 0.88 0.88 1.69

 HUB 317.76 267.00 47.13 0.25 4121.01 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.25 1.11 4.87 506.80 1.03 496.65 479.98 7.75

 MEAN 5.17 1.10 4.81 504.66 1.03 494.51 478.93 8.32

 HUB 5.15 1.09 4.74 503.82 1.03 492.41 478.65 8.92

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.60 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.01 27.15 23.50 3.65 0.95 0.52 1.63

 HUB 45.84 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 380.5927 243.2715 292.6941 1081.5264 0.3519 -0.1086 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1849 4.7650 493.4789 479.3183 8.6788 39.7315 30.6000 -9.1315

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 283.5291 60.1102 277.0839 1087.1711 0.2608 0.3603 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1796 4.9436 498.6469 478.8366 491.5697 0.0240 0.4572

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 293.8228 0.0000 293.8228 1086.6399 0.2704 0.3502 0.5911

NASA/TM—2013-218094 O–56
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9121 498.1707 478.9595 0.0000 0.0600 0.0635 0.2780

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8350 5.1644 1.0964 505.0911 15.0679 190.4582 1.4764

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93985.648 0.517 134.349 235728.641 0.113919E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.739 EfDer = 0.975 SH = 0.131603E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.295 2391.942 5.164 505.091 1.000 1.000 0.980

 W Kg/sec = 11.498 Wdry = 25.262 WH2O = 0.033 lbm/sec H2O = 0.568g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.050 2423.951 1.380 0.249 53.391 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56480.973 19837.760 2.621 545.479 208.138 424.468 2.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 248.50 -0.09 248.50 0.23 0.45 424.53

 MEAN 17.74 0.00 -0.02 248.50 -0.09 248.50 0.23 0.41

 HUB 15.05 0.00 -0.02 248.50 -0.09 248.50 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.33 46.36 12.97 418.93 487.17 4.98 500.14 479.21 8.52

 MEAN 56.14 43.40 12.74 370.27 446.00 4.98 500.14 479.21 8.52

 HUB 51.66 38.84 12.82 314.15 400.62 4.98 500.14 479.21 8.52

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 348.03 228.94 262.13 1100.03 0.32 2.26 1.98 8.75

 MEAN 17.51 349.99 229.43 264.31 1098.04 0.32 2.34 2.07 6.78

 HUB 14.85 373.60 261.62 266.71 1096.08 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 413.51 320.59 184.57 0.29 4536.97 0.92 0.89

 MEAN 365.43 297.24 136.00 0.27 4017.98 0.92 0.89 0.89 1.64

 HUB 309.97 271.06 48.35 0.25 3886.33 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.69 1.10 5.31 520.26 1.03 510.56 487.02 6.45

 MEAN 5.62 1.09 5.25 518.53 1.03 508.71 486.25 6.83

 HUB 5.61 1.09 5.18 518.09 1.03 506.91 486.20 7.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.13 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.96 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.45 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 376.2104 230.9315 296.9931 1096.8375 0.3430 -0.1171 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6355 5.2009 507.6246 486.6314 7.1148 37.8674 31.5000 -6.3674

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 292.5745 63.8232 285.5284 1101.6628 0.2656 0.3063 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6322 5.3664 512.1041 486.2028 451.3937 0.0184 0.4301

 

NASA/TM—2013-218094 O–57
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 297.4804 0.0000 297.4804 1101.4023 0.2701 0.3334 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3457 511.8726 486.3109 0.0000 0.0600 0.0502 0.2537

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8563 5.6197 1.0882 518.9586 13.8683 196.3914 1.5224

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86597.555 0.506 123.788 234578.797 0.147230E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.075 EfDer = 0.986 SH = 0.168295E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.295 2391.942 5.620 518.958 1.000 1.000 0.980

 W Kg/sec = 11.498 Wdry = 25.253 WH2O = 0.043 lbm/sec H2O = 0.769g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.184 2391.346 1.379 0.250 53.403 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53313.793 19834.893 2.647 513.330 193.932 395.845 2.041

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 249.26 -0.09 249.26 0.23 0.43 401.91

 MEAN 16.97 0.00 -0.02 249.26 -0.09 249.26 0.23 0.39

 HUB 14.32 0.00 -0.02 249.26 -0.09 249.26 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.21 46.36 11.85 402.03 473.10 5.43 513.99 486.56 7.04

 MEAN 54.87 43.80 11.07 354.24 433.22 5.43 513.99 486.56 7.04

 HUB 50.18 37.84 12.34 298.91 389.27 5.43 513.99 486.56 7.04

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 335.37 209.24 262.09 1113.43 0.30 2.16 1.89 8.34

 MEAN 16.57 337.33 209.93 264.05 1111.64 0.30 2.24 1.97 6.35

 HUB 13.89 359.59 241.76 266.19 1109.89 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 394.09 320.72 184.86 0.29 3952.06 0.92 0.90

 MEAN 345.96 297.02 136.03 0.27 3480.82 0.92 0.90 0.90 1.60

 HUB 289.93 270.51 48.17 0.24 3359.34 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.10 1.09 5.74 532.16 1.03 523.16 492.96 5.63

 MEAN 6.04 1.08 5.68 530.58 1.02 521.48 492.31 5.91

 HUB 6.03 1.07 5.61 530.18 1.02 519.83 492.27 6.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.60 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.49 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.25 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.3277 211.1112 289.5355 1110.7892 0.3226 -0.0930 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0547 5.6394 520.7040 492.6257 6.0918 36.0972 32.4000 -3.6972

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 291.0168 65.2665 283.6036 1114.5074 0.2611 0.2668 2.2705

 

NASA/TM—2013-218094 O–58
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0531 5.7768 524.2001 492.2886 432.2457 0.0143 0.4068

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 288.6818 0.0000 288.6818 1114.6121 0.2590 0.3175 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7712 524.3087 492.3686 0.0000 0.0600 0.0413 0.2524

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8700 6.0427 1.0753 530.9732 12.0153 212.2728 1.6455

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75122.000 0.484 107.384 240309.641 0.186470E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.551 EfDer = 0.993 SH = 0.211278E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.295 2391.942 6.043 530.973 1.000 1.000 0.980

 W Kg/sec = 11.498 Wdry = 25.242 WH2O = 0.053 lbm/sec H2O = 1.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.260 2364.136 1.379 0.250 53.417 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50605.133 19831.529 2.793 509.668 182.483 384.739 2.108

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5 

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 238.29 -0.08 238.29 0.21 0.40 377.95

 MEAN 15.91 0.00 -0.02 238.29 -0.08 238.29 0.21 0.37

 HUB 13.07 0.00 -0.02 238.29 -0.08 238.29 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.08 47.36 10.72 382.40 450.64 5.86 526.44 492.62 6.13

 MEAN 54.35 44.80 9.55 332.16 408.86 5.86 526.44 492.62 6.13

 HUB 48.87 38.84 10.03 272.82 362.30 5.86 526.44 492.62 6.13

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 318.63 196.16 251.09 1125.44 0.28 2.05 1.78 7.43

 MEAN 15.50 317.86 192.41 253.01 1123.60 0.28 2.13 1.86 5.75

 HUB 12.59 334.57 216.53 255.05 1121.78 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 374.47 307.97 178.31 0.27 3520.65 0.92 0.91

 MEAN 323.49 284.95 131.08 0.25 2983.25 0.92 0.91 0.91 1.59

 HUB 262.80 259.22 46.26 0.23 2727.24 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.50 1.08 6.15 542.72 1.02 534.60 498.08 5.10

 MEAN 6.43 1.06 6.08 540.92 1.02 532.85 497.35 5.35

 HUB 6.39 1.06 6.02 540.07 1.02 531.13 497.10 5.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.00 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.25 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.33 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 348.2561 195.9417 287.9047 1122.1980 0.3103 -0.1737 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4313 6.0219 531.5491 497.6789 5.5833 34.2384 33.0000 -1.2384

 

NASA/TM—2013-218094 O–59
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.4426 67.2362 286.6631 1125.1061 0.2617 0.1463 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4297 6.1350 534.3113 497.3968 410.5396 0.0247 0.3811

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.4330 0.0000 286.4330 1125.4860 0.2545 0.3041 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1464 534.6818 497.4523 0.0000 0.0600 0.0371 0.1783

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 6.4252 1.0633 541.2334 10.2628 232.5166 1.8025

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64257.465 0.458 91.854 252259.391 0.231100E-02

 

Melt Ratio at Stator LE, Throat, TE

0.85422E-02 0.14060E-01 0.36277E-01

 trTOT = 1.1480 Tt4 = 541.2334 T1 = 471.4691

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 435509.16 622.5456 84.4236 1.5301 0.8388 15.3429 1.1480 37.3740

NASA/TM—2013-218094 O–60
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.391 EfDer = 0.955 SH = 0.375744E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.855 2361.088 4.337 469.497 1.000 1.000 0.980

 W Kg/sec = 11.752 Wdry = 25.845 WH2O = 0.010 lbm/sec H2O = 0.148g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.373 2481.708 1.381 0.249 53.360 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 63167.656 20284.199 3.407 831.557 244.092 619.754 2.539

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 182.31 -0.06 182.31 0.17 0.44 446.77

 MEAN 17.06 0.00 -0.02 182.31 -0.06 182.31 0.17 0.38

 HUB 12.51 0.00 -0.02 182.31 -0.06 182.31 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.79 50.47 16.32 425.07 462.57 4.25 466.83 456.95 8.40

 MEAN 62.59 47.20 15.39 351.51 396.03 4.25 466.83 456.95 8.40

 HUB 54.74 38.62 16.12 257.76 315.77 4.25 466.83 456.95 8.40

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 381.44 292.53 244.79 1064.35 0.36 7.29 6.52 16.04

 MEAN 18.04 386.13 296.14 247.78 1061.47 0.36 7.43 6.80 12.53

 HUB 15.00 418.25 333.86 251.94 1057.91 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 425.07 278.36 132.54 0.26 6036.17 0.92 0.87

 MEAN 371.62 259.03 75.48 0.24 5342.20 0.92 0.87 0.87 1.76

 HUB 309.07 253.15 24.80 0.24 5008.74 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.54 489.48 1.04 477.79 469.98 7.54

 MEAN 4.88 1.12 4.46 487.19 1.04 475.21 468.71 8.29

 HUB 4.84 1.12 4.35 486.08 1.04 472.03 468.24 9.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.08 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 50.08 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.96 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.4477 295.5615 265.7218 1061.0918 0.3746 -0.0365 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8858 4.4404 474.8968 469.0467 8.6727 48.0432 35.4000 -12.6432

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 264.3923 64.6784 256.3591 1068.9552 0.2473 0.5119 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8752 4.6747 481.9697 468.6257 554.9116 0.0341 0.6035

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 263.2511 0.0000 263.2511 1068.9908 0.2463 0.4815 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6549 482.0183 468.8057 0.0000 0.0600 0.0849 0.4670

NASA/TM—2013-218094 O–61
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8167 4.8528 1.1189 487.5832 18.0872 168.3549 1.3051

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 112611.430 0.623 164.536 265726.188 0.631536E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.822 EfDer = 0.960 SH = 0.922339E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.855 2361.088 4.853 487.583 1.000 1.000 0.980

 W Kg/sec = 11.752 Wdry = 25.831 WH2O = 0.024 lbm/sec H2O = 0.388g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.935 2435.263 1.380 0.249 53.378 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59252.477 20279.844 2.655 590.487 222.389 468.502 2.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 240.82 -0.08 240.82 0.23 0.46 436.71

 MEAN 18.08 0.00 -0.02 240.82 -0.08 240.82 0.23 0.41

 HUB 15.21 0.00 -0.02 240.82 -0.08 240.82 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.38 46.36 14.02 423.42 487.19 4.69 482.93 469.61 11.25

 MEAN 57.12 42.30 14.82 372.49 443.63 4.69 482.93 469.61 11.25

 HUB 52.47 37.84 14.63 313.39 395.30 4.69 482.93 469.61 11.25

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 351.19 242.11 254.39 1082.17 0.32 2.33 2.04 9.02

 MEAN 18.01 351.09 239.43 256.77 1079.89 0.33 2.40 2.13 7.35

 HUB 15.22 372.39 267.15 259.43 1077.64 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 420.74 310.84 178.63 0.29 4945.62 0.92 0.88

 MEAN 371.08 288.56 131.65 0.27 4313.69 0.92 0.88 0.88 1.69

 HUB 313.66 263.56 46.51 0.24 4068.08 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.11 5.02 503.93 1.03 494.04 478.91 8.08

 MEAN 5.32 1.10 4.95 501.84 1.03 491.95 477.85 8.67

 HUB 5.29 1.09 4.88 501.03 1.03 489.91 477.57 9.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.58 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 43.00 27.14 23.50 3.64 0.95 0.52 1.63

 HUB 45.84 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.6909 240.1058 288.9513 1078.7633 0.3483 -0.1086 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3313 4.9079 490.9478 478.2308 9.0368 39.7251 30.6000 -9.1251

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 280.0620 59.3751 273.6957 1084.2708 0.2583 0.3599 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3260 5.0879 495.9766 477.7802 491.5697 0.0237 0.4568

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 290.2018 0.0000 290.2018 1083.7521 0.2678 0.3496 0.5911

NASA/TM—2013-218094 O–62
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0560 495.5131 477.8955 0.0000 0.0600 0.0635 0.2775

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8349 5.3107 1.0944 502.2659 14.6837 190.4227 1.4761

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91564.383 0.517 133.784 241702.063 0.103962E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.718 EfDer = 0.976 SH = 0.120020E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.855 2361.088 5.311 502.266 1.000 1.000 0.980

 W Kg/sec = 11.752 Wdry = 25.824 WH2O = 0.031 lbm/sec H2O = 0.536g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.424 2399.404 1.380 0.249 53.387 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55795.949 20277.629 2.644 545.479 206.292 424.468 2.058

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 245.49 -0.08 245.49 0.23 0.44 420.23

 MEAN 17.74 0.00 -0.02 245.49 -0.08 245.49 0.23 0.41

 HUB 15.05 0.00 -0.02 245.49 -0.08 245.49 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.31 46.36 12.95 413.53 480.98 5.13 497.44 478.14 8.88

 MEAN 56.12 43.40 12.72 365.49 440.35 5.13 497.44 478.14 8.88

 HUB 51.64 38.84 12.80 310.10 395.57 5.13 497.44 478.14 8.88

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 343.70 225.71 259.20 1096.82 0.31 2.26 1.98 8.75

 MEAN 17.51 345.65 226.28 261.30 1094.88 0.32 2.34 2.07 6.78

 HUB 14.85 369.00 258.19 263.62 1092.98 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 408.17 316.98 182.46 0.29 4473.01 0.92 0.89

 MEAN 360.71 293.85 134.44 0.27 3962.82 0.92 0.89 0.89 1.64

 HUB 305.98 267.92 47.78 0.25 3835.40 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.83 1.10 5.46 517.04 1.03 507.57 485.93 6.76

 MEAN 5.77 1.09 5.39 515.35 1.03 505.78 485.16 7.14

 HUB 5.76 1.08 5.33 514.93 1.03 504.02 485.10 7.54

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.05 35.14 31.50 3.64 0.93 0.51 1.40

 MEAN 40.89 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.40 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.5668 227.7612 293.5758 1093.7061 0.3397 -0.1172 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7847 5.3466 504.7121 485.5310 7.4453 37.8049 31.5000 -6.3049

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 289.3527 63.1203 282.3841 1098.4093 0.2634 0.3048 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7815 5.5129 509.0652 485.1295 451.3937 0.0182 0.4287

 

NASA/TM—2013-218094 O–63
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 294.1857 0.0000 294.1857 1098.1548 0.2679 0.3321 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4921 508.8396 485.2314 0.0000 0.0600 0.0499 0.2522

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8566 5.7689 1.0863 515.7720 13.5069 196.5858 1.5239

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 84310.563 0.506 123.186 240643.891 0.134213E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.021 EfDer = 0.986 SH = 0.153371E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.855 2361.088 5.769 515.772 1.000 1.000 0.980

 W Kg/sec = 11.752 Wdry = 25.815 WH2O = 0.040 lbm/sec H2O = 0.724g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.697 2367.780 1.379 0.250 53.398 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52732.254 20274.963 2.667 513.330 192.485 395.845 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 246.54 -0.08 246.54 0.22 0.42 397.95

 MEAN 16.97 0.00 -0.02 246.54 -0.08 246.54 0.22 0.39

 HUB 14.32 0.00 -0.02 246.54 -0.08 246.54 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.15 46.36 11.79 396.84 467.26 5.57 510.91 485.47 7.38

 MEAN 54.82 43.80 11.02 349.67 427.91 5.57 510.91 485.47 7.38

 HUB 50.13 37.84 12.29 295.05 384.56 5.57 510.91 485.47 7.38

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.31 206.04 259.44 1109.90 0.30 2.16 1.89 8.34

 MEAN 16.57 333.31 206.88 261.34 1108.16 0.30 2.24 1.97 6.35

 HUB 13.89 355.35 238.52 263.41 1106.45 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 389.01 317.47 182.97 0.29 3891.74 0.92 0.90

 MEAN 341.49 293.97 134.61 0.27 3430.27 0.92 0.90 0.90 1.59

 HUB 286.19 267.68 47.67 0.24 3314.27 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.25 1.08 5.88 528.61 1.02 519.82 491.85 5.92

 MEAN 6.20 1.07 5.82 527.09 1.02 518.19 491.20 6.21

 HUB 6.18 1.07 5.76 526.70 1.02 516.60 491.16 6.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.46 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.37 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.16 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 354.1038 208.0448 286.5429 1107.3203 0.3198 -0.0933 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2059 5.7872 517.4323 491.5103 6.4027 35.9816 32.4000 -3.5816

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.1273 64.6185 280.7878 1110.9386 0.2594 0.2642 2.2705

 

NASA/TM—2013-218094 O–64
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2043 5.9248 520.8231 491.1942 432.2457 0.0140 0.4047

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 285.8075 0.0000 285.8075 1111.0422 0.2572 0.3154 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9193 520.9299 491.2699 0.0000 0.0600 0.0410 0.2499

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8704 6.1939 1.0737 527.4655 11.6942 212.7422 1.6492

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73079.453 0.483 106.776 246635.875 0.169889E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.467 EfDer = 0.994 SH = 0.192457E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.855 2361.088 6.194 527.465 1.000 1.000 0.980

 W Kg/sec = 11.752 Wdry = 25.805 WH2O = 0.050 lbm/sec H2O = 0.956g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.878 2341.387 1.379 0.250 53.411 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50107.945 20271.838 2.811 509.668 181.344 384.739 2.122

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 235.95 -0.08 235.95 0.21 0.40 374.31

 MEAN 15.91 0.00 -0.02 235.95 -0.08 235.95 0.21 0.36

 HUB 13.07 0.00 -0.02 235.95 -0.08 235.95 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.00 47.36 10.64 377.47 445.22 6.01 523.01 491.51 6.45

 MEAN 54.27 44.80 9.47 327.88 404.02 6.01 523.01 491.51 6.45

 HUB 48.78 38.84 9.94 269.30 358.10 6.01 523.01 491.51 6.45

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.85 192.94 248.81 1121.62 0.28 2.05 1.78 7.43

 MEAN 15.50 314.22 189.48 250.66 1119.83 0.28 2.13 1.86 5.75

 HUB 12.59 330.85 213.62 252.64 1118.06 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 369.64 305.17 176.70 0.27 3462.82 0.92 0.91

 MEAN 319.32 282.30 129.84 0.25 2937.71 0.92 0.91 0.91 1.58

 HUB 259.41 256.76 45.79 0.23 2690.57 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.65 1.07 6.30 538.87 1.02 530.95 496.95 5.39

 MEAN 6.58 1.06 6.23 537.14 1.02 529.25 496.22 5.65

 HUB 6.55 1.06 6.16 536.33 1.02 527.58 495.98 5.92

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.79 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.09 27.38 23.50 3.88 0.94 0.44 1.64

 HUB 40.22 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 344.3422 192.9497 285.2052 1118.4500 0.3079 -0.1744 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5837 6.1709 527.9722 496.5421 5.8922 34.0795 33.0000 -1.0795

 

NASA/TM—2013-218094 O–65
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 291.7816 66.6286 284.0724 1121.2733 0.2602 0.1427 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5821 6.2838 530.6444 496.2800 410.5396 0.0244 0.3784

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 283.8516 0.0000 283.8516 1121.6488 0.2531 0.3013 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2952 531.0090 496.3398 0.0000 0.0600 0.0370 0.1746

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8794 6.5776 1.0619 537.4469 9.9824 233.2847 1.8084

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 62465.145 0.457 91.268 259007.469 0.211132E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.11010E-02 0.11168E-01

 trTOT = 1.1447 Tt4 = 537.4469 T1 = 469.4972

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 424030.97 619.5496 83.3730 1.5166 0.8389 15.3908 1.1447 37.3740

NASA/TM—2013-218094 O–66
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.483 EfDer = 0.954 SH = 0.388889E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.697 2286.627 4.829 471.207 1.000 1.000 0.980

 W Kg/sec = 12.590 Wdry = 27.687 WH2O = 0.011 lbm/sec H2O = 0.170g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.368 2399.081 1.381 0.249 53.361 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60935.738 21729.355 3.534 831.557 235.299 619.754 2.634

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 175.87 -0.06 175.87 0.17 0.42 431.90

 MEAN 17.06 0.00 -0.02 175.87 -0.06 175.87 0.17 0.36

 HUB 12.51 0.00 -0.02 175.87 -0.06 175.87 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.87 50.47 16.40 411.66 447.71 4.74 468.72 458.93 8.89

 MEAN 62.68 47.20 15.48 340.43 383.23 4.74 468.72 458.93 8.89

 HUB 54.84 38.62 16.22 249.63 305.41 4.74 468.72 458.93 8.89

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 369.37 283.45 236.83 1065.68 0.35 7.29 6.52 16.04

 MEAN 18.04 373.78 286.94 239.53 1062.98 0.35 7.43 6.80 12.53

 HUB 15.00 404.57 323.26 243.26 1059.66 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 411.66 269.31 128.21 0.25 5848.85 0.92 0.87

 MEAN 359.90 250.40 72.96 0.24 5176.36 0.92 0.87 0.87 1.76

 HUB 299.32 244.44 23.94 0.23 4849.63 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.47 1.13 5.03 489.96 1.04 479.00 471.31 7.99

 MEAN 5.39 1.12 4.95 487.80 1.04 476.58 470.09 8.73

 HUB 5.35 1.11 4.85 486.76 1.03 473.61 469.64 9.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 50.12 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 50.15 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 53.04 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.954 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 384.6732 286.3866 256.8194 1062.6298 0.3620 -0.0366 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3976 4.9361 476.2903 470.4124 9.0952 48.1156 35.4000 -12.7156

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.1432 62.6604 248.3606 1069.9749 0.2394 0.5124 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3870 5.1791 482.9048 470.0208 554.9116 0.0331 0.6033

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 254.9967 0.0000 254.9967 1070.0103 0.2383 0.4807 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1580 482.9521 470.1844 0.0000 0.0600 0.0854 0.4662

NASA/TM—2013-218094 O–67
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8156 5.3631 1.1107 488.1731 16.9670 167.9930 1.3023

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 105647.125 0.623 165.359 283569.125 0.624021E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.809 EfDer = 0.960 SH = 0.889338E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.697 2286.627 5.363 488.173 1.000 1.000 0.980

 W Kg/sec = 12.590 Wdry = 27.673 WH2O = 0.025 lbm/sec H2O = 0.413g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.649 2357.037 1.380 0.249 53.377 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57412.262 21725.084 2.738 590.487 215.694 468.502 2.172

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.34 -0.08 233.34 0.22 0.44 422.68

 MEAN 18.08 0.00 -0.02 233.34 -0.08 233.34 0.22 0.40

 HUB 15.21 0.00 -0.02 233.34 -0.08 233.34 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.36 46.36 14.00 410.07 471.88 5.19 483.81 470.93 11.59

 MEAN 57.11 42.30 14.81 360.74 429.70 5.19 483.81 470.93 11.59

 HUB 52.45 37.84 14.61 303.51 382.90 5.19 483.81 470.93 11.59

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 340.37 233.92 247.26 1082.32 0.31 2.33 2.04 9.02

 MEAN 18.01 340.34 231.57 249.41 1080.19 0.32 2.40 2.13 7.35

 HUB 15.22 360.97 258.63 251.81 1078.09 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 407.47 302.09 173.56 0.28 4778.23 0.92 0.88

 MEAN 359.38 280.25 127.81 0.26 4172.10 0.92 0.88 0.88 1.69

 HUB 303.77 255.82 45.14 0.24 3938.36 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.92 1.10 5.53 503.47 1.03 494.18 479.81 8.52

 MEAN 5.85 1.09 5.46 501.53 1.03 492.24 478.80 9.09

 HUB 5.82 1.08 5.39 500.78 1.03 490.33 478.53 9.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.41 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.88 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.77 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.960 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.1980 232.2248 280.5563 1079.1288 0.3375 -0.1091 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8568 5.4186 491.2884 479.1589 9.4561 39.6156 30.6000 -9.0156

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 272.3903 57.7487 266.1983 1084.2609 0.2512 0.3570 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8517 5.6037 495.9753 478.7499 491.5697 0.0227 0.4539

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 282.1679 0.0000 282.1679 1083.7747 0.2604 0.3469 0.5911

NASA/TM—2013-218094 O–68
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5706 495.5406 478.8554 0.0000 0.0600 0.0629 0.2742

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8352 5.8356 1.0881 501.9250 13.7529 190.6766 1.4781

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85756.125 0.516 134.225 258275.141 0.995669E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.598 EfDer = 0.976 SH = 0.114027E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.697 2286.627 5.836 501.925 1.000 1.000 0.980

 W Kg/sec = 12.590 Wdry = 27.666 WH2O = 0.032 lbm/sec H2O = 0.560g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.632 2324.524 1.380 0.249 53.385 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54282.242 21722.939 2.713 545.479 201.037 424.468 2.111

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 238.83 -0.08 238.83 0.22 0.43 407.11

 MEAN 17.74 0.00 -0.02 238.83 -0.08 238.83 0.22 0.39

 HUB 15.05 0.00 -0.02 238.83 -0.08 238.83 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.20 46.36 12.84 400.49 466.36 5.64 497.35 479.08 9.32

 MEAN 56.00 43.40 12.60 353.96 427.07 5.64 497.35 479.08 9.32

 HUB 51.51 38.84 12.67 300.32 383.77 5.64 497.35 479.08 9.32

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.45 217.36 252.87 1095.97 0.30 2.26 1.98 8.75

 MEAN 17.51 335.50 218.29 254.78 1094.18 0.31 2.34 2.07 6.78

 HUB 14.85 358.31 249.80 256.88 1092.41 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 395.30 309.21 177.94 0.28 4307.51 0.92 0.89

 MEAN 349.34 286.50 131.05 0.26 3822.98 0.92 0.89 0.89 1.63

 HUB 296.33 261.06 46.53 0.24 3710.73 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 515.70 1.03 506.79 486.54 7.23

 MEAN 6.31 1.08 5.92 514.15 1.02 505.13 485.80 7.61

 HUB 6.30 1.08 5.85 513.79 1.02 503.50 485.76 8.01

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.68 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.59 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.20 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 360.7807 219.7230 286.1546 1093.0620 0.3301 -0.1182 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3222 5.8689 504.1197 486.1557 7.9158 37.5188 31.5000 -6.0188

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 282.4693 61.6188 275.6665 1097.4260 0.2574 0.2983 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3192 6.0386 508.1559 485.7928 451.3937 0.0172 0.4232

 

NASA/TM—2013-218094 O–69
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 287.1297 0.0000 287.1297 1097.1864 0.2617 0.3269 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0171 507.9434 485.8864 0.0000 0.0600 0.0488 0.2459

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8578 6.3063 1.0806 514.5483 12.6240 197.5731 1.5316

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 78788.445 0.504 123.320 257562.688 0.126718E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.797 EfDer = 0.987 SH = 0.143769E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.697 2286.627 6.306 514.548 1.000 1.000 0.980

 W Kg/sec = 12.590 Wdry = 27.657 WH2O = 0.040 lbm/sec H2O = 0.745g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.304 2295.833 1.379 0.249 53.395 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51492.910 21720.393 2.725 513.330 188.395 395.845 2.101

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 240.74 -0.08 240.74 0.22 0.41 385.86

 MEAN 16.97 0.00 -0.02 240.74 -0.08 240.74 0.22 0.38

 HUB 14.32 0.00 -0.02 240.74 -0.08 240.74 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.94 46.36 11.58 384.33 453.57 6.10 509.91 486.10 7.86

 MEAN 54.60 43.80 10.80 338.64 415.56 6.10 509.91 486.10 7.86

 HUB 49.89 37.84 12.05 285.75 373.71 6.10 509.91 486.10 7.86

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 321.84 197.68 253.98 1108.15 0.29 2.16 1.89 8.34

 MEAN 16.57 324.04 199.05 255.69 1106.55 0.29 2.24 1.97 6.35

 HUB 13.89 345.67 230.53 257.57 1104.97 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.74 310.75 179.06 0.28 3733.85 0.92 0.90

 MEAN 330.72 287.60 131.67 0.26 3300.50 0.92 0.90 0.90 1.58

 HUB 277.17 261.76 46.64 0.24 3203.28 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.80 1.08 6.42 526.48 1.02 518.19 492.21 6.41

 MEAN 6.74 1.07 6.36 525.09 1.02 516.69 491.59 6.70

 HUB 6.73 1.07 6.29 524.78 1.02 515.22 491.57 6.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.90 35.18 31.50 3.68 0.93 0.47 1.40

 MEAN 37.90 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.83 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 344.4375 200.1734 280.2995 1105.7448 0.3115 -0.0947 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7524 6.3192 515.9556 491.8915 6.8922 35.5322 32.4000 -3.1322

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 282.2069 63.2908 275.0182 1109.0809 0.2545 0.2544 2.2705

 

NASA/TM—2013-218094 O–70
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7511 6.4580 519.0770 491.6078 432.2457 0.0133 0.3969

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 279.9094 0.0000 279.9094 1109.1825 0.2524 0.3077 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4525 519.1807 491.6768 0.0000 0.0600 0.0400 0.2407

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8719 6.7404 1.0688 525.4510 10.9034 214.6161 1.6637

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68120.172 0.480 106.622 264367.250 0.158393E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.152 EfDer = 0.995 SH = 0.178310E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.697 2286.627 6.740 525.451 1.000 1.000 0.980

 W Kg/sec = 12.590 Wdry = 27.648 WH2O = 0.049 lbm/sec H2O = 0.969g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 60.796 2271.890 1.379 0.250 53.406 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49093.113 21717.436 2.861 509.668 178.158 384.739 2.160

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.17 -0.08 231.17 0.21 0.39 363.20

 MEAN 15.91 0.00 -0.02 231.17 -0.08 231.17 0.21 0.35

 HUB 13.07 0.00 -0.02 231.17 -0.08 231.17 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.70 47.36 10.34 365.57 432.60 6.54 521.18 491.90 6.95

 MEAN 53.95 44.80 9.15 317.54 392.84 6.54 521.18 491.90 6.95

 HUB 48.46 38.84 9.62 260.81 348.57 6.54 521.18 491.90 6.95

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 306.17 184.52 244.32 1119.07 0.27 2.05 1.78 7.43

 MEAN 15.50 305.90 181.82 246.00 1117.42 0.27 2.13 1.86 5.75

 HUB 12.59 322.43 206.30 247.80 1115.79 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 357.99 299.64 173.47 0.27 3311.73 0.92 0.91

 MEAN 309.25 277.04 127.43 0.25 2819.07 0.92 0.91 0.91 1.57

 HUB 251.23 251.83 44.93 0.23 2598.39 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.20 1.07 6.84 536.02 1.02 528.52 497.09 5.87

 MEAN 7.13 1.06 6.77 534.45 1.02 526.96 496.41 6.14

 HUB 7.10 1.05 6.71 533.74 1.02 525.43 496.19 6.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.06 35.37 31.50 3.87 0.93 0.46 1.40

 MEAN 36.47 27.38 23.50 3.88 0.93 0.43 1.64

 HUB 39.78 10.28 6.50 3.78 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 335.5306 185.1562 279.8178 1116.0948 0.3006 -0.1767 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1362 6.7087 525.7365 496.7126 6.3945 33.4927 33.0000 -0.4927

 

NASA/TM—2013-218094 O–71
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 286.5802 65.4408 279.0085 1118.6732 0.2562 0.1289 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1349 6.8211 528.1713 496.4799 410.5396 0.0236 0.3687

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.8050 0.0000 278.8050 1119.0364 0.2491 0.2909 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8330 528.5223 496.5318 0.0000 0.0600 0.0367 0.1611

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8803 7.1300 1.0578 534.7360 9.2862 236.1614 1.8307

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 58084.676 0.453 90.914 277999.500 0.194637E-02

 

Melt Ratio at Stator LE, Throat, TE

0.80126E-03 0.28729E-02 0.14447E-01

 trTOT = 1.1348 Tt4 = 534.7360 T1 = 471.2072

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 396396.56 620.4397 80.3681 1.4766 0.8398 15.4827 1.1348 37.3740

NASA/TM—2013-218094 O–72
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =14.017 EfDer = 0.966 SH = 0.526954E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.582 2159.319 5.592 480.735 1.000 1.000 0.980

 W Kg/sec = 14.356 Wdry = 31.566 WH2O = 0.017 lbm/sec H2O = 0.262g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.922 2242.954 1.381 0.249 53.365 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 61202.996 24775.910 3.553 831.557 234.019 619.754 2.648

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 176.64 -0.06 176.64 0.17 0.40 403.79

 MEAN 17.06 0.00 -0.02 176.64 -0.06 176.64 0.17 0.34

 HUB 12.51 0.00 -0.02 176.64 -0.06 176.64 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.57 50.47 15.10 388.74 427.05 5.49 478.23 466.22 9.19

 MEAN 61.22 47.20 14.02 321.47 366.86 5.49 478.23 466.22 9.19

 HUB 53.16 38.62 14.54 235.73 294.62 5.49 478.23 466.22 9.19

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 353.11 259.74 239.21 1074.42 0.33 7.29 6.52 16.04

 MEAN 18.04 359.80 266.68 241.54 1072.16 0.34 7.43 6.80 12.53

 HUB 15.00 392.72 307.04 244.86 1069.28 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.74 271.78 129.00 0.25 5359.67 0.92 0.88

 MEAN 339.86 252.38 73.19 0.24 4810.81 0.92 0.88 0.88 1.66

 HUB 282.65 246.07 24.39 0.23 4606.37 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 496.95 1.03 486.94 476.69 8.45

 MEAN 6.15 1.10 5.70 495.29 1.03 484.90 475.80 9.07

 HUB 6.13 1.10 5.59 494.67 1.03 482.29 475.62 9.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.36 28.34 24.20 4.14 0.93 0.53 1.80

 MEAN 47.83 16.86 12.70 4.16 0.95 0.48 2.22

 HUB 51.43 -5.69 -9.30 3.61 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.966 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 371.3716 266.1580 258.9918 1071.7729 0.3465 -0.0419 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1638 5.6788 484.5714 476.1011 9.4195 45.7818 35.4000 -10.3818

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 259.6058 63.5075 251.7180 1078.0070 0.2408 0.4721 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1560 5.9157 490.2316 475.7250 554.9116 0.0262 0.5610

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 258.1738 0.0000 258.1738 1078.0577 0.2395 0.4517 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8979 490.2914 475.8853 0.0000 0.0600 0.0707 0.4348

NASA/TM—2013-218094 O–73
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8334 6.1347 1.0970 495.6401 14.9057 175.1292 1.3576

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92867.484 0.615 165.745 318462.063 0.774499E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.966 EfDer = 0.974 SH = 0.104175E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.582 2159.319 6.135 495.640 1.000 1.000 0.980

 W Kg/sec = 14.356 Wdry = 31.549 WH2O = 0.033 lbm/sec H2O = 0.545g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.976 2208.979 1.380 0.249 53.382 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58124.930 24770.896 2.725 590.487 216.675 468.502 2.162

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.24 -0.08 236.24 0.22 0.42 396.13

 MEAN 18.08 0.00 -0.02 236.24 -0.08 236.24 0.22 0.38

 HUB 15.21 0.00 -0.02 236.24 -0.08 236.24 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.62 46.36 12.26 387.24 453.68 5.94 491.17 476.59 11.46

 MEAN 55.27 42.30 12.97 340.66 414.63 5.94 491.17 476.59 11.46

 HUB 50.51 37.84 12.67 286.61 371.49 5.94 491.17 476.59 11.46

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 326.83 208.39 251.77 1088.55 0.30 2.33 2.04 9.02

 MEAN 18.01 329.04 209.68 253.58 1086.85 0.30 2.40 2.13 7.35

 HUB 15.22 351.47 241.26 255.59 1085.17 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.79 307.41 176.39 0.28 4257.09 0.92 0.89

 MEAN 339.37 284.82 129.69 0.26 3777.84 0.92 0.89 0.89 1.60

 HUB 286.86 259.62 45.59 0.24 3673.97 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.09 6.27 508.50 1.03 499.94 483.95 8.95

 MEAN 6.60 1.08 6.20 507.05 1.02 498.37 483.22 9.41

 HUB 6.59 1.07 6.14 506.74 1.02 496.84 483.19 9.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.61 35.02 31.50 3.52 0.93 0.49 1.40

 MEAN 39.59 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.35 10.11 6.50 3.61 0.94 0.47 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 354.4095 210.2710 285.2933 1085.7289 0.3264 -0.1223 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6162 6.1518 497.3639 483.5801 9.7914 36.3915 30.6000 -5.7915

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 278.1404 58.9677 271.8177 1089.9387 0.2552 0.2933 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6134 6.3245 501.2306 483.2209 491.5697 0.0167 0.4004

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 287.9078 0.0000 287.9078 1089.4476 0.2643 0.3016 0.5911

NASA/TM—2013-218094 O–74
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2918 500.7877 483.3331 0.0000 0.0600 0.0479 0.2152

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8551 6.6003 1.0759 507.4306 11.7913 203.2496 1.5756

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73568.070 0.497 131.300 291253.063 0.114725E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.522 EfDer = 0.989 SH = 0.128567E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.582 2159.319 6.600 507.430 1.000 1.000 0.980

 W Kg/sec = 14.356 Wdry = 31.542 WH2O = 0.041 lbm/sec H2O = 0.706g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.570 2183.165 1.380 0.249 53.390 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55369.285 24768.520 2.676 545.479 203.806 424.468 2.083

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.61 -0.08 243.61 0.22 0.41 382.36

 MEAN 17.74 0.00 -0.02 243.61 -0.08 243.61 0.22 0.38

 HUB 15.05 0.00 -0.02 243.61 -0.08 243.61 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.22 46.36 10.86 378.19 449.93 6.38 502.68 483.51 9.66

 MEAN 53.92 43.40 10.52 334.26 413.68 6.38 502.68 483.51 9.66

 HUB 49.35 38.84 10.51 283.60 373.93 6.38 502.68 483.51 9.66

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.08 190.83 259.46 1099.97 0.29 2.26 1.98 8.75

 MEAN 17.51 326.23 195.71 261.00 1098.58 0.30 2.34 2.07 6.78

 HUB 14.85 350.67 232.27 262.72 1097.23 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 373.29 317.19 182.46 0.29 3782.00 0.92 0.90

 MEAN 329.89 293.47 134.17 0.27 3427.75 0.92 0.90 0.90 1.54

 HUB 279.83 266.99 47.56 0.24 3450.44 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.10 1.08 6.70 518.85 1.02 510.54 489.69 7.87

 MEAN 7.05 1.07 6.64 517.78 1.02 509.25 489.20 8.19

 HUB 7.06 1.07 6.58 517.85 1.02 508.00 489.37 8.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.33 35.12 31.50 3.62 0.93 0.45 1.40

 MEAN 36.86 27.21 23.50 3.71 0.94 0.44 1.62

 HUB 41.48 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.2589 196.9972 293.2303 1097.3895 0.3219 -0.1327 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0665 6.5836 508.1632 489.5587 8.5198 33.8939 31.5000 -2.3939

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 290.6247 63.3978 283.6255 1100.8693 0.2640 0.2224 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0651 6.7356 511.3928 489.2499 451.3937 0.0133 0.3647

 

NASA/TM—2013-218094 O–75
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 295.2773 0.0000 295.2773 1100.6260 0.2683 0.2717 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7148 511.1748 489.3437 0.0000 0.0600 0.0386 0.1741

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8734 7.0542 1.0688 518.1562 10.7262 212.8347 1.6499

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66980.125 0.481 119.542 291532.125 0.140535E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.476 EfDer = 0.997 SH = 0.156191E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.582 2159.319 7.054 518.156 1.000 1.000 0.980

 W Kg/sec = 14.356 Wdry = 31.533 WH2O = 0.049 lbm/sec H2O = 0.898g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.779 2160.452 1.379 0.250 53.399 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52924.711 24765.824 2.663 513.330 192.734 395.845 2.054

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 247.44 -0.09 247.44 0.22 0.40 363.11

 MEAN 16.97 0.00 -0.02 247.44 -0.09 247.44 0.22 0.37

 HUB 14.32 0.00 -0.02 247.44 -0.09 247.44 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.72 46.36 9.36 362.93 439.32 6.81 513.26 489.50 8.43

 MEAN 52.28 43.80 8.48 319.79 404.41 6.81 513.26 489.50 8.43

 HUB 47.49 37.84 9.65 269.84 366.18 6.81 513.26 489.50 8.43

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 313.10 170.58 262.55 1110.08 0.28 2.16 1.89 8.34

 MEAN 16.57 317.37 176.28 263.91 1108.89 0.29 2.24 1.97 6.35

 HUB 13.89 340.67 213.58 265.40 1107.72 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.77 321.29 185.18 0.29 3222.27 0.92 0.91

 MEAN 312.31 296.90 136.03 0.27 2923.12 0.92 0.91 0.91 1.48

 HUB 261.74 269.73 48.16 0.24 2967.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.50 1.06 7.11 527.87 1.02 520.03 494.53 7.16

 MEAN 7.46 1.06 7.05 526.97 1.02 518.91 494.14 7.40

 HUB 7.47 1.06 7.00 527.11 1.02 517.82 494.34 7.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.01 35.20 31.50 3.70 0.93 0.41 1.40

 MEAN 33.74 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.83 10.28 6.50 3.78 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.997 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 339.3772 177.2730 289.3979 1108.0026 0.3063 -0.1071 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4727 7.0086 518.1024 494.4460 7.6241 31.4899 32.4000 0.9101

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.4697 65.5924 285.0196 1110.5326 0.2634 0.1700 2.2705

 

NASA/TM—2013-218094 O–76
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4718 7.1251 520.4738 494.2181 432.2457 0.0121 0.3338

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 290.0229 0.0000 290.0229 1110.6470 0.2611 0.2417 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1208 520.5881 494.2773 0.0000 0.0600 0.0369 0.1598

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8791 7.4613 1.0577 527.3168 9.1611 234.0459 1.8143

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57261.223 0.452 102.197 300255.969 0.169467E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.611 EfDer = 1.000 SH = 0.187201E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.582 2159.319 7.461 527.317 1.000 1.000 0.980

 W Kg/sec = 14.356 Wdry = 31.523 WH2O = 0.059 lbm/sec H2O = 1.120g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.737 2141.604 1.379 0.250 53.409 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50827.988 24762.795 2.772 509.668 183.859 384.739 2.093

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.34 -0.08 239.34 0.22 0.38 342.37

 MEAN 15.91 0.00 -0.02 239.34 -0.08 239.34 0.22 0.34

 HUB 13.07 0.00 -0.02 239.34 -0.08 239.34 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.27 47.36 7.91 345.21 420.14 7.23 522.74 494.43 7.62

 MEAN 51.41 44.80 6.61 299.86 383.73 7.23 522.74 494.43 7.62

 HUB 45.83 38.84 6.99 246.29 343.49 7.23 522.74 494.43 7.62

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.03 157.19 254.38 1119.19 0.27 2.05 1.78 7.43

 MEAN 15.50 301.29 159.33 255.72 1117.96 0.27 2.13 1.86 5.75

 HUB 12.59 319.95 190.36 257.16 1116.74 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 338.05 312.13 180.86 0.28 2821.52 0.92 0.91

 MEAN 292.03 288.10 132.70 0.26 2470.56 0.92 0.91 0.91 1.46

 HUB 237.24 261.39 46.88 0.23 2397.74 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.87 1.05 7.49 535.82 1.02 528.67 498.67 6.67

 MEAN 7.82 1.05 7.44 534.76 1.01 527.50 498.22 6.89

 HUB 7.81 1.05 7.38 534.54 1.01 526.36 498.23 7.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.71 35.41 31.50 3.91 0.93 0.39 1.40

 MEAN 31.93 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.51 10.33 6.50 3.83 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 333.1894 162.2529 291.0140 1116.5198 0.2984 -0.1956 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8238 7.3617 526.1656 498.5423 7.1888 29.1416 33.0000 3.8584

 

NASA/TM—2013-218094 O–77
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 299.1602 68.3135 291.2561 1118.3412 0.2675 0.0233 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8212 7.4471 527.8853 498.3654 410.5396 0.0267 0.3027

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 291.0161 0.0000 291.0161 1118.7404 0.2601 0.2155 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4613 528.2680 498.3911 0.0000 0.0600 0.0417 0.0592

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8750 7.8152 1.0474 535.0359 7.7220 260.5247 2.0196

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 48316.176 0.423 86.232 316639.750 0.200694E-02

 

Melt Ratio at Stator LE, Throat, TE

0.23121E-01 0.29926E-01 0.53604E-01

 trTOT = 1.1130 Tt4 = 535.0359 T1 = 480.7353

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 338993.09 605.0160 79.9221 1.3975 0.8538 14.0171 1.1130 37.3740

NASA/TM—2013-218094 O–78
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.253 EfDer = 0.995 SH = 0.703876E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.605 1974.585 6.513 491.411 1.000 1.000 0.980

 W Kg/sec = 18.002 Wdry = 39.577 WH2O = 0.028 lbm/sec H2O = 0.397g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.009 2028.667 1.380 0.249 53.371 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67551.438 31067.453 3.264 831.557 254.804 619.754 2.432

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 194.96 -0.07 194.96 0.18 0.38 365.21

 MEAN 17.06 0.00 -0.02 194.96 -0.07 194.96 0.18 0.33

 HUB 12.51 0.00 -0.02 194.96 -0.07 194.96 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.26 50.47 10.79 355.49 405.50 6.37 488.36 474.10 9.31

 MEAN 56.45 47.20 9.25 293.97 352.80 6.37 488.36 474.10 9.31

 HUB 47.88 38.62 9.26 215.57 290.70 6.37 488.36 474.10 9.31

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 340.81 212.11 266.76 1082.33 0.31 7.29 6.52 16.04

 MEAN 18.04 353.46 229.78 268.57 1080.86 0.33 7.43 6.80 12.53

 HUB 15.00 394.26 285.79 271.60 1078.60 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.49 302.85 143.38 0.28 4377.18 0.92 0.91

 MEAN 310.79 280.52 81.00 0.26 4145.53 0.92 0.91 0.91 1.42

 HUB 258.47 272.97 27.31 0.25 4287.63 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.06 1.08 6.60 503.52 1.02 494.20 481.86 9.11

 MEAN 7.03 1.08 6.53 502.87 1.02 492.85 481.57 9.53

 HUB 7.05 1.08 6.43 503.27 1.02 490.79 482.02 10.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.49 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.55 16.78 12.70 4.08 0.93 0.36 2.22

 HUB 46.46 -5.74 -9.30 3.56 0.93 0.24 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.3355 229.3376 288.2279 1080.2668 0.3410 -0.0593 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0394 6.5023 492.3376 481.8943 9.9068 38.5086 35.4000 -3.1086

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 291.1993 71.2362 282.3517 1084.7280 0.2685 0.3379 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0370 6.6978 496.4183 481.5913 554.9116 0.0146 0.4378

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 289.0782 0.0000 289.0782 1084.8247 0.2665 0.3495 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6900 496.5174 481.7387 0.0000 0.0600 0.0399 0.3230

NASA/TM—2013-218094 O–79
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8747 7.0237 1.0785 503.2189 11.8083 200.2616 1.5524

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73620.422 0.583 164.771 393886.375 0.944229E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.406 EfDer = 0.999 SH = 0.118389E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.605 1974.585 7.024 503.219 1.000 1.000 0.980

 W Kg/sec = 18.002 Wdry = 39.558 WH2O = 0.047 lbm/sec H2O = 0.695g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.644 2004.728 1.380 0.249 53.387 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65004.543 31061.590 2.469 590.487 239.159 468.502 1.959

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 264.20 -0.09 264.20 0.24 0.41 359.50

 MEAN 18.08 0.00 -0.02 264.20 -0.09 264.20 0.24 0.38

 HUB 15.21 0.00 -0.02 264.20 -0.09 264.20 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.28 46.36 6.92 354.11 441.88 6.74 497.63 482.32 11.44

 MEAN 49.71 42.30 7.41 311.52 408.54 6.74 497.63 482.32 11.44

 HUB 44.78 37.84 6.94 262.09 372.21 6.74 497.63 482.32 11.44

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.87 152.24 284.72 1092.32 0.30 2.33 2.04 9.02

 MEAN 18.01 329.49 163.94 285.81 1091.48 0.30 2.40 2.13 7.35

 HUB 15.22 356.16 210.81 287.07 1090.66 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.87 347.73 199.62 0.32 3110.67 0.92 0.91

 MEAN 310.34 321.12 146.40 0.29 2954.11 0.92 0.91 0.91 1.38

 HUB 262.32 291.65 51.51 0.27 3210.54 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.43 1.06 7.00 511.81 1.02 503.46 487.23 9.82

 MEAN 7.41 1.05 6.96 511.38 1.02 502.68 487.05 10.06

 HUB 7.44 1.06 6.92 512.08 1.02 501.92 487.57 10.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 28.13 35.04 31.50 3.54 0.93 0.34 1.40

 MEAN 29.84 27.12 23.50 3.62 0.93 0.34 1.63

 HUB 36.29 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 361.7041 164.3956 322.1862 1089.9413 0.3319 -0.1632 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4230 6.8854 501.2751 487.4606 10.5823 27.0330 30.6000 3.5670

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 316.4260 67.0846 309.2331 1092.6118 0.2896 0.0994 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4209 7.0069 503.7347 487.2104 491.5697 0.0146 0.2571

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 327.6678 0.0000 327.6678 1091.9766 0.3001 0.1501 0.5911

NASA/TM—2013-218094 O–80
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9661 503.1551 487.3332 0.0000 0.0600 0.0410 0.0120

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8718 7.4086 1.0548 511.7551 8.5367 250.3279 1.9405

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 53290.500 0.430 119.270 363151.563 0.127627E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.486 EfDer = 0.995 SH = 0.139079E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.605 1974.585 7.409 511.755 1.000 1.000 0.980

 W Kg/sec = 18.002 Wdry = 39.550 WH2O = 0.055 lbm/sec H2O = 0.844g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.056 1987.938 1.379 0.249 53.393 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62822.516 31059.059 2.385 545.479 228.683 424.468 1.856

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 276.40 -0.10 276.40 0.25 0.40 348.16

 MEAN 17.74 0.00 -0.02 276.40 -0.10 276.40 0.25 0.38

 HUB 15.05 0.00 -0.02 276.40 -0.10 276.40 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.37 46.36 5.01 345.84 442.80 7.09 505.64 487.37 10.37

 MEAN 47.89 43.40 4.49 305.66 412.17 7.09 505.64 487.37 10.37

 HUB 43.19 38.84 4.35 259.33 379.08 7.09 505.64 487.37 10.37

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 325.67 130.88 298.21 1099.81 0.30 2.26 1.98 8.75

 MEAN 17.51 333.21 147.30 298.88 1099.34 0.30 2.34 2.07 6.78

 HUB 14.85 360.86 200.95 299.74 1098.88 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 341.36 365.01 210.47 0.33 2594.70 0.92 0.91

 MEAN 301.66 336.39 154.36 0.31 2580.41 0.92 0.91 0.91 1.32

 HUB 255.89 304.73 54.94 0.28 2985.47 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.76 1.05 7.31 518.91 1.01 510.42 491.32 9.23

 MEAN 7.76 1.05 7.28 518.87 1.01 509.99 491.35 9.35

 HUB 7.81 1.05 7.26 519.99 1.02 509.57 492.07 9.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.70 35.21 31.50 3.71 0.93 0.28 1.40

 MEAN 26.24 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.84 10.39 6.50 3.89 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 367.8047 148.2668 336.5966 1097.6442 0.3351 -0.1760 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7696 7.1965 508.4312 491.7817 9.8615 23.7729 31.5000 7.7271

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 336.2635 73.3536 328.1652 1099.5620 0.3058 0.0038 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7646 7.2837 510.2090 491.5883 451.3937 0.0202 0.2149

 

NASA/TM—2013-218094 O–81
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 342.0755 0.0000 342.0755 1099.2170 0.3112 0.0946 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2507 509.8938 491.6694 0.0000 0.0600 0.0563 -0.0631

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8424 7.7469 1.0457 519.2603 7.5054 270.8968 2.1000

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46885.754 0.402 104.936 365812.375 0.148755E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.895 EfDer = 0.975 SH = 0.160854E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.605 1974.585 7.747 519.260 1.000 1.000 0.980

 W Kg/sec = 18.002 Wdry = 39.541 WH2O = 0.064 lbm/sec H2O = 1.005g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.193 1973.520 1.379 0.250 53.400 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61069.125 31056.395 2.330 513.330 220.326 395.845 1.797

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 285.52 -0.10 285.52 0.26 0.40 331.69

 MEAN 16.97 0.00 -0.02 285.52 -0.10 285.52 0.26 0.37

 HUB 14.32 0.00 -0.02 285.52 -0.10 285.52 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.30 46.36 2.94 331.88 437.87 7.40 512.74 491.64 9.60

 MEAN 45.70 43.80 1.90 292.43 408.77 7.40 512.74 491.64 9.60

 HUB 40.85 37.84 3.01 246.76 377.43 7.40 512.74 491.64 9.60

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 325.52 107.38 307.30 1106.15 0.29 2.16 1.89 8.34

 MEAN 16.57 332.41 125.88 307.65 1105.94 0.30 2.24 1.97 6.35

 HUB 13.89 358.16 182.41 308.23 1105.73 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 325.33 376.75 217.96 0.34 2029.14 0.92 0.89

 MEAN 285.59 346.64 159.71 0.31 2087.95 0.92 0.89 0.89 1.27

 HUB 239.35 313.44 56.94 0.28 2535.06 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.02 1.04 7.56 524.85 1.01 516.38 494.66 8.85

 MEAN 8.03 1.04 7.55 525.02 1.01 516.18 494.77 8.90

 HUB 8.09 1.04 7.53 526.25 1.01 515.99 495.52 8.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.26 35.35 31.50 3.85 0.93 0.23 1.40

 MEAN 22.25 27.44 23.50 3.94 0.91 0.25 1.62

 HUB 30.62 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 361.0570 126.5859 338.1393 1104.6047 0.3269 -0.1437 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0420 7.4763 514.9458 495.1533 9.2820 20.5239 32.4000 11.8761

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 344.5693 77.2768 335.7921 1105.6029 0.3117 -0.0585 2.2705

 

NASA/TM—2013-218094 O–82
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0330 7.5172 515.8766 495.0463 432.2457 0.0280 0.1784

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 342.2926 0.0000 342.2926 1105.7339 0.3096 0.0409 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4995 516.0021 495.0544 0.0000 0.0600 0.0799 -0.0939

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7746 8.0070 1.0336 525.3737 6.1137 311.3334 2.4134

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 38219.277 0.361 85.539 379067.406 0.170852E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.506 EfDer = 0.942 SH = 0.183839E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.605 1974.585 8.007 525.374 1.000 1.000 0.980

 W Kg/sec = 18.002 Wdry = 39.532 WH2O = 0.073 lbm/sec H2O = 1.175g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.177 1962.004 1.379 0.250 53.408 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59705.633 31053.580 2.377 509.668 214.451 384.739 1.794

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 281.15 -0.10 281.15 0.25 0.38 313.66

 MEAN 15.91 0.00 -0.02 281.15 -0.10 281.15 0.25 0.35

 HUB 13.07 0.00 -0.02 281.15 -0.10 281.15 0.25 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.32 47.36 0.96 315.68 422.80 7.66 519.05 494.99 9.04

 MEAN 44.29 44.80 -0.51 274.20 392.79 7.66 519.05 494.99 9.04

 HUB 38.71 38.84 -0.13 225.22 360.29 7.66 519.05 494.99 9.04

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 316.89 91.92 303.26 1111.99 0.28 2.05 1.78 7.43

 MEAN 15.50 322.24 108.02 303.60 1111.78 0.29 2.13 1.86 5.75

 HUB 12.59 343.81 160.24 304.18 1111.56 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 309.13 373.03 217.22 0.34 1650.76 0.92 0.86

 MEAN 267.05 342.73 159.02 0.31 1675.63 0.92 0.86 0.86 1.24

 HUB 216.94 309.42 56.71 0.28 2018.64 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.23 1.03 7.78 529.92 1.01 521.89 497.40 8.54

 MEAN 8.23 1.03 7.77 529.99 1.01 521.69 497.46 8.59

 HUB 8.28 1.03 7.75 530.94 1.01 521.49 498.03 8.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.86 35.61 31.50 4.11 0.93 0.19 1.40

 MEAN 19.59 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.78 10.56 6.50 4.06 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.942 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 363.7902 110.0035 346.7601 1109.6467 0.3278 -0.2480 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2346 7.6522 519.7037 497.8928 9.1268 17.6007 33.0000 15.3993

 

NASA/TM—2013-218094 O–83
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 360.1368 82.2376 350.6216 1109.8745 0.3245 -0.2687 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2096 7.6403 519.9153 497.8381 410.5396 0.0725 0.1462

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 350.3824 0.0000 350.3824 1110.4645 0.3155 0.0070 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6563 520.4695 497.8106 0.0000 0.0600 0.1033 -0.2351

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6845 8.1950 1.0235 530.2822 4.9087 362.7292 2.8119

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30709.229 0.321 68.731 401722.531 0.194281E-02 

 

Melt Ratio at Stator LE, Throat, TE

0.30299E-02 0.30299E-02 0.30512E-02

 trTOT = 1.0791 Tt4 = 530.2822 T1 = 491.4111

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 242725.19 543.2468 87.0091 1.2583 0.8246 9.2535 1.0791 37.3740

NASA/TM—2013-218094 O–84
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.667 EfDer = 0.999 SH = 0.105739E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.642 1797.020 7.939 506.409 1.000 1.000 0.980

 W Kg/sec = 22.110 Wdry = 48.590 WH2O = 0.051 lbm/sec H2O = 0.706g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.992 1818.697 1.380 0.249 53.383 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70208.000 38150.992 3.190 831.557 260.675 619.754 2.377

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.63 -0.07 202.63 0.19 0.35 327.41

 MEAN 17.06 0.00 -0.02 202.63 -0.07 202.63 0.19 0.31

 HUB 12.51 0.00 -0.02 202.63 -0.07 202.63 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.95 50.47 7.48 323.52 381.80 7.75 503.12 484.81 9.49

 MEAN 52.87 47.20 5.67 267.54 335.67 7.75 503.12 484.81 9.49

 HUB 44.08 38.62 5.46 196.18 282.09 7.75 503.12 484.81 9.49

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.08 172.76 280.09 1095.82 0.30 7.29 6.52 16.04

 MEAN 18.04 343.80 197.75 281.24 1094.97 0.31 7.43 6.80 12.53

 HUB 15.00 387.23 263.54 283.72 1093.26 0.35 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 323.52 318.09 150.76 0.29 3565.43 0.92 0.91

 MEAN 282.84 293.83 85.09 0.27 3567.84 0.92 0.91 0.91 1.28

 HUB 235.23 285.13 28.31 0.26 3953.97 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.42 1.06 7.91 515.37 1.02 506.69 490.48 9.65

 MEAN 8.42 1.06 7.87 515.38 1.02 505.90 490.56 9.89

 HUB 8.47 1.07 7.77 516.35 1.02 504.33 491.34 10.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.67 28.29 24.20 4.09 0.93 0.29 1.80

 MEAN 35.11 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.89 -5.70 -9.30 3.60 0.92 0.16 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 360.7457 197.3676 301.9660 1094.2592 0.3297 -0.0733 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4274 7.8247 505.2738 490.8895 10.2605 33.1690 35.4000 2.2310

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.1304 75.1335 297.7986 1097.3555 0.2799 0.2305 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4254 7.9854 508.1425 490.6383 554.9116 0.0135 0.3506

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 304.8211 0.0000 304.8211 1097.4689 0.2777 0.2546 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9782 508.2562 490.7684 0.0000 0.0600 0.0383 0.2181

NASA/TM—2013-218094 O–85
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 8.4110 1.0594 515.6976 9.2889 222.2218 1.7226

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57989.602 0.554 159.402 473451.094 0.131289E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.226 EfDer = 0.987 SH = 0.155659E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.642 1797.020 8.411 515.697 1.000 1.000 0.980

 W Kg/sec = 22.110 Wdry = 48.566 WH2O = 0.076 lbm/sec H2O = 1.064g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.766 1802.243 1.379 0.250 53.399 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68507.922 38143.492 2.377 590.487 248.369 468.502 1.886

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.44 -0.10 278.44 0.25 0.39 323.19

 MEAN 18.08 0.00 -0.02 278.44 -0.10 278.44 0.25 0.36

 HUB 15.21 0.00 -0.02 278.44 -0.10 278.44 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.18 46.36 2.82 322.26 425.96 8.05 509.49 491.27 11.40

 MEAN 45.53 42.30 3.23 283.50 397.44 8.05 509.49 491.27 11.40

 HUB 40.60 37.84 2.76 238.52 366.70 8.05 509.49 491.27 11.40

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.78 106.68 303.58 1102.40 0.29 2.33 2.04 9.02

 MEAN 18.01 328.99 126.12 303.85 1102.25 0.30 2.40 2.13 7.35

 HUB 15.22 355.37 183.49 304.33 1102.10 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 320.23 371.16 213.54 0.34 2180.47 0.92 0.90

 MEAN 282.43 341.70 156.31 0.31 2273.23 0.92 0.90 0.90 1.25

 HUB 238.73 309.30 55.23 0.28 2794.75 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.71 1.04 8.21 521.17 1.01 512.88 494.36 10.55

 MEAN 8.72 1.04 8.21 521.40 1.01 512.74 494.53 10.60

 HUB 8.79 1.05 8.19 522.71 1.01 512.61 495.34 10.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.36 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.54 27.22 23.50 3.72 0.92 0.24 1.63

 HUB 31.09 10.29 6.50 3.79 0.92 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.5287 126.4785 342.9495 1100.4369 0.3322 -0.1932 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7352 8.1016 511.0717 494.9782 11.1944 20.2438 30.6000 10.3562

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 338.7641 71.8204 331.0633 1102.0609 0.3074 -0.0414 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7271 8.1813 512.5798 494.7930 491.5697 0.0251 0.1628

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 351.3944 0.0000 351.3944 1101.3069 0.3191 0.0261 0.5911

NASA/TM—2013-218094 O–86
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1181 511.8829 494.9166 0.0000 0.0600 0.0705 -0.1590

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8008 8.7027 1.0347 521.7606 6.0632 301.9909 2.3410

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37899.855 0.370 104.179 439105.344 0.164823E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.156 EfDer = 0.947 SH = 0.175819E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.642 1797.020 8.703 521.760 1.000 1.000 0.980

 W Kg/sec = 22.110 Wdry = 48.556 WH2O = 0.086 lbm/sec H2O = 1.225g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.405 1791.741 1.379 0.250 53.405 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67248.844 38140.461 2.259 545.479 241.485 424.468 1.758

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 295.88 -0.10 295.88 0.27 0.39 313.80

 MEAN 17.74 0.00 -0.02 295.88 -0.10 295.88 0.27 0.37

 HUB 15.05 0.00 -0.02 295.88 -0.10 295.88 0.27 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.78 46.36 0.42 314.74 432.05 8.29 514.76 494.83 10.92

 MEAN 43.24 43.40 -0.16 278.17 406.18 8.29 514.76 494.83 10.92

 HUB 38.59 38.84 -0.25 236.01 378.54 8.29 514.76 494.83 10.92

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.50 81.41 323.41 1106.68 0.30 2.26 1.98 8.75

 MEAN 17.51 340.30 106.65 323.15 1106.97 0.31 2.34 2.07 6.78

 HUB 14.85 366.48 172.73 323.22 1107.26 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 310.66 396.42 229.25 0.36 1614.72 0.92 0.87

 MEAN 274.54 364.16 167.88 0.33 1868.95 0.92 0.87 0.87 1.19

 HUB 232.88 328.77 60.15 0.30 2566.60 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.92 1.02 8.38 525.81 1.01 516.92 497.11 10.47

 MEAN 8.95 1.03 8.39 526.45 1.01 517.19 497.46 10.38

 HUB 9.05 1.04 8.39 528.20 1.01 517.46 498.47 10.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 14.13 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.27 27.45 23.50 3.95 0.90 0.18 1.62

 HUB 28.12 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.947 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.0854 107.3536 364.6096 1104.9034 0.3440 -0.2076 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9661 8.2711 515.2683 497.9616 11.0290 16.4062 31.5000 15.0938

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 366.5066 79.9509 357.6800 1105.7749 0.3314 -0.1465 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9501 8.3038 516.0790 497.8433 451.3937 0.0373 0.1183

 

NASA/TM—2013-218094 O–87
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 373.7532 0.0000 373.7532 1105.3130 0.3381 -0.0386 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2442 515.6505 497.9072 0.0000 0.0600 0.1012 -0.2487

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6788 8.9129 1.0242 526.8182 5.0576 342.6302 2.6560

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31634.492 0.328 86.957 444688.406 0.184846E-02

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.239 EfDer = 0.889 SH = 0.195806E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.642 1797.020 8.913 526.818 1.000 1.000 0.980

 W Kg/sec = 22.110 Wdry = 48.547 WH2O = 0.095 lbm/sec H2O = 1.379g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.850 1783.120 1.379 0.250 53.412 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66532.984 38137.449 2.166 513.330 236.959 395.845 1.671

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 311.06 -0.11 311.06 0.28 0.39 299.69

 MEAN 16.97 0.00 -0.02 311.06 -0.11 311.06 0.28 0.37

 HUB 14.32 0.00 -0.02 311.06 -0.11 311.06 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.17 46.36 -2.19 302.03 433.65 8.45 519.09 497.71 10.60

 MEAN 40.56 43.80 -3.24 266.13 409.44 8.45 519.09 497.71 10.60

 HUB 35.84 37.84 -2.00 224.57 383.72 8.45 519.09 497.71 10.60

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 343.60 54.21 339.30 1109.89 0.31 2.16 1.89 8.34

 MEAN 16.57 348.66 82.97 338.64 1110.53 0.31 2.24 1.97 6.35

 HUB 13.89 371.98 154.30 338.47 1111.15 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 296.08 416.68 241.87 0.38 1025.48 0.92 0.81

 MEAN 259.91 382.08 176.94 0.34 1376.98 0.92 0.81 0.81 1.14

 HUB 217.82 344.38 63.52 0.31 2144.75 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.04 1.01 8.47 529.39 1.00 519.95 499.21 10.53

 MEAN 9.09 1.02 8.50 530.27 1.01 520.55 499.65 10.34

 HUB 9.19 1.03 8.51 532.19 1.01 521.14 500.69 10.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 9.08 35.48 31.50 3.98 0.93 0.08 1.40

 MEAN 13.77 27.59 23.50 4.09 0.89 0.13 1.62

 HUB 24.51 10.63 6.50 4.13 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.889 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.2029 83.4383 372.9840 1108.7993 0.3447 -0.1705 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0987 8.3908 518.9446 500.0952 10.8581 12.6097 32.4000 19.7903

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 382.4800 85.7791 372.7371 1108.7842 0.3450 -0.2005 2.2705

 

NASA/TM—2013-218094 O–88
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0753 8.3682 518.9276 500.0745 432.2457 0.0481 0.0821

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 380.8919 0.0000 380.8919 1108.8867 0.3435 -0.0895 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3275 519.0242 500.0279 0.0000 0.0600 0.1303 -0.2670

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4766 9.0249 1.0126 530.6155 3.7985 422.2346 3.2731

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23773.406 0.271 65.348 463308.031 0.203938E-02

 

Melt Ratio at Stator LE, Throat, TE

0.21890E-01 0.23913E-01 0.30326E-01

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.101 EfDer = 0.826 SH = 0.214232E-02

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.642 1797.020 9.025 530.615 1.000 1.000 0.980

 W Kg/sec = 22.110 Wdry = 48.538 WH2O = 0.104 lbm/sec H2O = 1.517g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.134 1776.728 1.378 0.250 53.418 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66179.219 38134.680 2.170 509.668 234.888 384.739 1.638

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 311.63 -0.11 311.63 0.28 0.38 284.04

 MEAN 15.91 0.00 -0.02 311.63 -0.11 311.63 0.28 0.36

 HUB 13.07 0.00 -0.02 311.63 -0.11 311.63 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.68 47.36 -4.68 287.29 423.93 8.55 522.86 499.72 10.28

 MEAN 38.70 44.80 -6.10 249.55 399.30 8.55 522.86 499.72 10.28

 HUB 33.35 38.84 -5.49 204.96 373.05 8.55 522.86 499.72 10.28

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 342.35 36.20 340.43 1112.97 0.31 2.05 1.78 7.43

 MEAN 15.50 345.71 63.79 339.77 1113.68 0.31 2.13 1.86 5.75

 HUB 12.59 364.77 133.03 339.65 1114.36 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 281.33 419.51 245.13 0.38 651.42 0.92 0.76

 MEAN 243.03 384.15 179.24 0.34 990.31 0.92 0.76 0.76 1.11

 HUB 197.44 345.70 64.40 0.31 1676.29 0.92 0.76

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.10 1.01 8.53 532.25 1.00 522.89 500.75 10.42

 MEAN 9.14 1.01 8.56 533.09 1.00 523.55 501.15 10.21

 HUB 9.22 1.02 8.57 534.81 1.01 524.19 502.04 10.01

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 6.07 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.63 27.81 23.50 4.31 0.87 0.09 1.64

 HUB 21.39 10.74 6.50 4.24 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.826 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 394.8201 64.9607 389.4394 1110.8905 0.3554 -0.2824 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1434 8.3896 520.9359 501.7089 11.0192 9.4701 33.0000 23.5299

 

NASA/TM—2013-218094 O–89
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 407.7911 93.1194 397.0168 1110.0089 0.3674 -0.4380 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0892 8.2915 520.1042 501.7593 410.5396 0.1101 0.0550

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 396.6086 0.0000 396.6086 1110.7760 0.3571 -0.0999 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3144 520.8216 501.6620 0.0000 0.0600 0.1446 -0.4000

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2537 9.0685 1.0048 533.3826 2.7694 533.4933 4.1356

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17342.613 0.219 47.671 493265.500 0.221779E-02

 

Melt Ratio at Stator LE, Throat, TE

0.82500E-01 0.86728E-01 0.98848E-01

 trTOT = 1.0533 Tt4 = 533.3826 T1 = 506.4091

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 168639.95 463.5572 88.9916 1.1423 0.6988 5.6671 1.0533 37.3740

NASA/TM—2013-218094 O–90
25μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.160 EfDer = 0.957 SH = 0.757291E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.808 2406.177 4.265 457.733 1.000 1.000 0.980

 W Kg/sec = 12.185 Wdry = 26.806 WH2O = 0.002 lbm/sec H2O = 0.030g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.805 2561.392 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65010.715 21034.178 3.273 831.557 254.091 619.754 2.439

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 187.63 -0.06 187.63 0.18 0.45 461.12

 MEAN 17.06 0.00 -0.02 187.63 -0.06 187.63 0.18 0.39

 HUB 12.51 0.00 -0.02 187.63 -0.06 187.63 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.58 50.47 16.11 433.19 472.13 4.17 454.90 448.33 2.90

 MEAN 62.36 47.20 15.16 358.23 404.45 4.17 454.90 448.33 2.90

 HUB 54.47 38.62 15.85 262.68 322.86 4.17 454.90 448.33 2.90

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 389.11 297.17 251.19 1051.48 0.37 7.29 6.52 16.04

 MEAN 18.04 394.31 301.19 254.48 1048.45 0.38 7.43 6.80 12.53

 HUB 15.00 427.84 340.50 259.05 1044.69 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 433.19 285.65 136.01 0.27 6132.02 0.92 0.88

 MEAN 378.72 266.03 77.53 0.25 5433.42 0.92 0.88 0.88 1.74

 HUB 314.97 260.31 25.53 0.25 5108.29 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 478.44 1.05 466.27 462.42 2.23

 MEAN 4.83 1.13 4.39 476.08 1.04 463.58 460.94 2.47

 HUB 4.80 1.12 4.28 474.99 1.04 460.26 460.28 2.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.79 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.81 16.94 12.70 4.24 0.95 0.51 2.22

 HUB 52.74 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 406.0353 300.6079 272.9461 1048.0632 0.3874 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8415 4.3711 463.2456 461.2161 2.5580 47.7612 35.4000 -12.3612

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 270.9535 66.2835 262.7209 1056.3455 0.2565 0.5081 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8301 4.6168 470.5998 461.0930 554.9116 0.0345 0.6002

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 269.7996 0.0000 269.7996 1056.3905 0.2554 0.4801 1.3089

NASA/TM—2013-218094 O–91
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5969 470.6497 461.0742 0.0000 0.0600 0.0831 0.4655

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8200 4.8074 1.1273 476.5031 18.7717 169.4341 1.3134

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 116724.781 0.622 176.831 281204.188 0.104176E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.690 EfDer = 0.961 SH = 0.135903E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.808 2406.177 4.807 476.503 1.000 1.000 0.980

 W Kg/sec = 12.185 Wdry = 26.804 WH2O = 0.004 lbm/sec H2O = 0.058g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.567 2510.457 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60689.570 21033.680 2.567 590.487 229.989 468.502 2.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 246.67 -0.08 246.67 0.23 0.47 450.19

 MEAN 18.08 0.00 -0.02 246.67 -0.08 246.67 0.23 0.43

 HUB 15.21 0.00 -0.02 246.67 -0.08 246.67 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.25 46.36 13.89 431.51 497.11 4.63 471.61 461.17 2.67

 MEAN 56.99 42.30 14.69 379.60 452.78 4.63 471.61 461.17 2.67

 HUB 52.33 37.84 14.49 319.38 403.61 4.63 471.61 461.17 2.67

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 357.99 246.34 259.76 1070.36 0.33 2.33 2.04 9.02

 MEAN 18.01 358.03 243.64 262.35 1067.96 0.34 2.40 2.13 7.35

 HUB 15.22 379.96 272.07 265.24 1065.58 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 428.78 317.42 182.44 0.30 5031.92 0.92 0.88

 MEAN 378.17 294.84 134.53 0.28 4389.40 0.92 0.88 0.88 1.69

 HUB 319.65 269.47 47.58 0.25 4143.01 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 493.49 1.04 483.19 471.46 1.82

 MEAN 5.30 1.10 4.91 491.32 1.03 481.02 470.22 1.97

 HUB 5.27 1.10 4.83 490.49 1.03 478.88 469.77 2.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.48 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.88 27.15 23.50 3.65 0.95 0.51 1.63

 HUB 45.73 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 383.3097 244.3196 295.3544 1066.7676 0.3593 -0.1092 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3125 4.8646 479.9571 470.4999 2.0531 39.5978 30.6000 -8.9978

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 285.8075 60.5932 279.3105 1072.5791 0.2665 0.3583 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3067 5.0544 485.2022 470.4005 491.5697 0.0242 0.4558

 

NASA/TM—2013-218094 O–92
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.2314 0.0000 296.2314 1072.0310 0.2763 0.3494 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0211 484.7143 470.3872 0.0000 0.0600 0.0628 0.2767

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8366 5.2909 1.1006 491.7691 15.2670 191.1124 1.4815

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 94957.875 0.516 143.855 255351.516 0.148324E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.696 EfDer = 0.976 SH = 0.165413E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.808 2406.177 5.291 491.769 1.000 1.000 0.980

 W Kg/sec = 12.185 Wdry = 26.803 WH2O = 0.004 lbm/sec H2O = 0.075g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.522 2471.184 1.381 0.248 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56908.867 21033.436 2.569 545.479 212.300 424.468 1.999

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.39 -0.09 250.39 0.23 0.46 432.80

 MEAN 17.74 0.00 -0.02 250.39 -0.09 250.39 0.23 0.42

 HUB 15.05 0.00 -0.02 250.39 -0.09 250.39 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.29 46.36 12.93 421.43 490.27 5.10 486.73 470.41 1.87

 MEAN 56.10 43.40 12.70 372.47 448.88 5.10 486.73 470.41 1.87

 HUB 51.62 38.84 12.78 316.02 403.26 5.10 486.73 470.41 1.87

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 350.06 230.30 263.64 1085.88 0.32 2.26 1.98 8.75

 MEAN 17.51 352.07 230.73 265.92 1083.83 0.32 2.34 2.07 6.78

 HUB 14.85 375.91 263.15 268.44 1081.81 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.97 322.46 185.67 0.30 4563.98 0.92 0.89

 MEAN 367.60 299.08 136.87 0.28 4040.84 0.92 0.89 0.89 1.64

 HUB 311.82 272.82 48.67 0.25 3909.07 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.85 1.11 5.45 507.18 1.03 497.33 478.96 1.36

 MEAN 5.78 1.09 5.38 505.41 1.03 495.45 478.03 1.45

 HUB 5.76 1.09 5.31 504.97 1.03 493.61 477.82 1.54

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.14 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.95 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.43 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 378.5036 232.2454 298.8763 1082.5999 0.3496 -0.1171 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7936 5.3298 494.3347 478.2858 1.5122 37.8494 31.5000 -6.3494

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 294.1625 64.1696 287.0781 1087.5806 0.2705 0.3065 2.3726

 

NASA/TM—2013-218094 O–93
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7899 5.5066 498.8949 478.2044 451.3937 0.0188 0.4304

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 299.1237 0.0000 299.1237 1087.3138 0.2751 0.3339 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4847 498.6581 478.1913 0.0000 0.0600 0.0501 0.2543

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8570 5.7768 1.0918 505.8499 14.0818 196.5973 1.5240

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87603.977 0.506 132.715 253743.719 0.180114E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.102 EfDer = 0.986 SH = 0.201317E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.808 2406.177 5.777 505.850 1.000 1.000 0.980

 W Kg/sec = 12.185 Wdry = 26.803 WH2O = 0.005 lbm/sec H2O = 0.097g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.367 2436.547 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53577.164 21033.139 2.603 513.330 197.217 395.845 2.007

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.49 -0.09 250.49 0.23 0.44 409.51

 MEAN 16.97 0.00 -0.02 250.49 -0.09 250.49 0.23 0.40

 HUB 14.32 0.00 -0.02 250.49 -0.09 250.49 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.23 46.36 11.87 404.42 475.78 5.57 500.81 478.21 1.42

 MEAN 54.90 43.80 11.10 356.35 435.65 5.57 500.81 478.21 1.42

 HUB 50.21 37.84 12.37 300.69 391.42 5.57 500.81 478.21 1.42

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 337.11 210.93 262.97 1099.78 0.31 2.16 1.89 8.34

 MEAN 16.57 339.04 211.45 265.02 1097.92 0.31 2.24 1.97 6.35

 HUB 13.89 361.40 243.27 267.26 1096.10 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 396.44 321.82 185.51 0.29 3983.99 0.92 0.90 

 MEAN 348.02 298.14 136.57 0.27 3505.99 0.92 0.90 0.90 1.60

 HUB 291.66 271.61 48.39 0.25 3380.22 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.29 1.09 5.90 519.30 1.03 510.16 485.16 1.10

 MEAN 6.23 1.08 5.84 517.68 1.02 508.44 484.37 1.16

 HUB 6.21 1.08 5.77 517.26 1.02 506.76 484.18 1.22

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.73 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.58 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.31 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 360.1203 212.6379 290.6402 1097.0609 0.3283 -0.0927 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2425 5.7992 507.6569 484.5787 1.1959 36.1899 32.4000 -3.7899

 

NASA/TM—2013-218094 O–94
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 291.9123 65.4674 284.4764 1100.9139 0.2652 0.2691 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2406 5.9467 511.2309 484.5188 432.2457 0.0146 0.4088

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.5780 0.0000 289.5780 1101.0233 0.2630 0.3195 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9408 511.3399 484.5050 0.0000 0.0600 0.0415 0.2547

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8702 6.2295 1.0784 518.0785 12.2295 212.0030 1.6434

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76097.578 0.484 115.283 259594.844 0.219144E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.642 EfDer = 0.993 SH = 0.245945E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.808 2406.177 6.230 518.078 1.000 1.000 0.980

 W Kg/sec = 12.185 Wdry = 26.801 WH2O = 0.007 lbm/sec H2O = 0.125g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.221 2407.620 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50735.617 21032.771 2.754 509.668 185.089 384.739 2.079

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 238.91 -0.08 238.91 0.22 0.41 384.90

 MEAN 15.91 0.00 -0.02 238.91 -0.08 238.91 0.22 0.37

 HUB 13.07 0.00 -0.02 238.91 -0.08 238.91 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.16 47.36 10.80 384.68 452.90 6.03 513.49 484.53 1.16

 MEAN 54.44 44.80 9.64 334.14 410.83 6.03 513.49 484.53 1.16

 HUB 48.97 38.84 10.13 274.44 363.93 6.03 513.49 484.53 1.16

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 320.10 198.15 251.40 1112.27 0.29 2.05 1.78 7.43

 MEAN 15.50 319.20 194.10 253.40 1110.35 0.29 2.13 1.86 5.75

 HUB 12.59 335.91 218.03 255.54 1108.46 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.70 308.35 178.55 0.28 3556.34 0.92 0.91

 MEAN 325.42 285.40 131.31 0.26 3009.47 0.92 0.91 0.91 1.59

 HUB 264.36 259.70 46.34 0.23 2746.03 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.08 6.35 530.08 1.02 521.85 490.39 0.95

 MEAN 6.64 1.07 6.28 528.23 1.02 520.05 489.53 1.00

 HUB 6.60 1.06 6.20 527.34 1.02 518.28 489.12 1.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.25 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.45 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.47 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 349.6348 197.6640 288.3980 1108.9291 0.3153 -0.1729 2.0437

 

NASA/TM—2013-218094 O–95
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6470 6.2100 518.7302 489.6932 1.0432 34.4262 33.0000 -1.4262

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.7655 67.3100 286.9775 1111.9602 0.2651 0.1509 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6450 6.3323 521.5709 489.6436 410.5396 0.0252 0.3844

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.7317 0.0000 286.7317 1112.3530 0.2578 0.3077 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3445 521.9461 489.6415 0.0000 0.0600 0.0373 0.1829

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 6.6404 1.0660 528.5513 10.4736 231.6919 1.7961

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65188.008 0.459 98.756 272157.563 0.267726E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1547 Tt4 = 528.5513 T1 = 457.7325

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 440572.19 667.4399 86.8047 1.5571 0.8401 15.1597 1.1547 37.3740

NASA/TM—2013-218094 O–96
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.262 EfDer = 0.956 SH = 0.710167E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.833 2330.941 4.199 451.559 1.000 1.000 0.980

 W Kg/sec = 11.742 Wdry = 25.831 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.375 2498.209 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62705.395 20269.203 3.367 831.557 246.980 619.754 2.509

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 180.98 -0.06 180.98 0.18 0.44 449.74

 MEAN 17.06 0.00 -0.02 180.98 -0.06 180.98 0.18 0.38

 HUB 12.51 0.00 -0.02 180.98 -0.06 180.98 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.67 50.47 16.20 419.64 457.06 4.11 448.92 443.94 3.59

 MEAN 62.46 47.20 15.26 347.03 391.44 4.11 448.92 443.94 3.59

 HUB 54.59 38.62 15.97 254.47 312.31 4.11 448.92 443.94 3.59

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 376.85 288.16 242.86 1043.93 0.36 7.29 6.52 16.04

 MEAN 18.04 381.73 292.00 245.87 1041.07 0.37 7.43 6.80 12.53

 HUB 15.00 413.83 329.74 250.05 1037.53 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 419.64 276.16 131.49 0.26 5945.94 0.92 0.87

 MEAN 366.88 257.02 74.87 0.25 5267.66 0.92 0.87 0.87 1.75

 HUB 305.12 251.26 24.63 0.24 4946.95 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 471.01 1.04 459.59 457.85 2.74

 MEAN 4.73 1.13 4.32 468.79 1.04 457.07 456.38 3.03

 HUB 4.70 1.12 4.21 467.75 1.04 453.97 455.71 3.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.88 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.90 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.83 -5.62 -9.30 3.68 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 393.0082 291.4371 263.6662 1040.7087 0.3776 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7381 4.2993 456.7627 456.6496 3.1298 47.8640 35.4000 -12.4640

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.2315 64.1498 254.2639 1048.5262 0.2501 0.5091 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7278 4.5290 463.6540 456.5348 554.9116 0.0339 0.6008

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.0894 0.0000 261.0894 1048.5703 0.2490 0.4800 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5099 463.7017 456.5193 0.0000 0.0600 0.0837 0.4653

NASA/TM—2013-218094 O–97
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8188 4.7061 1.1207 469.1836 17.6256 169.0044 1.3101

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 109593.594 0.622 159.989 273551.438 0.948329E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.710 EfDer = 0.961 SH = 0.121340E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.833 2330.941 4.706 469.183 1.000 1.000 0.980

 W Kg/sec = 11.742 Wdry = 25.830 WH2O = 0.003 lbm/sec H2O = 0.051g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.744 2450.857 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58746.426 20268.803 2.628 590.487 224.650 468.502 2.085

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.77 -0.08 238.77 0.23 0.46 439.51

 MEAN 18.08 0.00 -0.02 238.77 -0.08 238.77 0.23 0.42

 HUB 15.21 0.00 -0.02 238.77 -0.08 238.77 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.27 46.36 13.91 418.01 481.47 4.54 464.60 456.61 3.21

 MEAN 57.01 42.30 14.71 367.74 438.52 4.54 464.60 456.61 3.21

 HUB 52.35 37.84 14.51 309.39 390.88 4.54 464.60 456.61 3.21

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 346.93 238.37 252.06 1061.75 0.33 2.33 2.04 9.02

 MEAN 18.01 346.98 235.90 254.45 1059.48 0.33 2.40 2.13 7.35

 HUB 15.22 368.18 263.54 257.11 1057.25 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.37 308.00 177.00 0.29 4869.28 0.92 0.88

 MEAN 366.35 285.94 130.45 0.27 4249.96 0.92 0.88 0.88 1.69

 HUB 309.66 261.21 46.12 0.25 4013.12 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.24 1.11 4.87 485.11 1.03 475.43 466.81 2.21

 MEAN 5.17 1.10 4.80 483.09 1.03 473.41 465.58 2.38

 HUB 5.14 1.09 4.73 482.31 1.03 471.41 465.13 2.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.40 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.83 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.71 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.4385 236.5582 286.3683 1058.3558 0.3510 -0.1094 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1761 4.7587 472.4097 465.8562 2.4811 39.5588 30.6000 -8.9588

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 277.4830 58.8284 271.1753 1063.8314 0.2608 0.3569 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1710 4.9351 477.3119 465.7645 491.5697 0.0235 0.4543

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 287.5384 0.0000 287.5384 1063.3143 0.2704 0.3478 0.5911

NASA/TM—2013-218094 O–98
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9039 476.8549 465.7539 0.0000 0.0600 0.0626 0.2749

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8365 5.1561 1.0956 483.5023 14.3197 191.1253 1.4816

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89058.492 0.516 130.011 248638.234 0.131767E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.630 EfDer = 0.976 SH = 0.146079E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.833 2330.941 5.156 483.502 1.000 1.000 0.980

 W Kg/sec = 11.742 Wdry = 25.829 WH2O = 0.004 lbm/sec H2O = 0.066g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.107 2414.294 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55265.527 20268.607 2.621 545.479 208.154 424.468 2.039 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.16 -0.08 243.16 0.23 0.45 422.84

 MEAN 17.74 0.00 -0.02 243.16 -0.08 243.16 0.23 0.41

 HUB 15.05 0.00 -0.02 243.16 -0.08 243.16 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.23 46.36 12.87 408.25 475.25 4.97 478.75 465.77 2.26

 MEAN 56.03 43.40 12.63 360.82 435.18 4.97 478.75 465.77 2.26

 HUB 51.55 38.84 12.71 306.14 391.02 4.97 478.75 465.77 2.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.51 222.31 256.60 1076.37 0.32 2.26 1.98 8.75

 MEAN 17.51 341.54 222.99 258.70 1074.45 0.32 2.34 2.07 6.78

 HUB 14.85 364.72 254.73 261.02 1072.56 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.96 313.81 180.65 0.29 4405.73 0.92 0.89

 MEAN 356.11 290.94 133.11 0.27 3905.34 0.92 0.89 0.89 1.64

 HUB 302.07 265.28 47.34 0.25 3783.98 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.67 1.10 5.30 497.91 1.03 488.64 474.25 1.65

 MEAN 5.61 1.09 5.24 496.28 1.03 486.90 473.34 1.76

 HUB 5.60 1.09 5.17 495.88 1.03 485.18 473.14 1.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.91 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.76 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.30 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 367.2573 224.4572 290.6834 1073.2762 0.3422 -0.1178 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6220 5.1899 485.8452 473.5897 1.8318 37.6743 31.5000 -6.1743

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.4391 62.4847 279.5407 1077.9559 0.2657 0.3023 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6189 5.3532 490.0922 473.5147 451.3937 0.0181 0.4269

 

NASA/TM—2013-218094 O–99
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.2262 0.0000 291.2262 1077.7037 0.2702 0.3306 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3328 489.8696 473.5040 0.0000 0.0600 0.0494 0.2501

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8577 5.6066 1.0874 496.6875 13.1862 197.1773 1.5285

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 82023.664 0.505 119.741 247379.250 0.158375E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.955 EfDer = 0.987 SH = 0.176184E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.833 2330.941 5.607 496.687 1.000 1.000 0.980

 W Kg/sec = 11.742 Wdry = 25.828 WH2O = 0.005 lbm/sec H2O = 0.084g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.278 2382.033 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52184.211 20268.367 2.646 513.330 194.025 395.845 2.040

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 243.98 -0.08 243.98 0.23 0.43 400.35

 MEAN 16.97 0.00 -0.02 243.98 -0.08 243.98 0.23 0.39

 HUB 14.32 0.00 -0.02 243.98 -0.08 243.98 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.09 46.36 11.73 391.77 461.60 5.41 491.90 473.52 1.72

 MEAN 54.76 43.80 10.96 345.21 422.79 5.41 491.90 473.52 1.72

 HUB 50.06 37.84 12.22 291.29 380.03 5.41 491.90 473.52 1.72

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.25 203.04 256.64 1089.46 0.30 2.16 1.89 8.34

 MEAN 16.57 329.29 203.94 258.53 1087.73 0.30 2.24 1.97 6.35

 HUB 13.89 351.14 235.35 260.60 1086.03 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.04 314.04 181.00 0.29 3835.10 0.92 0.90

 MEAN 337.13 290.82 133.19 0.27 3381.54 0.92 0.90 0.90 1.59

 HUB 282.54 264.83 47.19 0.24 3270.28 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.08 1.09 5.72 509.23 1.03 500.62 480.40 1.34

 MEAN 6.03 1.07 5.66 507.75 1.02 499.03 479.62 1.41

 HUB 6.01 1.07 5.60 507.38 1.02 497.47 479.45 1.48

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.35 35.19 31.50 3.69 0.93 0.48 1.40

 MEAN 38.27 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.09 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.8846 205.0893 283.4742 1086.8971 0.3219 -0.0936 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0366 5.6236 498.2784 479.8333 1.4516 35.8852 32.4000 -3.4852

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 284.9962 63.9163 277.7365 1090.5007 0.2613 0.2624 2.2705

 

NASA/TM—2013-218094 O–100
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0350 5.7587 501.5895 479.7783 432.2457 0.0141 0.4034

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 282.6978 0.0000 282.6978 1090.6079 0.2592 0.3142 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7534 501.6942 479.7666 0.0000 0.0600 0.0408 0.2484

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8712 6.0248 1.0746 508.1174 11.4308 213.2405 1.6530

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71117.852 0.482 103.821 253372.438 0.191180E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.423 EfDer = 0.994 SH = 0.213797E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.833 2330.941 6.025 508.117 1.000 1.000 0.980

 W Kg/sec = 11.742 Wdry = 25.827 WH2O = 0.006 lbm/sec H2O = 0.107g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.383 2355.089 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49546.383 20268.068 2.791 509.668 182.630 384.739 2.107

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 233.31 -0.08 233.31 0.21 0.40 376.50

 MEAN 15.91 0.00 -0.02 233.31 -0.08 233.31 0.21 0.37

 HUB 13.07 0.00 -0.02 233.31 -0.08 233.31 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.96 47.36 10.60 372.65 439.73 5.84 503.74 479.79 1.41

 MEAN 54.22 44.80 9.42 323.69 399.08 5.84 503.74 479.79 1.41

 HUB 48.74 38.84 9.90 265.86 353.78 5.84 503.74 479.79 1.41

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 310.94 190.26 245.93 1101.22 0.28 2.05 1.78 7.43

 MEAN 15.50 310.34 186.86 247.78 1099.43 0.28 2.13 1.86 5.75

 HUB 12.59 326.84 210.83 249.76 1097.66 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 364.92 301.65 174.66 0.27 3414.72 0.92 0.91

 MEAN 315.24 279.07 128.38 0.25 2897.13 0.92 0.91 0.91 1.58

 HUB 256.10 253.83 45.27 0.23 2655.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.47 1.07 6.13 519.28 1.02 511.51 485.57 1.15

 MEAN 6.40 1.06 6.06 517.59 1.02 509.85 484.73 1.21

 HUB 6.37 1.06 6.00 516.80 1.02 508.21 484.35 1.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.73 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.02 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.17 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 340.1484 190.2841 281.9449 1098.0608 0.3098 -0.1746 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4087 6.0014 508.5917 484.8971 1.2682 34.0153 33.0000 -1.0153

 

NASA/TM—2013-218094 O–101
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 288.4118 65.8591 280.7916 1100.8773 0.2620 0.1412 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4071 6.1124 511.2049 484.8521 410.5396 0.0245 0.3775

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 280.5623 0.0000 280.5623 1101.2577 0.2548 0.3004 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1237 511.5636 484.8502 0.0000 0.0600 0.0370 0.1734

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8799 6.4027 1.0627 517.8888 9.7722 233.6680 1.8114

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 60811.801 0.457 88.776 265910.156 0.232265E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1469 Tt4 = 517.8888 T1 = 451.5591

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 412605.41 602.3381 84.3755 1.5247 0.8404 15.2617 1.1469 37.3740

NASA/TM—2013-218094 O–102
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.307 EfDer = 0.956 SH = 0.665101E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.424 2302.428 4.337 449.670 1.000 1.000 0.980

 W Kg/sec = 12.011 Wdry = 26.423 WH2O = 0.002 lbm/sec H2O = 0.027g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.388 2472.829 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 61819.016 20733.348 3.407 831.557 244.090 619.754 2.539

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 178.42 -0.06 178.42 0.17 0.44 445.17

 MEAN 17.06 0.00 -0.02 178.42 -0.06 178.42 0.17 0.38

 HUB 12.51 0.00 -0.02 178.42 -0.06 178.42 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.71 50.47 16.24 414.51 451.33 4.25 447.11 442.74 3.80

 MEAN 62.51 47.20 15.31 342.78 386.49 4.25 447.11 442.74 3.80

 HUB 54.64 38.62 16.02 251.36 308.29 4.25 447.11 442.74 3.80

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 372.18 284.77 239.64 1041.57 0.36 7.29 6.52 16.04

 MEAN 18.04 376.94 288.53 242.55 1038.77 0.36 7.43 6.80 12.53

 HUB 15.00 408.49 325.66 246.59 1035.32 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 414.51 272.51 129.74 0.26 5876.03 0.92 0.87

 MEAN 362.39 253.55 73.86 0.24 5205.00 0.92 0.87 0.87 1.75

 HUB 301.39 247.78 24.28 0.24 4885.70 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 468.66 1.04 457.52 456.61 2.90

 MEAN 4.87 1.12 4.45 466.49 1.04 455.06 455.14 3.20

 HUB 4.84 1.12 4.35 465.46 1.04 452.04 454.46 3.62

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.92 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.95 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.87 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 388.0404 287.9706 260.0928 1038.4220 0.3737 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8819 4.4386 454.7609 455.4124 3.3040 47.9119 35.4000 -12.5119

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 258.8680 63.3270 251.0027 1046.0629 0.2475 0.5097 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8715 4.6709 461.4811 455.3045 554.9116 0.0336 0.6011

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.7307 0.0000 257.7307 1046.1064 0.2464 0.4800 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6514 461.5280 455.2896 0.0000 0.0600 0.0840 0.4653

NASA/TM—2013-218094 O–103
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8182 4.8494 1.1181 466.8698 17.2010 168.8117 1.3086

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 106953.977 0.622 159.711 280612.125 0.878088E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.724 EfDer = 0.961 SH = 0.111474E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.424 2302.428 4.849 466.870 1.000 1.000 0.980

 W Kg/sec = 12.011 Wdry = 26.421 WH2O = 0.003 lbm/sec H2O = 0.049g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.993 2426.868 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57997.063 20732.984 2.654 590.487 222.452 468.502 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 235.73 -0.08 235.73 0.23 0.45 435.20

 MEAN 18.08 0.00 -0.02 235.73 -0.08 235.73 0.23 0.41

 HUB 15.21 0.00 -0.02 235.73 -0.08 235.73 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.28 46.36 13.92 412.90 475.52 4.68 462.40 455.37 3.36

 MEAN 57.02 42.30 14.72 363.24 433.09 4.68 462.40 455.37 3.36

 HUB 52.36 37.84 14.52 305.61 386.02 4.68 462.40 455.37 3.36

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 342.73 235.41 249.09 1058.98 0.32 2.33 2.04 9.02

 MEAN 18.01 342.77 233.01 251.40 1056.77 0.32 2.40 2.13 7.35

 HUB 15.22 363.69 260.33 253.97 1054.58 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.29 304.35 174.88 0.29 4808.80 0.92 0.88

 MEAN 361.86 282.50 128.86 0.27 4197.89 0.92 0.88 0.88 1.69

 HUB 305.87 258.02 45.54 0.24 3964.20 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.11 5.01 482.41 1.03 472.96 465.58 2.32

 MEAN 5.31 1.10 4.94 480.43 1.03 470.99 464.35 2.50

 HUB 5.29 1.09 4.87 479.68 1.03 469.04 463.90 2.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.38 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.83 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.71 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.9165 233.6599 282.8972 1055.6681 0.3476 -0.1094 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3239 4.9023 470.0153 464.6252 2.6085 39.5551 30.6000 -8.9551

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.2624 58.1456 268.0279 1061.0175 0.2585 0.3566 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3188 5.0804 474.7919 464.5394 491.5697 0.0233 0.4539

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.1760 0.0000 284.1760 1060.5122 0.2680 0.3474 0.5911

NASA/TM—2013-218094 O–104
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0488 474.3465 464.5293 0.0000 0.0600 0.0626 0.2744

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8364 5.3037 1.0937 480.8395 13.9707 191.0842 1.4813

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86887.242 0.516 129.746 255151.453 0.120800E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.611 EfDer = 0.976 SH = 0.133569E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.424 2302.428 5.304 480.839 1.000 1.000 0.980

 W Kg/sec = 12.011 Wdry = 26.421 WH2O = 0.004 lbm/sec H2O = 0.062g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.516 2391.355 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54629.992 20732.803 2.643 545.479 206.424 424.468 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.36 -0.08 240.36 0.23 0.44 418.82

 MEAN 17.74 0.00 -0.02 240.36 -0.08 240.36 0.23 0.40

 HUB 15.05 0.00 -0.02 240.36 -0.08 240.36 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.21 46.36 12.85 403.26 469.53 5.12 476.19 464.54 2.37

 MEAN 56.01 43.40 12.61 356.41 429.95 5.12 476.19 464.54 2.37

 HUB 51.53 38.84 12.69 302.39 386.35 5.12 476.19 464.54 2.37

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.48 219.31 253.87 1073.27 0.31 2.26 1.98 8.75

 MEAN 17.51 337.53 220.08 255.91 1071.39 0.32 2.34 2.07 6.78

 HUB 14.85 360.45 251.56 258.15 1069.55 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.03 310.47 178.72 0.29 4346.22 0.92 0.89

 MEAN 351.75 287.79 131.67 0.27 3854.39 0.92 0.89 0.89 1.64

 HUB 298.37 262.36 46.81 0.25 3736.91 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.82 1.10 5.45 494.88 1.03 485.83 473.03 1.74

 MEAN 5.76 1.09 5.38 493.29 1.03 484.13 472.12 1.85

 HUB 5.75 1.08 5.32 492.91 1.03 482.47 471.93 1.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.82 35.14 31.50 3.64 0.93 0.50 1.40

 MEAN 40.70 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.26 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 362.9561 221.5288 287.5102 1070.2434 0.3391 -0.1180 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7733 5.3370 483.1040 472.3756 1.9292 37.6145 31.5000 -6.1145

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 283.4440 61.8314 276.6177 1074.8092 0.2637 0.3009 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7702 5.5013 487.2357 472.3054 451.3937 0.0179 0.4256

 

NASA/TM—2013-218094 O–105
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.1640 0.0000 288.1640 1074.5627 0.2682 0.3293 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4807 487.0186 472.2952 0.0000 0.0600 0.0491 0.2487

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8579 5.7578 1.0856 493.6940 12.8556 197.3700 1.5300

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79964.617 0.505 119.409 253982.953 0.144566E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.904 EfDer = 0.987 SH = 0.160491E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.424 2302.428 5.758 493.694 1.000 1.000 0.980

 W Kg/sec = 12.011 Wdry = 26.420 WH2O = 0.004 lbm/sec H2O = 0.079g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.816 2360.017 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51644.375 20732.584 2.664 513.330 192.672 395.845 2.055

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.46 -0.08 241.46 0.22 0.42 396.65

 MEAN 16.97 0.00 -0.02 241.46 -0.08 241.46 0.22 0.39

 HUB 14.32 0.00 -0.02 241.46 -0.08 241.46 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.04 46.36 11.68 386.98 456.20 5.56 489.01 472.31 1.81

 MEAN 54.70 43.80 10.90 340.98 417.88 5.56 489.01 472.31 1.81

 HUB 50.01 37.84 12.17 287.72 375.68 5.56 489.01 472.31 1.81

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.49 200.10 254.18 1086.05 0.30 2.16 1.89 8.34

 MEAN 16.57 325.57 201.13 256.01 1084.36 0.30 2.24 1.97 6.35

 HUB 13.89 347.22 232.36 258.01 1082.70 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 379.35 311.02 179.25 0.29 3779.49 0.92 0.90

 MEAN 333.01 287.98 131.88 0.27 3334.88 0.92 0.90 0.90 1.59

 HUB 279.08 262.21 46.73 0.24 3228.62 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.24 1.08 5.87 505.90 1.02 497.49 479.19 1.41

 MEAN 6.18 1.07 5.81 504.47 1.02 495.95 478.42 1.49

 HUB 6.17 1.07 5.75 504.12 1.02 494.43 478.25 1.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.21 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.15 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.01 10.27 6.50 3.77 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 345.9732 202.2588 280.6935 1083.5450 0.3193 -0.0939 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1905 5.7735 495.2090 478.6328 1.5313 35.7753 32.4000 -3.3753

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 282.3085 63.3135 275.1172 1087.0552 0.2597 0.2600 2.2705

 

NASA/TM—2013-218094 O–106
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1890 5.9091 498.4240 478.5815 432.2457 0.0139 0.4014

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.0247 0.0000 280.0247 1087.1613 0.2576 0.3123 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9037 498.5269 478.5703 0.0000 0.0600 0.0405 0.2461

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8716 6.1787 1.0731 504.8295 11.1364 213.6872 1.6565

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 69283.414 0.481 103.459 260252.953 0.173933E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.343 EfDer = 0.994 SH = 0.194232E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.424 2302.428 6.179 504.829 1.000 1.000 0.980

 W Kg/sec = 12.011 Wdry = 26.419 WH2O = 0.005 lbm/sec H2O = 0.101g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.021 2333.844 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49084.703 20732.309 2.807 509.668 181.567 384.739 2.119

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.14 -0.08 231.14 0.21 0.40 373.11

 MEAN 15.91 0.00 -0.02 231.14 -0.08 231.14 0.21 0.36

 HUB 13.07 0.00 -0.02 231.14 -0.08 231.14 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.88 47.36 10.52 368.09 434.71 5.99 500.54 478.59 1.49

 MEAN 54.14 44.80 9.34 319.73 394.59 5.99 500.54 478.59 1.49

 HUB 48.66 38.84 9.82 262.61 349.90 5.99 500.54 478.59 1.49

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 307.46 187.31 243.81 1097.53 0.28 2.05 1.78 7.43

 MEAN 15.50 306.97 184.15 245.60 1095.79 0.28 2.13 1.86 5.75

 HUB 12.59 323.35 208.07 247.52 1094.07 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 360.46 299.04 173.15 0.27 3361.87 0.92 0.91

 MEAN 311.39 276.60 127.24 0.25 2855.09 0.92 0.91 0.91 1.58

 HUB 252.96 251.55 44.90 0.23 2620.61 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.63 1.07 6.28 515.69 1.02 508.09 484.38 1.22

 MEAN 6.56 1.06 6.22 514.05 1.02 506.48 483.54 1.28

 HUB 6.53 1.06 6.15 513.29 1.02 504.89 483.16 1.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.53 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.86 27.39 23.50 3.89 0.93 0.44 1.64

 HUB 40.05 10.28 6.50 3.78 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 336.5258 187.5228 279.4365 1094.4412 0.3075 -0.1753 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5643 6.1530 505.2418 483.7037 1.3395 33.8646 33.0000 -0.8646

 

NASA/TM—2013-218094 O–107
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 285.9379 65.2942 278.3831 1097.1777 0.2606 0.1376 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5628 6.2640 507.7722 483.6619 410.5396 0.0243 0.3750

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.1609 0.0000 278.1609 1097.5529 0.2534 0.2977 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2755 508.1246 483.6597 0.0000 0.0600 0.0369 0.1699

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8801 6.5583 1.0614 514.3423 9.5136 234.4091 1.8171

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59199.301 0.456 88.400 273243.094 0.210822E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1438 Tt4 = 514.3423 T1 = 449.6699

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 402288.56 600.7241 83.3883 1.5121 0.8405 15.3070 1.1438 37.3740

NASA/TM—2013-218094 O–108
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.370 EfDer = 0.955 SH = 0.622437E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.397 2235.809 4.829 451.604 1.000 1.000 0.980

 W Kg/sec = 12.908 Wdry = 28.396 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.666 2396.135 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59869.883 22281.535 3.522 831.557 236.124 619.754 2.625

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.79 -0.06 172.79 0.17 0.42 431.37

 MEAN 17.06 0.00 -0.02 172.79 -0.06 172.79 0.17 0.36

 HUB 12.51 0.00 -0.02 172.79 -0.06 172.79 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.77 50.47 16.30 402.51 438.09 4.74 449.20 444.71 3.57

 MEAN 62.57 47.20 15.37 332.86 375.09 4.74 449.20 444.71 3.57

 HUB 54.71 38.62 16.09 244.08 299.10 4.74 449.20 444.71 3.57

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 361.46 276.58 232.72 1043.25 0.35 7.29 6.52 16.04

 MEAN 18.04 365.96 280.23 235.36 1040.62 0.35 7.43 6.80 12.53

 HUB 15.00 396.39 316.22 239.03 1037.38 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.51 264.61 125.94 0.25 5707.05 0.92 0.87

 MEAN 351.90 246.03 71.67 0.24 5055.27 0.92 0.87 0.87 1.75

 HUB 292.67 240.18 23.55 0.23 4744.06 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 469.51 1.04 459.01 457.90 2.82

 MEAN 5.39 1.12 4.95 467.47 1.04 456.70 456.49 3.10

 HUB 5.35 1.11 4.85 466.49 1.03 453.85 455.84 3.48

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.92 28.42 24.20 4.22 0.93 0.57 1.80

 MEAN 49.97 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.92 -5.63 -9.30 3.67 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 376.6928 279.6867 252.3347 1040.2899 0.3621 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3963 4.9346 456.4131 456.7514 3.1935 47.9431 35.4000 -12.5431

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 251.7043 61.5745 244.0566 1047.4597 0.2403 0.5096 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3859 5.1765 462.7291 456.6577 554.9116 0.0327 0.6003

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 250.5590 0.0000 250.5590 1047.5027 0.2392 0.4788 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1557 462.7750 456.6436 0.0000 0.0600 0.0842 0.4642

NASA/TM—2013-218094 O–109
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8175 5.3623 1.1105 467.8232 16.2204 168.5730 1.3068

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 100864.617 0.623 161.864 300278.688 0.826318E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.686 EfDer = 0.961 SH = 0.104791E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.397 2235.809 5.362 467.823 1.000 1.000 0.980

 W Kg/sec = 12.908 Wdry = 28.395 WH2O = 0.003 lbm/sec H2O = 0.051g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.931 2354.247 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56399.977 22281.164 2.728 590.487 216.416 468.502 2.165

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 229.23 -0.08 229.23 0.22 0.44 422.18

 MEAN 18.08 0.00 -0.02 229.23 -0.08 229.23 0.22 0.40

 HUB 15.21 0.00 -0.02 229.23 -0.08 229.23 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.25 46.36 13.89 400.95 461.93 5.19 463.60 456.72 3.31

 MEAN 56.99 42.30 14.69 352.73 420.74 5.19 463.60 456.72 3.31

 HUB 52.32 37.84 14.48 296.76 375.05 5.19 463.60 456.72 3.31

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 333.12 227.94 242.92 1059.58 0.31 2.33 2.04 9.02

 MEAN 18.01 333.23 225.84 245.03 1057.51 0.32 2.40 2.13 7.35

 HUB 15.22 353.63 252.71 247.37 1055.47 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.42 296.78 170.48 0.28 4656.09 0.92 0.88

 MEAN 351.39 275.33 125.56 0.26 4068.76 0.92 0.88 0.88 1.68

 HUB 297.02 251.31 44.31 0.24 3848.15 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.92 1.10 5.53 482.43 1.03 473.51 466.48 2.35

 MEAN 5.84 1.09 5.46 480.59 1.03 471.66 465.31 2.52

 HUB 5.82 1.08 5.39 479.90 1.03 469.84 464.88 2.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.18 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.67 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.61 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 356.7401 226.4719 275.6338 1056.4667 0.3377 -0.1099 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8543 5.4156 470.7403 465.5692 2.6222 39.4079 30.6000 -8.8079

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 267.6486 56.7434 261.5644 1061.4722 0.2521 0.3532 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8494 5.5996 475.2127 465.4938 491.5697 0.0223 0.4505

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 277.2452 0.0000 277.2452 1060.9952 0.2613 0.3442 0.5911

NASA/TM—2013-218094 O–110
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5666 474.7921 465.4843 0.0000 0.0600 0.0618 0.2707

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8369 5.8336 1.0879 480.9718 13.1495 191.4799 1.4843

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 81784.617 0.515 131.245 273388.469 0.113468E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.473 EfDer = 0.977 SH = 0.125257E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.397 2235.809 5.834 480.972 1.000 1.000 0.980

 W Kg/sec = 12.908 Wdry = 28.394 WH2O = 0.004 lbm/sec H2O = 0.064g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.907 2321.844 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53325.566 22280.986 2.704 545.479 201.714 424.468 2.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 234.62 -0.08 234.62 0.22 0.43 406.64

 MEAN 17.74 0.00 -0.02 234.62 -0.08 234.62 0.22 0.39 

 HUB 15.05 0.00 -0.02 234.62 -0.08 234.62 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.08 46.36 12.72 391.59 456.57 5.64 476.55 465.50 2.42 

 MEAN 55.87 43.40 12.47 346.10 418.19 5.64 476.55 465.50 2.42

 HUB 51.38 38.84 12.54 293.64 375.93 5.64 476.55 465.50 2.42

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 326.41 211.68 248.46 1072.96 0.30 2.26 1.98 8.75

 MEAN 17.51 328.57 212.85 250.31 1071.22 0.31 2.34 2.07 6.78

 HUB 14.85 351.07 244.05 252.37 1069.50 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.52 303.80 174.83 0.28 4195.06 0.92 0.89

 MEAN 341.57 281.47 128.72 0.26 3727.69 0.92 0.89 0.89 1.63

 HUB 289.74 256.47 45.69 0.24 3625.39 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 494.13 1.03 485.57 473.64 1.81

 MEAN 6.31 1.08 5.91 492.67 1.02 483.99 472.77 1.92

 HUB 6.29 1.08 5.85 492.34 1.02 482.44 472.60 2.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.43 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.38 27.21 23.50 3.71 0.94 0.48 1.62

 HUB 44.04 10.26 6.50 3.76 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.4726 214.2460 281.1433 1070.1177 0.3303 -0.1191 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3182 5.8642 483.0032 473.0177 1.9948 37.3093 31.5000 -5.8093

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 277.5619 60.5482 270.8773 1074.3740 0.2583 0.2940 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3154 6.0326 486.8539 472.9557 451.3937 0.0170 0.4198

 

NASA/TM—2013-218094 O–111
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 282.1314 0.0000 282.1314 1074.1401 0.2627 0.3240 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0113 486.6481 472.9465 0.0000 0.0600 0.0480 0.2420

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8592 6.3026 1.0804 493.0466 12.0757 198.4488 1.5384

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75117.750 0.503 120.547 272558.531 0.135340E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.669 EfDer = 0.988 SH = 0.149797E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.397 2235.809 6.303 493.046 1.000 1.000 0.980

 W Kg/sec = 12.908 Wdry = 28.393 WH2O = 0.004 lbm/sec H2O = 0.081g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.574 2293.237 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50586.242 22280.771 2.716 513.330 189.036 395.845 2.094

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 236.51 -0.08 236.51 0.22 0.41 385.42

 MEAN 16.97 0.00 -0.02 236.51 -0.08 236.51 0.22 0.38

 HUB 14.32 0.00 -0.02 236.51 -0.08 236.51 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.82 46.36 11.46 375.78 444.08 6.10 488.55 472.96 1.88

 MEAN 54.47 43.80 10.67 331.12 406.98 6.10 488.55 472.96 1.88

 HUB 49.76 37.84 11.92 279.40 366.12 6.10 488.55 472.96 1.88

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 315.13 192.43 249.55 1084.91 0.29 2.16 1.89 8.34

 MEAN 16.57 317.41 194.00 251.22 1083.35 0.29 2.24 1.97 6.35

 HUB 13.89 338.75 225.21 253.05 1081.82 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 368.37 305.34 175.94 0.28 3634.64 0.92 0.90

 MEAN 323.37 282.58 129.37 0.26 3216.71 0.92 0.90 0.90 1.58

 HUB 271.01 257.16 45.80 0.24 3129.33 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.08 6.41 504.45 1.02 496.46 479.56 1.50

 MEAN 6.74 1.07 6.35 503.14 1.02 495.04 478.84 1.57

 HUB 6.72 1.07 6.29 502.86 1.02 493.64 478.70 1.64

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.64 35.18 31.50 3.68 0.93 0.47 1.40

 MEAN 37.68 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.67 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 337.4939 195.0909 275.3936 1082.5662 0.3118 -0.0953 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7468 6.3127 494.3263 479.0433 1.6163 35.3140 32.4000 -2.9140

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 277.3079 62.1921 270.2440 1085.8164 0.2554 0.2500 2.2705

 

NASA/TM—2013-218094 O–112
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7455 6.4502 497.3003 478.9981 432.2457 0.0132 0.3935

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 275.0416 0.0000 275.0416 1085.9203 0.2533 0.3044 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4449 497.4007 478.9879 0.0000 0.0600 0.0395 0.2367

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 6.7350 1.0686 503.4807 10.4349 215.6312 1.6716

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64921.660 0.478 104.184 279682.688 0.161884E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.023 EfDer = 0.995 SH = 0.179978E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.397 2235.809 6.735 503.480 1.000 1.000 0.980

 W Kg/sec = 12.908 Wdry = 28.392 WH2O = 0.005 lbm/sec H2O = 0.102g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.065 2269.350 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48228.703 22280.506 2.851 509.668 178.769 384.739 2.152

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 227.11 -0.08 227.11 0.21 0.39 362.80

 MEAN 15.91 0.00 -0.02 227.11 -0.08 227.11 0.21 0.35

 HUB 13.07 0.00 -0.02 227.11 -0.08 227.11 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.58 47.36 10.22 357.44 423.56 6.54 499.34 479.01 1.58

 MEAN 53.82 44.80 9.02 310.48 384.74 6.54 499.34 479.01 1.58

 HUB 48.32 38.84 9.48 255.01 341.54 6.54 499.34 479.01 1.58

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.78 179.56 240.06 1095.65 0.27 2.05 1.78 7.43

 MEAN 15.50 299.68 177.17 241.70 1094.04 0.27 2.13 1.86 5.75

 HUB 12.59 315.99 201.46 243.45 1092.46 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 350.03 294.43 170.47 0.27 3222.73 0.92 0.91

 MEAN 302.38 272.20 125.20 0.25 2747.01 0.92 0.91 0.91 1.56

 HUB 245.64 247.43 44.19 0.23 2537.34 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.19 1.07 6.83 513.59 1.02 506.36 484.56 1.31

 MEAN 7.12 1.06 6.77 512.10 1.02 504.88 483.77 1.37

 HUB 7.09 1.05 6.70 511.44 1.02 503.41 483.43 1.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.80 35.38 31.50 3.88 0.93 0.45 1.40

 MEAN 36.24 27.38 23.50 3.88 0.93 0.43 1.64

 HUB 39.61 10.29 6.50 3.79 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.8411 180.4221 274.9260 1092.7406 0.3009 -0.1778 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1287 6.7002 503.6830 483.9289 1.4316 33.2752 33.0000 -0.2752

 

NASA/TM—2013-218094 O–113
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 281.6100 64.3059 274.1696 1095.2505 0.2571 0.1237 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1274 6.8112 506.0000 483.8923 410.5396 0.0236 0.3654

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 273.9629 0.0000 273.9629 1095.6149 0.2501 0.2874 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8233 506.3412 483.8897 0.0000 0.0600 0.0366 0.1562

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 7.1225 1.0575 512.3726 8.8927 237.3464 1.8399

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55336.320 0.452 88.802 294018.906 0.194678E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1346 Tt4 = 512.3726 T1 = 451.6038

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 378024.97 606.6426 80.6660 1.4750 0.8415 15.3697 1.1346 37.3740

NASA/TM—2013-218094 O–114
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.856 EfDer = 0.967 SH = 0.105864E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.551 2121.947 5.592 461.413 1.000 1.000 0.980

 W Kg/sec = 14.796 Wdry = 32.547 WH2O = 0.003 lbm/sec H2O = 0.055g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.699 2249.811 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60544.008 25539.906 3.520 831.557 236.232 619.754 2.623

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.74 -0.06 174.74 0.17 0.40 405.02

 MEAN 17.06 0.00 -0.02 174.74 -0.06 174.74 0.17 0.35

 HUB 12.51 0.00 -0.02 174.74 -0.06 174.74 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.42 50.47 14.95 382.02 420.14 5.49 458.96 452.73 4.39

 MEAN 61.06 47.20 13.86 315.91 361.07 5.49 458.96 452.73 4.39

 HUB 52.98 38.62 14.36 231.65 290.22 5.49 458.96 452.73 4.39

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 347.45 254.44 236.60 1052.64 0.33 7.29 6.52 16.04

 MEAN 18.04 354.30 261.62 238.91 1050.43 0.34 7.43 6.80 12.53

 HUB 15.00 387.08 301.93 242.22 1047.58 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 382.02 268.80 127.57 0.26 5250.41 0.92 0.89

 MEAN 333.98 249.63 72.36 0.24 4719.67 0.92 0.89 0.89 1.65

 HUB 277.76 243.43 24.16 0.23 4529.66 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 477.05 1.03 467.34 463.84 3.56

 MEAN 6.16 1.10 5.70 475.47 1.03 465.37 462.80 3.84

 HUB 6.13 1.10 5.59 474.90 1.03 462.85 462.46 4.23

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.08 28.33 24.20 4.13 0.93 0.53 1.80

 MEAN 47.60 16.85 12.70 4.15 0.94 0.48 2.22

 HUB 51.26 -5.70 -9.30 3.60 0.94 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.967 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.7941 261.1154 256.1720 1050.0518 0.3484 -0.0424 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1675 5.6771 465.0465 463.0402 3.9452 45.5475 35.4000 -10.1475

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.7500 62.8089 248.9490 1056.1917 0.2431 0.4681 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1598 5.9148 470.5041 462.9311 554.9116 0.0259 0.5572

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.3171 0.0000 255.3171 1056.2488 0.2417 0.4491 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8973 470.5628 462.9217 0.0000 0.0600 0.0693 0.4320

NASA/TM—2013-218094 O–115
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8357 6.1388 1.0977 475.8033 14.3915 175.9555 1.3640

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89514.609 0.613 164.660 338607.281 0.129406E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.803 EfDer = 0.975 SH = 0.153443E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.551 2121.947 6.139 475.803 1.000 1.000 0.980

 W Kg/sec = 14.796 Wdry = 32.546 WH2O = 0.005 lbm/sec H2O = 0.084g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.654 2215.537 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57465.125 25539.428 2.702 590.487 218.541 468.502 2.144

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.56 -0.08 233.56 0.22 0.42 397.31

 MEAN 18.08 0.00 -0.02 233.56 -0.08 233.56 0.22 0.39

 HUB 15.21 0.00 -0.02 233.56 -0.08 233.56 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.46 46.36 12.10 380.53 446.56 5.94 471.42 463.00 3.90

 MEAN 55.10 42.30 12.80 334.76 408.26 5.94 471.42 463.00 3.90

 HUB 50.34 37.84 12.50 281.65 365.96 5.94 471.42 463.00 3.90

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.65 203.76 248.87 1066.65 0.30 2.33 2.04 9.02

 MEAN 18.01 324.00 205.30 250.66 1064.98 0.30 2.40 2.13 7.35

 HUB 15.22 346.28 236.82 252.64 1063.33 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.13 303.88 174.36 0.28 4162.51 0.92 0.89

 MEAN 333.50 281.54 128.20 0.26 3698.93 0.92 0.89 0.89 1.59

 HUB 281.89 256.63 45.08 0.24 3606.28 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.09 6.27 488.19 1.03 479.88 471.07 2.93

 MEAN 6.61 1.08 6.20 486.81 1.02 478.38 470.22 3.10

 HUB 6.60 1.07 6.14 486.54 1.02 476.90 470.07 3.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.31 35.02 31.50 3.52 0.93 0.48 1.40

 MEAN 39.32 27.09 23.50 3.59 0.94 0.46 1.63

 HUB 43.15 10.12 6.50 3.62 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 349.1836 205.8782 282.0343 1063.8610 0.3282 -0.1235 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6227 6.1525 477.3821 470.4727 3.2218 36.1285 30.6000 -5.5285

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.9577 58.2930 268.7074 1068.0015 0.2575 0.2882 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6199 6.3256 481.1057 470.3932 491.5697 0.0165 0.3964

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.6159 0.0000 284.6159 1067.5126 0.2666 0.2980 0.5911

NASA/TM—2013-218094 O–116
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2927 480.6712 470.3924 0.0000 0.0600 0.0469 0.2104

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8569 6.6071 1.0763 487.1822 11.3797 204.4007 1.5845

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 70796.102 0.495 130.228 309542.188 0.162714E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.367 EfDer = 0.990 SH = 0.174966E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.551 2121.947 6.607 487.182 1.000 1.000 0.980

 W Kg/sec = 14.796 Wdry = 32.545 WH2O = 0.006 lbm/sec H2O = 0.100g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.187 2189.510 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54720.441 25539.213 2.655 545.479 205.471 424.468 2.066

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.76 -0.08 240.76 0.23 0.41 383.47

 MEAN 17.74 0.00 -0.02 240.76 -0.08 240.76 0.23 0.38

 HUB 15.05 0.00 -0.02 240.76 -0.08 240.76 0.23 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.07 46.36 10.71 371.65 442.89 6.38 482.52 470.40 2.96

 MEAN 53.77 43.40 10.37 328.47 407.32 6.38 482.52 470.40 2.96

 HUB 49.18 38.84 10.34 278.69 368.35 6.38 482.52 470.40 2.96

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 317.06 186.52 256.39 1077.93 0.29 2.26 1.98 8.75

 MEAN 17.51 321.29 191.58 257.92 1076.58 0.30 2.34 2.07 6.78

 HUB 14.85 345.50 227.97 259.61 1075.25 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.83 313.45 180.32 0.29 3696.54 0.92 0.91

 MEAN 324.18 290.00 132.59 0.27 3355.44 0.92 0.91 0.91 1.53

 HUB 274.98 263.83 47.01 0.25 3386.63 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.11 1.08 6.70 498.18 1.02 490.11 477.12 2.33

 MEAN 7.06 1.07 6.64 497.17 1.02 488.87 476.53 2.43

 HUB 7.07 1.07 6.59 497.26 1.02 487.67 476.62 2.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.03 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.61 27.21 23.50 3.71 0.94 0.43 1.62

 HUB 41.29 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 348.0866 192.8407 289.7875 1075.3876 0.3237 -0.1338 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0754 6.5863 487.8011 476.7783 2.5343 33.6420 31.5000 -2.1420

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 287.2176 62.6546 280.3004 1078.8075 0.2662 0.2171 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0740 6.7383 490.9089 476.7151 451.3937 0.0132 0.3609

 

NASA/TM—2013-218094 O–117
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.8179 0.0000 291.8179 1078.5664 0.2706 0.2679 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7173 490.6947 476.7115 0.0000 0.0600 0.0382 0.1691

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8744 7.0632 1.0690 497.5384 10.3569 214.0340 1.6592

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64442.547 0.479 118.540 309720.750 0.185165E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.327 EfDer = 0.998 SH = 0.199396E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.551 2121.947 7.063 497.538 1.000 1.000 0.980

 W Kg/sec = 14.796 Wdry = 32.544 WH2O = 0.006 lbm/sec H2O = 0.120g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.349 2166.603 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52288.617 25538.971 2.643 513.330 194.241 395.845 2.038

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.47 -0.08 244.47 0.23 0.40 364.14

 MEAN 16.97 0.00 -0.02 244.47 -0.08 244.47 0.23 0.37

 HUB 14.32 0.00 -0.02 244.47 -0.08 244.47 0.23 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.58 46.36 9.22 356.65 432.46 6.82 492.74 476.72 2.37

 MEAN 52.13 43.80 8.33 314.25 398.21 6.82 492.74 476.72 2.37

 HUB 47.34 37.84 9.50 265.17 360.73 6.82 492.74 476.72 2.37

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 308.30 166.63 259.39 1087.94 0.28 2.16 1.89 8.34

 MEAN 16.57 312.63 172.52 260.72 1086.77 0.29 2.24 1.97 6.35

 HUB 13.89 335.68 209.62 262.19 1085.63 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.61 317.44 182.98 0.29 3147.64 0.92 0.91

 MEAN 306.91 293.32 134.39 0.27 2860.73 0.92 0.91 0.91 1.48

 HUB 257.21 266.47 47.59 0.25 2912.80 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.51 1.06 7.11 506.91 1.02 499.27 482.14 1.96

 MEAN 7.47 1.06 7.06 506.05 1.02 498.20 481.67 2.03

 HUB 7.48 1.06 7.01 506.21 1.02 497.15 481.78 2.10

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.72 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.49 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.64 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 334.4377 173.4889 285.9199 1085.8965 0.3080 -0.1080 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4835 7.0132 497.4004 481.8763 2.0903 31.2483 32.4000 1.1517

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 288.9704 64.8076 281.6094 1088.3793 0.2655 0.1649 2.2705

 

NASA/TM—2013-218094 O–118
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4825 7.1293 499.6779 481.8319 432.2457 0.0122 0.3302

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.5527 0.0000 286.5527 1088.4962 0.2633 0.2377 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1250 499.7896 481.8218 0.0000 0.0600 0.0371 0.1548

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.4719 1.0579 506.3875 8.8499 235.3848 1.8247

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55074.441 0.451 101.308 318872.969 0.210913E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.468 EfDer = 1.000 SH = 0.227858E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.551 2121.947 7.472 506.387 1.000 1.000 0.980

 W Kg/sec = 14.796 Wdry = 32.543 WH2O = 0.007 lbm/sec H2O = 0.142g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.275 2147.589 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 50204.121 25538.684 2.751 509.668 185.247 384.739 2.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.41 -0.08 236.41 0.22 0.38 343.33

 MEAN 15.91 0.00 -0.02 236.41 -0.08 236.41 0.22 0.35

 HUB 13.07 0.00 -0.02 236.41 -0.08 236.41 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.13 47.36 7.77 339.24 413.56 7.23 501.90 481.83 2.00

 MEAN 51.27 44.80 6.47 294.67 377.84 7.23 501.90 481.83 2.00

 HUB 45.68 38.84 6.84 242.02 338.38 7.23 501.90 481.83 2.00

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.45 153.52 251.27 1096.98 0.27 2.05 1.78 7.43

 MEAN 15.50 296.81 155.89 252.58 1095.77 0.27 2.13 1.86 5.75

 HUB 12.59 315.30 186.83 253.99 1094.58 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 332.20 308.32 178.68 0.28 2755.66 0.92 0.91

 MEAN 286.98 284.57 131.09 0.26 2417.17 0.92 0.91 0.91 1.46

 HUB 233.14 258.18 46.31 0.24 2353.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.88 1.05 7.50 514.59 1.02 507.62 486.37 1.72

 MEAN 7.83 1.05 7.45 513.58 1.01 506.50 485.83 1.78

 HUB 7.82 1.05 7.39 513.39 1.01 505.40 485.75 1.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.42 35.42 31.50 3.92 0.93 0.39 1.40

 MEAN 31.68 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.34 10.33 6.50 3.83 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.3842 158.7456 287.4648 1094.3440 0.3001 -0.1967 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8357 7.3673 505.1881 486.0020 1.8584 28.9086 33.0000 4.0914

 

NASA/TM—2013-218094 O–119
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.5398 67.4868 287.7314 1096.1260 0.2696 0.0176 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8328 7.4519 506.8344 485.9665 410.5396 0.0272 0.2994

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.4886 0.0000 287.4886 1096.5300 0.2622 0.2115 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4663 507.2115 485.9595 0.0000 0.0600 0.0423 0.0536

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 7.8268 1.0475 513.8516 7.4647 262.0222 2.0312

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46461.359 0.421 85.465 336145.938 0.241208E-03

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1136 Tt4 = 513.8516 T1 = 461.4126

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 326289.06 600.2006 80.6992 1.3995 0.8551 13.8564 1.1136 37.3740

NASA/TM—2013-218094 O–120
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.032 EfDer = 0.995 SH = 0.174965E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.058 1951.430 6.513 472.323 1.000 1.000 0.980

 W Kg/sec = 18.663 Wdry = 41.051 WH2O = 0.007 lbm/sec H2O = 0.103g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.429 2044.987 1.381 0.249 53.354 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 67321.938 32213.691 3.212 831.557 258.875 619.754 2.394

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 194.30 -0.07 194.30 0.18 0.38 368.15

 MEAN 17.06 0.00 -0.02 194.30 -0.07 194.30 0.18 0.33

 HUB 12.51 0.00 -0.02 194.30 -0.07 194.30 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.06 50.47 10.59 351.32 401.53 6.36 469.29 461.35 5.24

 MEAN 56.23 47.20 9.03 290.52 349.57 6.36 469.29 461.35 5.24

 HUB 47.64 38.62 9.02 213.04 288.39 6.36 469.29 461.35 5.24

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 337.80 208.44 265.83 1061.11 0.32 7.29 6.52 16.04

 MEAN 18.04 350.56 226.41 267.64 1059.66 0.33 7.43 6.80 12.53

 HUB 15.00 391.41 282.69 270.72 1057.41 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.32 301.79 142.88 0.28 4301.40 0.92 0.91 

 MEAN 307.14 279.55 80.74 0.26 4084.64 0.92 0.91 0.91 1.41

 HUB 255.44 272.09 27.25 0.26 4241.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.07 1.08 6.59 484.10 1.02 474.93 469.46 4.60

 MEAN 7.04 1.08 6.53 483.50 1.02 473.63 469.10 4.82

 HUB 7.06 1.08 6.43 483.93 1.02 471.62 469.45 5.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.10 28.26 24.20 4.06 0.93 0.39 1.80

 MEAN 40.23 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.24 -5.75 -9.30 3.55 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.4763 225.9682 287.2478 1059.0768 0.3451 -0.0600 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0475 6.4971 473.1093 469.3484 4.9608 38.1909 35.4000 -2.7909

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 290.1436 70.9780 281.3280 1063.5076 0.2728 0.3321 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0450 6.6945 477.0786 469.2401 554.9116 0.0145 0.4330

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 288.0212 0.0000 288.0212 1063.6101 0.2708 0.3449 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6869 477.1772 469.2395 0.0000 0.0600 0.0393 0.3180

NASA/TM—2013-218094 O–121
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8762 7.0318 1.0797 483.8439 11.5219 201.5529 1.5624

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71690.344 0.581 166.337 420826.219 0.199548E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.187 EfDer = 1.000 SH = 0.222413E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.058 1951.430 7.032 483.844 1.000 1.000 0.980

 W Kg/sec = 18.663 Wdry = 41.049 WH2O = 0.009 lbm/sec H2O = 0.136g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.898 2020.498 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64742.219 32213.090 2.433 590.487 242.690 468.502 1.930

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 263.14 -0.09 263.14 0.25 0.41 362.33

 MEAN 18.08 0.00 -0.02 263.14 -0.09 263.14 0.25 0.38

 HUB 15.21 0.00 -0.02 263.14 -0.09 263.14 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.07 46.36 6.71 349.95 437.92 6.74 478.28 469.29 4.76

 MEAN 49.49 42.30 7.19 307.86 405.07 6.74 478.28 469.29 4.76

 HUB 44.56 37.84 6.72 259.02 369.30 6.74 478.28 469.29 4.76

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 320.25 148.90 283.53 1071.10 0.30 2.33 2.04 9.02

 MEAN 18.01 326.93 160.87 284.60 1070.28 0.31 2.40 2.13 7.35

 HUB 15.22 353.48 207.94 285.85 1069.49 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 347.74 346.31 198.84 0.32 3042.41 0.92 0.91

 MEAN 306.70 319.79 145.83 0.30 2898.96 0.92 0.91 0.91 1.37

 HUB 259.24 290.41 51.30 0.27 3166.87 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.44 1.06 7.00 492.17 1.02 483.93 474.64 3.96

 MEAN 7.42 1.06 6.96 491.78 1.02 483.19 474.40 4.06

 HUB 7.46 1.06 6.92 492.51 1.02 482.47 474.90 4.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.71 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.48 27.13 23.50 3.63 0.93 0.33 1.63

 HUB 36.03 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.1811 161.3248 320.9134 1068.7213 0.3361 -0.1649 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4357 6.8835 481.7865 474.6864 4.2781 26.6889 30.6000 3.9111

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 315.1645 66.8171 308.0002 1071.3644 0.2942 0.0923 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4332 7.0055 484.1714 474.6145 491.5697 0.0151 0.2523

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 326.4169 0.0000 326.4169 1070.7180 0.3049 0.1442 0.5911

NASA/TM—2013-218094 O–122
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9631 483.5913 474.6228 0.0000 0.0600 0.0418 0.0038

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8707 7.4204 1.0553 492.1526 8.3092 252.5300 1.9576

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 51710.891 0.428 119.980 387886.906 0.230998E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.274 EfDer = 0.994 SH = 0.242031E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.058 1951.430 7.420 492.153 1.000 1.000 0.980

 W Kg/sec = 18.663 Wdry = 41.048 WH2O = 0.010 lbm/sec H2O = 0.153g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.228 2003.370 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62549.512 32212.842 2.352 545.479 231.950 424.468 1.830

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 275.21 -0.09 275.21 0.26 0.41 350.87

 MEAN 17.74 0.00 -0.02 275.21 -0.09 275.21 0.26 0.38

 HUB 15.05 0.00 -0.02 275.21 -0.09 275.21 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.17 46.36 4.81 341.78 438.88 7.09 486.07 474.59 3.92

 MEAN 47.67 43.40 4.27 302.08 408.71 7.09 486.07 474.59 3.92

 HUB 42.97 38.84 4.13 256.29 376.13 7.09 486.07 474.59 3.92

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 323.25 127.76 296.93 1078.54 0.30 2.26 1.98 8.75

 MEAN 17.51 330.75 144.37 297.57 1078.10 0.31 2.34 2.07 6.78

 HUB 14.85 358.18 198.11 298.41 1077.67 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.35 363.45 209.60 0.34 2532.77 0.92 0.91

 MEAN 298.13 334.95 153.75 0.31 2529.19 0.92 0.91 0.91 1.31

 HUB 252.89 303.39 54.78 0.28 2943.35 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.77 1.05 7.31 499.08 1.01 490.69 478.84 3.40

 MEAN 7.77 1.05 7.29 499.07 1.01 490.28 478.85 3.45

 HUB 7.83 1.06 7.26 500.21 1.02 489.90 479.56 3.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.28 35.22 31.50 3.72 0.93 0.28 1.40

 MEAN 25.88 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.58 10.40 6.50 3.90 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.3618 145.3223 335.2173 1076.3790 0.3394 -0.1776 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7848 7.1957 488.7296 479.1245 3.6417 23.4375 31.5000 8.0625

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 334.9129 73.0590 326.8471 1078.2657 0.3106 -0.0035 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7792 7.2823 490.4425 479.0682 451.3937 0.0211 0.2104

 

NASA/TM—2013-218094 O–123
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 340.7590 0.0000 340.7590 1077.9136 0.3161 0.0885 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2478 490.1251 479.0587 0.0000 0.0600 0.0579 -0.0717

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8386 7.7606 1.0458 499.4543 7.3021 273.4493 2.1198

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45448.680 0.399 105.450 390602.438 0.250717E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.684 EfDer = 0.973 SH = 0.262573E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.058 1951.430 7.761 499.454 1.000 1.000 0.980

 W Kg/sec = 18.663 Wdry = 41.047 WH2O = 0.011 lbm/sec H2O = 0.171g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.315 1988.672 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60798.211 32212.584 2.298 513.330 223.426 395.845 1.772 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 284.25 -0.10 284.25 0.26 0.40 334.24

 MEAN 16.97 0.00 -0.02 284.25 -0.10 284.25 0.26 0.38

 HUB 14.32 0.00 -0.02 284.25 -0.10 284.25 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.09 46.36 2.73 327.99 434.10 7.40 492.96 479.02 3.35

 MEAN 45.48 43.80 1.68 289.00 405.44 7.40 492.96 479.02 3.35

 HUB 40.64 37.84 2.80 243.86 374.59 7.40 492.96 479.02 3.35

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.33 104.43 306.00 1084.85 0.30 2.16 1.89 8.34

 MEAN 16.57 330.14 123.14 306.32 1084.66 0.30 2.24 1.97 6.35

 HUB 13.89 355.66 179.78 306.87 1084.49 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.52 375.18 217.09 0.35 1973.53 0.92 0.89

 MEAN 282.24 345.17 159.10 0.32 2042.64 0.92 0.89 0.89 1.26

 HUB 236.54 312.08 56.76 0.29 2498.57 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.03 1.04 7.56 504.85 1.01 496.46 482.20 3.03

 MEAN 8.04 1.04 7.55 505.04 1.01 496.29 482.32 3.04

 HUB 8.11 1.04 7.53 506.29 1.01 496.13 483.06 3.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.84 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 21.90 27.45 23.50 3.95 0.91 0.24 1.62

 HUB 30.36 10.48 6.50 3.98 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.7962 123.8371 336.7478 1083.3075 0.3312 -0.1450 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0575 7.4756 495.0540 482.5609 3.1776 20.1907 32.4000 12.2093

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 343.2218 76.9746 334.4789 1084.2699 0.3165 -0.0655 2.2705

 

NASA/TM—2013-218094 O–124
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0477 7.5147 495.9322 482.5229 432.2457 0.0291 0.1740

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 340.9997 0.0000 340.9997 1084.4017 0.3145 0.0348 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4959 496.0543 482.4861 0.0000 0.0600 0.0821 -0.1019

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7673 8.0205 1.0335 505.3956 5.9417 314.6474 2.4391

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 36985.910 0.358 85.815 404643.688 0.271504E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.718 EfDer = 0.938 SH = 0.284628E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.058 1951.430 8.020 505.396 1.000 1.000 0.980

 W Kg/sec = 18.663 Wdry = 41.046 WH2O = 0.012 lbm/sec H2O = 0.189g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.280 1976.949 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59443.031 32212.305 2.344 509.668 217.473 384.739 1.769

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 279.91 -0.10 279.91 0.26 0.39 316.05

 MEAN 15.91 0.00 -0.02 279.91 -0.10 279.91 0.26 0.36

 HUB 13.07 0.00 -0.02 279.91 -0.10 279.91 0.26 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.11 47.36 0.75 311.98 419.22 7.66 499.10 482.44 2.95

 MEAN 44.08 44.80 -0.72 270.99 389.67 7.66 499.10 482.44 2.95

 HUB 38.50 38.84 -0.34 222.57 357.68 7.66 499.10 482.44 2.95

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.90 89.15 302.02 1090.67 0.29 2.05 1.78 7.43

 MEAN 15.50 320.20 105.52 302.32 1090.48 0.29 2.13 1.86 5.75

 HUB 12.59 341.56 157.89 302.88 1090.29 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 305.51 371.52 216.36 0.34 1601.07 0.92 0.86

 MEAN 263.92 341.30 158.39 0.31 1636.87 0.92 0.86 0.86 1.23

 HUB 214.40 308.11 56.52 0.28 1989.03 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.24 1.03 7.78 509.78 1.01 501.81 484.94 2.74

 MEAN 8.24 1.03 7.77 509.87 1.01 501.64 485.00 2.76

 HUB 8.29 1.03 7.75 510.84 1.01 501.47 485.56 2.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.45 35.62 31.50 4.12 0.93 0.19 1.40

 MEAN 19.24 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.53 10.57 6.50 4.07 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.938 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.7520 107.4571 345.4237 1088.3124 0.3324 -0.2499 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2487 7.6489 499.6504 485.2124 2.9415 17.2803 33.0000 15.7197

 

NASA/TM—2013-218094 O–125
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 358.9044 81.9561 349.4217 1088.4954 0.3297 -0.2778 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2217 7.6330 499.8150 485.1683 410.5396 0.0751 0.1423

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 349.1546 0.0000 349.1546 1089.0991 0.3206 0.0017 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6499 500.3694 485.1376 0.0000 0.0600 0.1054 -0.2432

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6740 8.2069 1.0232 510.1620 4.7667 366.9999 2.8450

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 29674.760 0.318 68.852 428692.844 0.294440E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0801 Tt4 = 510.1620 T1 = 472.3225

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 235510.58 546.4335 88.4287 1.2601 0.8219 9.0317 1.0801 37.3740

NASA/TM—2013-218094 O–126
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.403 EfDer = 0.998 SH = 0.326391E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.861 1792.631 7.939 487.555 1.000 1.000 0.980

 W Kg/sec = 23.119 Wdry = 50.844 WH2O = 0.017 lbm/sec H2O = 0.226g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 91.301 1849.000 1.381 0.249 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 70709.500 39902.941 3.111 831.557 267.316 619.754 2.318

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 204.08 -0.07 204.08 0.19 0.36 332.87

 MEAN 17.06 0.00 -0.02 204.08 -0.07 204.08 0.19 0.31

 HUB 12.51 0.00 -0.02 204.08 -0.07 204.08 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.70 50.47 7.23 322.73 381.90 7.74 484.21 472.90 6.24

 MEAN 52.60 47.20 5.40 266.88 336.02 7.74 484.21 472.90 6.24

 HUB 43.81 38.62 5.19 195.70 282.80 7.74 484.21 472.90 6.24

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.79 170.82 282.10 1075.19 0.31 7.29 6.52 16.04

 MEAN 18.04 344.69 196.39 283.27 1074.35 0.32 7.43 6.80 12.53

 HUB 15.00 388.53 263.13 285.86 1072.63 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.73 320.40 151.91 0.30 3525.49 0.92 0.91

 MEAN 282.15 295.97 85.76 0.28 3543.33 0.92 0.91 0.91 1.27

 HUB 234.65 287.27 28.48 0.27 3947.83 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.90 496.41 1.02 487.68 478.71 5.81

 MEAN 8.43 1.06 7.86 496.46 1.02 486.92 478.78 5.96

 HUB 8.49 1.07 7.76 497.48 1.02 485.35 479.51 6.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.20 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 34.73 16.84 12.70 4.14 0.92 0.25 2.22

 HUB 42.63 -5.69 -9.30 3.61 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.8823 196.0108 304.2016 1073.6320 0.3371 -0.0744 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4422 7.8119 486.2649 479.0180 6.1324 32.7955 35.4000 2.6045

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 309.3062 75.6657 299.9083 1076.7542 0.2873 0.2234 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4398 7.9759 489.0991 478.8997 554.9116 0.0141 0.3453

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 306.9932 0.0000 306.9932 1076.8745 0.2851 0.2483 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9684 489.2137 478.8948 0.0000 0.0600 0.0389 0.2110

NASA/TM—2013-218094 O–127
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8717 8.4246 1.0611 496.7826 9.2281 224.0152 1.7366

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57456.695 0.552 165.142 509592.969 0.354378E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 2.968 EfDer = 0.985 SH = 0.378929E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.861 1792.631 8.425 496.782 1.000 1.000 0.980

 W Kg/sec = 23.119 Wdry = 50.842 WH2O = 0.019 lbm/sec H2O = 0.269g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.851 1831.749 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68958.469 39902.121 2.322 590.487 254.296 468.502 1.842 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 280.28 -0.10 280.28 0.26 0.40 328.48

 MEAN 18.08 0.00 -0.02 280.28 -0.10 280.28 0.26 0.37

 HUB 15.21 0.00 -0.02 280.28 -0.10 280.28 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.93 46.36 2.57 321.48 426.57 8.04 490.47 478.93 5.81

 MEAN 45.27 42.30 2.97 282.81 398.24 8.04 490.47 478.93 5.81

 HUB 40.34 37.84 2.50 237.94 367.72 8.04 490.47 478.93 5.81

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.93 104.42 305.58 1081.87 0.30 2.33 2.04 9.02

 MEAN 18.01 330.14 124.36 305.82 1081.75 0.31 2.40 2.13 7.35

 HUB 15.22 356.55 182.55 306.28 1081.64 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.44 373.65 215.02 0.35 2134.30 0.92 0.90

 MEAN 281.74 343.94 157.38 0.32 2241.44 0.92 0.90 0.90 1.24

 HUB 238.14 311.28 55.59 0.29 2780.49 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.21 502.14 1.01 493.77 482.23 5.25

 MEAN 8.74 1.04 8.20 502.41 1.01 493.66 482.40 5.27

 HUB 8.82 1.05 8.19 503.77 1.01 493.56 483.25 5.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.87 35.13 31.50 3.63 0.93 0.21 1.40

 MEAN 22.13 27.23 23.50 3.73 0.91 0.23 1.63

 HUB 30.80 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 367.1811 124.7079 345.3547 1079.8682 0.3400 -0.1954 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7562 8.0914 491.9495 482.7006 5.5848 19.8547 30.6000 10.7453

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 341.1415 72.3244 333.3867 1081.4954 0.3154 -0.0497 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7469 8.1715 493.4304 482.6238 491.5697 0.0265 0.1577

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 354.0062 0.0000 354.0062 1080.7053 0.3276 0.0192 0.5911

NASA/TM—2013-218094 O–128
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1042 492.7123 482.6304 0.0000 0.0600 0.0729 -0.1693

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7934 8.7208 1.0352 502.7755 5.9932 305.7462 2.3701

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37322.313 0.366 107.272 472609.000 0.387922E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.411 EfDer = 0.943 SH = 0.399389E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.861 1792.631 8.721 502.775 1.000 1.000 0.980

 W Kg/sec = 23.119 Wdry = 50.841 WH2O = 0.020 lbm/sec H2O = 0.289g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.406 1820.799 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67684.922 39901.801 2.207 545.479 247.142 424.468 1.718

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 297.80 -0.10 297.80 0.27 0.40 318.89

 MEAN 17.74 0.00 -0.02 297.80 -0.10 297.80 0.27 0.38

 HUB 15.05 0.00 -0.02 297.80 -0.10 297.80 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.52 46.36 0.16 313.97 432.81 8.28 495.65 482.54 5.12

 MEAN 42.99 43.40 -0.41 277.49 407.12 8.28 495.65 482.54 5.12

 HUB 38.34 38.84 -0.50 235.44 379.69 8.28 495.65 482.54 5.12

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.07 79.03 325.62 1086.15 0.31 2.26 1.98 8.75

 MEAN 17.51 341.76 104.80 325.30 1086.49 0.31 2.34 2.07 6.78

 HUB 14.85 367.87 171.71 325.33 1086.83 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 309.90 399.16 230.87 0.37 1567.72 0.92 0.86

 MEAN 273.87 366.61 169.07 0.34 1836.49 0.92 0.86 0.86 1.18

 HUB 232.31 330.93 60.60 0.30 2551.44 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.94 1.02 8.37 506.71 1.01 497.70 484.90 4.83

 MEAN 8.97 1.03 8.39 507.39 1.01 498.01 485.29 4.78

 HUB 9.07 1.04 8.39 509.19 1.01 498.32 486.37 4.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.64 35.34 31.50 3.84 0.93 0.14 1.40

 MEAN 17.86 27.46 23.50 3.96 0.90 0.18 1.62

 HUB 27.82 10.55 6.50 4.05 0.90 0.24 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.943 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 382.1121 105.4868 367.2631 1084.3368 0.3524 -0.2099 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9887 8.2585 496.0391 485.6052 5.0973 16.0253 31.5000 15.4747

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 369.2670 80.5531 360.3738 1085.1875 0.3403 -0.1551 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9709 8.2889 496.8138 485.5474 451.3937 0.0392 0.1134

 

NASA/TM—2013-218094 O–129
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 376.7187 0.0000 376.7187 1084.6986 0.3473 -0.0451 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2256 496.3675 485.5217 0.0000 0.0600 0.1038 -0.2587

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6655 8.9314 1.0241 507.7624 4.9872 347.6439 2.6949

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31060.398 0.323 89.274 478511.188 0.408031E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.500 EfDer = 0.883 SH = 0.419688E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.861 1792.631 8.931 507.762 1.000 1.000 0.980

 W Kg/sec = 23.119 Wdry = 50.840 WH2O = 0.021 lbm/sec H2O = 0.307g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.824 1811.836 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66985.430 39901.480 2.117 513.330 242.512 395.845 1.632

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 313.18 -0.11 313.18 0.29 0.40 304.52

 MEAN 16.97 0.00 -0.02 313.18 -0.11 313.18 0.29 0.38

 HUB 14.32 0.00 -0.02 313.18 -0.11 313.18 0.29 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.90 46.36 -2.46 301.30 434.66 8.44 499.89 485.40 4.65

 MEAN 40.30 43.80 -3.50 265.48 410.63 8.44 499.89 485.40 4.65

 HUB 35.59 37.84 -2.25 224.02 385.12 8.44 499.89 485.40 4.65

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.69 51.64 341.81 1089.33 0.32 2.16 1.89 8.34

 MEAN 16.57 350.56 81.01 341.07 1090.04 0.32 2.24 1.97 6.35

 HUB 13.89 373.70 153.20 340.86 1090.72 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.35 419.80 243.71 0.39 977.05 0.92 0.81

 MEAN 259.28 384.85 178.27 0.35 1344.44 0.92 0.81 0.81 1.13

 HUB 217.29 346.83 64.09 0.32 2129.47 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.06 1.01 8.46 510.22 1.00 500.62 486.85 4.57

 MEAN 9.11 1.02 8.49 511.14 1.01 501.27 487.37 4.47

 HUB 9.21 1.03 8.50 513.11 1.01 501.90 488.50 4.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.59 35.49 31.50 3.99 0.93 0.08 1.40

 MEAN 13.36 27.59 23.50 4.09 0.89 0.12 1.62

 HUB 24.20 10.65 6.50 4.15 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.883 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 384.5955 81.4633 375.8689 1088.2291 0.3534 -0.1725 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1188 8.3740 499.6138 487.6445 4.7159 12.2288 32.4000 20.1712

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 385.6340 86.4864 375.8107 1088.1631 0.3544 -0.2084 2.2705

 

NASA/TM—2013-218094 O–130
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0930 8.3463 499.5493 487.6138 432.2457 0.0501 0.0776

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 384.1392 0.0000 384.1392 1088.2643 0.3530 -0.0948 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3033 499.6417 487.5415 0.0000 0.0600 0.1322 -0.2751

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4548 9.0400 1.0122 511.4890 3.7268 430.2679 3.3354

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23212.771 0.266 66.718 498484.969 0.428061E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.372 EfDer = 0.820 SH = 0.440314E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.861 1792.631 9.040 511.489 1.000 1.000 0.980

 W Kg/sec = 23.119 Wdry = 50.839 WH2O = 0.022 lbm/sec H2O = 0.324g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.128 1805.223 1.381 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66659.672 39901.160 2.119 509.668 240.479 384.739 1.600

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 313.90 -0.11 313.90 0.29 0.39 288.60

 MEAN 15.91 0.00 -0.02 313.90 -0.11 313.90 0.29 0.37

 HUB 13.07 0.00 -0.02 313.90 -0.11 313.90 0.29 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.41 47.36 -4.95 286.59 425.12 8.54 503.58 487.41 4.28

 MEAN 38.43 44.80 -6.37 248.94 400.69 8.54 503.58 487.41 4.28

 HUB 33.09 38.84 -5.75 204.46 374.67 8.54 503.58 487.41 4.28

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 344.77 33.48 343.14 1092.40 0.32 2.05 1.78 7.43

 MEAN 15.50 347.93 61.82 342.40 1093.19 0.32 2.13 1.86 5.75

 HUB 12.59 366.84 132.08 342.23 1093.93 0.34 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.65 422.89 247.16 0.39 602.69 0.92 0.75

 MEAN 242.44 387.12 180.62 0.35 959.70 0.92 0.75 0.75 1.10

 HUB 196.95 348.33 64.88 0.32 1664.28 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.11 1.01 8.51 513.00 1.00 503.46 488.30 4.32

 MEAN 9.16 1.01 8.54 513.90 1.00 504.18 488.79 4.22

 HUB 9.24 1.02 8.56 515.67 1.01 504.87 489.77 4.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.57 35.76 31.50 4.26 0.93 0.03 1.40

 MEAN 10.23 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.10 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.820 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 397.8221 62.9485 392.8102 1090.2588 0.3649 -0.2852 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1582 8.3636 501.4852 489.0640 4.5942 9.1043 33.0000 23.8957

 

NASA/TM—2013-218094 O–131
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 411.7576 94.0252 400.8785 1089.2799 0.3780 -0.4487 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0990 8.2552 500.5791 489.0250 410.5396 0.1136 0.0509

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 400.3325 0.0000 400.3325 1090.0931 0.3672 -0.1032 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2816 501.3238 488.9675 0.0000 0.0600 0.1453 -0.4069

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2245 9.0790 1.0043 514.1904 2.7015 546.3323 4.2351

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 16827.703 0.214 48.366 530610.438 0.449068E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0546 Tt4 = 514.1904 T1 = 487.5548

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 165879.88 476.7722 91.3007 1.1435 0.6896 5.4031 1.0546 37.3740

NASA/TM—2013-218094 O–132
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.478 EfDer = 1.000 SH = 0.534222E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.699 1582.520 9.337 500.812 1.000 1.000 0.980

 W Kg/sec = 22.590 Wdry = 49.672 WH2O = 0.027 lbm/sec H2O = 0.426g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.882 1610.535 1.380 0.249 53.366 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60028.742 38988.039 3.694 831.557 225.134 619.754 2.753

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.25 -0.06 173.25 0.16 0.31 289.94

 MEAN 17.06 0.00 -0.02 173.25 -0.06 173.25 0.16 0.27

 HUB 12.51 0.00 -0.02 173.25 -0.06 173.25 0.16 0.23

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.70 50.47 8.23 284.90 333.50 9.18 498.40 482.52 6.81

 MEAN 53.68 47.20 6.48 235.60 292.49 9.18 498.40 482.52 6.81

 HUB 44.93 38.62 6.31 172.76 244.71 9.18 498.40 482.52 6.81

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 286.13 155.89 239.94 1090.11 0.26 7.29 6.52 16.04

 MEAN 18.04 298.46 176.40 240.75 1089.39 0.27 7.43 6.80 12.53

 HUB 15.00 335.11 231.40 242.40 1088.06 0.31 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 284.90 272.42 129.01 0.25 3217.26 0.92 0.91

 MEAN 249.08 251.49 72.68 0.23 3182.50 0.92 0.91 0.91 1.30

 HUB 207.15 243.61 24.24 0.22 3471.68 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.33 507.94 1.01 501.37 487.00 6.45

 MEAN 9.78 1.05 9.29 507.87 1.01 500.72 486.99 6.58

 HUB 9.82 1.05 9.21 508.51 1.02 499.50 487.46 6.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 33.01 28.27 24.20 4.07 0.93 0.31 1.80

 MEAN 36.23 16.80 12.70 4.10 0.93 0.28 2.22

 HUB 43.67 -5.71 -9.30 3.59 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 312.4910 176.0535 258.1778 1088.9017 0.2870 -0.0700 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7914 9.2544 500.2697 487.1692 6.7078 34.2904 35.4000 1.1096

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 263.3343 64.4196 255.3332 1091.3689 0.2413 0.2506 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7906 9.4071 502.5411 487.0522 554.9116 0.0114 0.3653

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.2955 0.0000 261.2955 1091.4568 0.2394 0.2714 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.4001 502.6270 487.0530 0.0000 0.0600 0.0370 0.2372

NASA/TM—2013-218094 O–133
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8770 9.7773 1.0471 508.1055 7.2935 217.2342 1.6840

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45450.492 0.560 127.649 485437.594 0.571386E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.953 EfDer = 0.992 SH = 0.603769E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.699 1582.520 9.777 508.105 1.000 1.000 0.980

 W Kg/sec = 22.590 Wdry = 49.669 WH2O = 0.030 lbm/sec H2O = 0.491g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.954 1598.934 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58816.742 38986.969 2.727 590.487 216.570 468.502 2.163

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 239.06 -0.08 239.06 0.22 0.34 286.73

 MEAN 18.08 0.00 -0.02 239.06 -0.08 239.06 0.22 0.32

 HUB 15.21 0.00 -0.02 239.06 -0.08 239.06 0.22 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.90 46.36 3.54 283.80 371.13 9.46 503.52 487.10 6.51

 MEAN 46.25 42.30 3.95 249.66 345.72 9.46 503.52 487.10 6.51

 HUB 41.32 37.84 3.48 210.05 318.28 9.46 503.52 487.10 6.51

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 279.15 98.49 261.20 1095.44 0.25 2.33 2.04 9.02

 MEAN 18.01 285.39 114.41 261.45 1095.26 0.26 2.40 2.13 7.35

 HUB 15.22 308.37 162.89 261.84 1095.08 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 282.00 319.22 183.51 0.29 2012.84 0.92 0.91

 MEAN 248.72 293.93 134.31 0.27 2062.03 0.92 0.91 0.91 1.27

 HUB 210.23 266.08 47.34 0.24 2480.99 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.06 1.03 9.62 512.57 1.01 506.31 489.74 6.01

 MEAN 10.07 1.03 9.61 512.67 1.01 506.14 489.82 6.05

 HUB 10.13 1.04 9.59 513.60 1.01 505.97 490.39 6.07

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 20.66 35.09 31.50 3.59 0.93 0.23 1.40

 MEAN 23.63 27.19 23.50 3.69 0.92 0.25 1.63

 HUB 31.89 10.25 6.50 3.75 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 315.9029 114.7326 294.3315 1093.9529 0.2888 -0.1855 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0831 9.5235 504.9416 490.0491 6.2821 21.2962 30.6000 9.3038

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 291.0335 61.7012 284.4178 1095.2659 0.2657 -0.0176 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0784 9.6021 506.1524 489.9773 491.5697 0.0199 0.1763

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 301.3610 0.0000 301.3610 1094.7319 0.2753 0.0441 0.5911

NASA/TM—2013-218094 O–134
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5482 505.6616 489.9879 0.0000 0.0600 0.0645 -0.1305

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8189 10.0571 1.0286 512.9478 4.8425 292.2964 2.2659

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30183.654 0.380 84.772 449734.563 0.615537E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.490 EfDer = 0.957 SH = 0.630334E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.699 1582.520 10.057 512.948 1.000 1.000 0.980

 W Kg/sec = 22.590 Wdry = 49.668 WH2O = 0.031 lbm/sec H2O = 0.521g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.239 1591.369 1.380 0.249 53.369 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57899.246 38986.566 2.578 545.479 211.551 424.468 2.006

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 254.75 -0.09 254.75 0.23 0.34 278.71

 MEAN 17.74 0.00 -0.02 254.75 -0.09 254.75 0.23 0.32

 HUB 15.05 0.00 -0.02 254.75 -0.09 254.75 0.23 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.42 46.36 1.06 277.17 376.52 9.69 507.74 489.91 5.93

 MEAN 43.89 43.40 0.49 244.97 353.48 9.69 507.74 489.91 5.93

 HUB 39.22 38.84 0.38 207.84 328.83 9.69 507.74 489.91 5.93

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 288.86 76.28 278.61 1098.99 0.26 2.26 1.98 8.75

 MEAN 17.51 295.01 97.26 278.52 1099.13 0.27 2.34 2.07 6.78

 HUB 14.85 318.08 153.44 278.62 1099.29 0.29 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 273.58 341.39 197.30 0.31 1512.87 0.92 0.88

 MEAN 241.77 313.77 144.51 0.29 1704.21 0.92 0.88 0.88 1.20

 HUB 205.08 283.37 51.64 0.26 2279.87 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.27 1.02 9.79 516.30 1.01 509.61 491.86 5.64

 MEAN 10.29 1.02 9.80 516.72 1.01 509.74 492.10 5.62

 HUB 10.38 1.03 9.80 518.00 1.01 509.88 492.86 5.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 15.31 35.30 31.50 3.80 0.93 0.17 1.40

 MEAN 19.25 27.42 23.50 3.92 0.90 0.20 1.62

 HUB 28.84 10.50 6.50 4.00 0.90 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 328.2587 97.8963 313.3210 1097.6422 0.2991 -0.1995 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3074 9.6955 508.3636 492.3500 5.8631 17.3513 31.5000 14.1487

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 314.8966 68.6926 307.3128 1098.3892 0.2867 -0.1218 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2969 9.7333 509.0529 492.2993 451.3937 0.0304 0.1306

 

NASA/TM—2013-218094 O–135
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 320.5998 0.0000 320.5998 1098.0741 0.2920 -0.0224 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6818 508.7622 492.2816 0.0000 0.0600 0.0949 -0.2217

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7093 10.2636 1.0205 517.0074 4.0599 330.9730 2.5657

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25308.199 0.338 71.079 455803.063 0.641440E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.626 EfDer = 0.902 SH = 0.656142E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.699 1582.520 10.264 517.007 1.000 1.000 0.980

 W Kg/sec = 22.590 Wdry = 49.666 WH2O = 0.033 lbm/sec H2O = 0.548g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.065 1585.108 1.380 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57336.824 38986.172 2.467 513.330 208.118 395.845 1.902

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 268.07 -0.09 268.07 0.24 0.34 266.41

 MEAN 16.97 0.00 -0.02 268.07 -0.09 268.07 0.24 0.32

 HUB 14.32 0.00 -0.02 268.07 -0.09 268.07 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.79 46.36 -1.57 265.98 377.70 9.85 511.24 492.18 5.51

 MEAN 41.17 43.80 -2.63 234.37 356.14 9.85 511.24 492.18 5.51

 HUB 36.43 37.84 -1.41 197.76 333.18 9.85 511.24 492.18 5.51

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 296.86 52.62 292.16 1101.71 0.27 2.16 1.89 8.34

 MEAN 16.57 301.68 76.54 291.81 1102.12 0.27 2.24 1.97 6.35

 HUB 13.89 322.37 137.13 291.75 1102.52 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 260.73 358.70 208.11 0.33 995.24 0.92 0.83

 MEAN 228.89 329.18 152.34 0.30 1270.21 0.92 0.83 0.83 1.15

 HUB 191.82 296.83 54.69 0.27 1906.10 0.92 0.83

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.40 1.01 9.89 519.21 1.00 512.14 493.45 5.40

 MEAN 10.43 1.02 9.91 519.82 1.01 512.52 493.78 5.33

 HUB 10.52 1.02 9.92 521.23 1.01 512.89 494.58 5.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.21 35.46 31.50 3.96 0.93 0.10 1.40

 MEAN 14.70 27.57 23.50 4.07 0.89 0.14 1.62

 HUB 25.18 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.902 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 329.6908 76.9754 320.5789 1100.8733 0.2995 -0.1640 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4426 9.8210 511.3693 494.0026 5.5234 13.5019 32.4000 18.8981

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 328.2519 73.6173 319.8903 1100.9581 0.2982 -0.1766 2.2705

 

NASA/TM—2013-218094 O–136
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4263 9.8109 511.4452 493.9794 432.2457 0.0402 0.0938

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 326.5255 0.0000 326.5255 1101.0558 0.2966 -0.0759 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7738 511.5358 493.9206 0.0000 0.0600 0.1254 -0.2451

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5230 10.3802 1.0114 520.0879 3.0806 405.0847 3.1402

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 19205.729 0.283 53.940 475102.563 0.666683E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.493 EfDer = 0.839 SH = 0.681755E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.699 1582.520 10.380 520.088 1.000 1.000 0.980

 W Kg/sec = 22.590 Wdry = 49.665 WH2O = 0.034 lbm/sec H2O = 0.572g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.476 1580.407 1.380 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57027.391 38985.777 2.469 509.668 206.396 384.739 1.864

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 268.54 -0.09 268.54 0.24 0.33 252.66

 MEAN 15.91 0.00 -0.02 268.54 -0.09 268.54 0.24 0.31

 HUB 13.07 0.00 -0.02 268.54 -0.09 268.54 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.30 47.36 -4.06 253.00 369.01 9.97 514.30 493.81 5.18

 MEAN 39.31 44.80 -5.49 219.76 347.06 9.97 514.30 493.81 5.18

 HUB 33.92 38.84 -4.92 180.50 323.61 9.97 514.30 493.81 5.18

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 295.22 36.95 292.89 1104.31 0.27 2.05 1.78 7.43

 MEAN 15.50 298.59 59.85 292.53 1104.76 0.27 2.13 1.86 5.75

 HUB 12.59 315.63 118.59 292.51 1105.21 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 247.75 360.86 210.80 0.33 664.64 0.92 0.77

 MEAN 214.02 330.67 154.17 0.30 929.02 0.92 0.77 0.77 1.12

 HUB 173.87 297.68 55.28 0.27 1494.20 0.92 0.77

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.46 1.01 9.96 521.56 1.00 514.57 494.65 5.17

 MEAN 10.50 1.01 9.98 522.15 1.00 514.99 494.96 5.10

 HUB 10.57 1.02 9.99 523.40 1.01 515.41 495.65 5.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.19 35.74 31.50 4.24 0.93 0.06 1.40

 MEAN 11.56 27.79 23.50 4.29 0.87 0.10 1.64

 HUB 22.07 10.70 6.50 4.20 0.87 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.839 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.4348 60.9488 333.9180 1102.7563 0.3078 -0.2726 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4971 9.8385 513.1272 495.1886 5.3873 10.3441 33.0000 22.6559

 

NASA/TM—2013-218094 O–137
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 348.2792 79.5298 339.0773 1102.2368 0.3160 -0.3986 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4580 9.7680 512.6392 495.1678 410.5396 0.0939 0.0658

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 339.1496 0.0000 339.1496 1102.7795 0.3075 -0.0905 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7789 513.1425 495.1114 0.0000 0.0600 0.1424 -0.3781

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3153 10.4324 1.0050 522.3679 2.2801 506.2393 3.9243

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14216.211 0.232 39.927 506267.531 0.692478E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0430 Tt4 = 522.3679 T1 = 500.8123 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 134364.28 377.3661 76.8815 1.1173 0.7208 6.4777 1.0430 37.3740

NASA/TM—2013-218094 O–138
 25μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.118 EfDer = 0.957 SH = 0.157989E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.354 2465.824 4.265 477.914 1.000 1.000 0.980

 W Kg/sec = 11.979 Wdry = 26.349 WH2O = 0.004 lbm/sec H2O = 0.060g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.196 2568.871 1.381 0.248 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66741.695 20676.977 3.258 831.557 255.251 619.754 2.428 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 192.63 -0.07 192.63 0.18 0.46 462.46

 MEAN 17.06 0.00 -0.02 192.63 -0.07 192.63 0.18 0.39

 HUB 12.51 0.00 -0.02 192.63 -0.07 192.63 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.55 50.47 16.08 443.92 483.98 4.17 474.93 460.84 2.42

 MEAN 62.32 47.20 15.12 367.11 414.63 4.17 474.93 460.84 2.42

 HUB 54.42 38.62 15.80 269.19 331.07 4.17 474.93 460.84 2.42

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 398.85 304.32 257.81 1074.42 0.37 7.29 6.52 16.04

 MEAN 18.04 404.26 308.54 261.20 1071.31 0.38 7.43 6.80 12.53

 HUB 15.00 438.76 348.99 265.93 1067.45 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 443.92 293.18 139.60 0.27 6279.55 0.92 0.88

 MEAN 388.11 273.05 79.56 0.25 5566.04 0.92 0.88 0.88 1.74

 HUB 322.78 267.22 26.21 0.25 5235.66 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 499.64 1.05 486.85 473.47 1.88

 MEAN 4.84 1.13 4.39 497.17 1.04 484.03 472.17 2.08

 HUB 4.80 1.13 4.28 496.03 1.04 480.55 471.61 2.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.73 28.44 24.20 4.24 0.93 0.57 1.80

 MEAN 49.75 16.94 12.70 4.24 0.95 0.51 2.22

 HUB 52.69 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 416.3228 307.9446 280.1692 1070.9060 0.3888 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8449 4.3712 483.6812 472.4266 2.1461 47.7040 35.4000 -12.3040

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 278.0645 68.0231 269.6159 1079.4109 0.2576 0.5072 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8334 4.6182 491.3993 472.2449 554.9116 0.0344 0.5994

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 276.8794 0.0000 276.8794 1079.4552 0.2565 0.4796 1.3089

NASA/TM—2013-218094 O–139
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5984 491.4521 472.2234 0.0000 0.0600 0.0827 0.4649

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8204 4.8108 1.1281 497.6145 19.7018 169.6211 1.3149

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 122549.633 0.622 182.508 267580.438 0.212974E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.654 EfDer = 0.961 SH = 0.271433E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.354 2465.824 4.811 497.614 1.000 1.000 0.980

 W Kg/sec = 11.979 Wdry = 26.346 WH2O = 0.007 lbm/sec H2O = 0.111g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.873 2517.524 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62280.418 20676.057 2.557 590.487 230.905 468.502 2.029

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 253.13 -0.09 253.13 0.23 0.47 451.46

 MEAN 18.08 0.00 -0.02 253.13 -0.09 253.13 0.23 0.43

 HUB 15.21 0.00 -0.02 253.13 -0.09 253.13 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.22 46.36 13.86 442.20 509.60 4.63 492.46 472.37 2.21

 MEAN 56.95 42.30 14.65 389.01 464.20 4.63 492.46 472.37 2.21

 HUB 52.29 37.84 14.45 327.29 413.83 4.63 492.46 472.37 2.21

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 366.93 252.24 266.48 1093.80 0.34 2.33 2.04 9.02

 MEAN 18.01 367.03 249.53 269.16 1091.33 0.34 2.40 2.13 7.35

 HUB 15.22 389.58 278.77 272.14 1088.90 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 439.41 325.64 187.16 0.30 5152.57 0.92 0.88

 MEAN 387.54 302.48 138.02 0.28 4495.59 0.92 0.88 0.88 1.69

 HUB 327.57 276.48 48.81 0.25 4244.98 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 515.44 1.04 504.61 481.58 1.54

 MEAN 5.31 1.10 4.91 513.16 1.03 502.34 480.48 1.66

 HUB 5.28 1.10 4.84 512.30 1.03 500.10 480.09 1.78

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.43 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.83 27.15 23.50 3.65 0.95 0.51 1.63

 HUB 45.69 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 392.9985 250.2297 303.0395 1090.1022 0.3605 -0.1094 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3190 4.8677 501.2201 480.7439 1.7234 39.5476 30.6000 -8.9476

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 293.2023 62.1610 286.5373 1096.0677 0.2675 0.3575 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3132 5.0587 506.7230 480.6017 491.5697 0.0242 0.4551

 

NASA/TM—2013-218094 O–140
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 303.9026 0.0000 303.9026 1095.5013 0.2774 0.3489 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0252 506.2096 480.5886 0.0000 0.0600 0.0625 0.2760

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8370 5.2974 1.1011 513.6307 16.0172 191.3180 1.4831

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 99673.313 0.516 148.439 243035.516 0.293956E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.669 EfDer = 0.976 SH = 0.324344E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.354 2465.824 5.297 513.631 1.000 1.000 0.980

 W Kg/sec = 11.979 Wdry = 26.345 WH2O = 0.009 lbm/sec H2O = 0.141g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.772 2477.962 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58377.945 20675.627 2.560 545.479 213.055 424.468 1.992

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 256.85 -0.09 256.85 0.23 0.46 433.99

 MEAN 17.74 0.00 -0.02 256.85 -0.09 256.85 0.23 0.42

 HUB 15.05 0.00 -0.02 256.85 -0.09 256.85 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.26 46.36 12.90 431.87 502.56 5.10 508.33 480.61 1.57

 MEAN 56.07 43.40 12.67 381.70 460.15 5.10 508.33 480.61 1.57

 HUB 51.59 38.84 12.75 323.85 413.41 5.10 508.33 480.61 1.57

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 358.79 235.85 270.38 1109.73 0.32 2.26 1.98 8.75

 MEAN 17.51 360.87 236.33 272.73 1107.62 0.33 2.34 2.07 6.78

 HUB 14.85 385.33 269.58 275.32 1105.55 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.28 330.70 190.43 0.30 4674.01 0.92 0.89

 MEAN 376.71 306.74 140.39 0.28 4138.81 0.92 0.89 0.89 1.64

 HUB 319.55 279.82 49.96 0.25 4004.65 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.86 1.11 5.45 529.79 1.03 519.45 488.35 1.16

 MEAN 5.79 1.09 5.39 527.94 1.03 517.48 487.51 1.23

 HUB 5.77 1.09 5.31 527.48 1.03 515.55 487.34 1.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.10 35.16 31.50 3.66 0.93 0.51 1.40

 MEAN 40.91 27.24 23.50 3.74 0.94 0.49 1.62

 HUB 44.40 10.29 6.50 3.79 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 388.0117 237.8760 306.5422 1106.3495 0.3507 -0.1173 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8033 5.3360 516.3085 487.7543 1.2820 37.8114 31.5000 -6.3114

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 301.6723 65.8078 294.4071 1111.4609 0.2714 0.3058 2.3726

 

NASA/TM—2013-218094 O–141
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7996 5.5139 521.0921 487.6394 451.3937 0.0188 0.4299

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 306.7641 0.0000 306.7641 1111.1841 0.2761 0.3335 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4919 520.8433 487.6261 0.0000 0.0600 0.0499 0.2537

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8572 5.7864 1.0923 528.4025 14.7726 196.7667 1.5253

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91956.719 0.506 136.947 241522.422 0.349909E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.084 EfDer = 0.986 SH = 0.385848E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.354 2465.824 5.786 528.402 1.000 1.000 0.980

 W Kg/sec = 11.979 Wdry = 26.343 WH2O = 0.010 lbm/sec H2O = 0.178g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.573 2443.080 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54941.703 20675.129 2.595 513.330 197.845 395.845 2.001

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 256.87 -0.09 256.87 0.23 0.44 410.61

 MEAN 16.97 0.00 -0.02 256.87 -0.09 256.87 0.23 0.40

 HUB 14.32 0.00 -0.02 256.87 -0.09 256.87 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.21 46.36 11.85 414.44 487.67 5.58 523.10 487.65 1.20

 MEAN 54.88 43.80 11.08 365.18 446.55 5.58 523.10 487.65 1.20

 HUB 50.19 37.84 12.35 308.14 401.23 5.58 523.10 487.65 1.20

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.50 216.06 269.61 1123.98 0.31 2.16 1.89 8.34

 MEAN 16.57 347.50 216.61 271.72 1122.08 0.31 2.24 1.97 6.35

 HUB 13.89 370.45 249.28 274.03 1120.21 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.27 329.95 190.21 0.29 4080.88 0.92 0.90

 MEAN 356.64 305.69 140.03 0.27 3591.53 0.92 0.90 0.90 1.60

 HUB 298.89 278.49 49.61 0.25 3463.77 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.31 1.09 5.91 542.51 1.03 532.92 493.99 0.94

 MEAN 6.24 1.08 5.85 540.82 1.02 531.12 493.27 0.99

 HUB 6.23 1.08 5.78 540.37 1.02 529.35 493.11 1.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.71 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.56 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.29 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 369.1219 217.8261 297.9980 1121.1876 0.3292 -0.0927 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2553 5.8087 530.2909 493.4719 1.0156 36.1655 32.4000 -3.7655

 

NASA/TM—2013-218094 O–142
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 299.2758 67.1188 291.6523 1125.1412 0.2660 0.2687 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2534 5.9572 534.0400 493.3883 432.2457 0.0146 0.4085

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 296.8831 0.0000 296.8831 1125.2516 0.2638 0.3193 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9513 534.1545 493.3730 0.0000 0.0600 0.0414 0.2544

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8703 6.2423 1.0788 541.2322 12.8306 212.1170 1.6443

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79895.141 0.484 118.985 247101.438 0.415323E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.632 EfDer = 0.993 SH = 0.458460E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.354 2465.824 6.242 541.232 1.000 1.000 0.980

 W Kg/sec = 11.979 Wdry = 26.341 WH2O = 0.012 lbm/sec H2O = 0.224g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.394 2413.950 1.381 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52012.363 20674.539 2.746 509.668 185.621 384.739 2.073

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 244.92 -0.08 244.92 0.22 0.41 385.91

 MEAN 15.91 0.00 -0.02 244.92 -0.08 244.92 0.22 0.37

 HUB 13.07 0.00 -0.02 244.92 -0.08 244.92 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.15 47.36 10.79 394.22 464.18 6.04 536.42 493.41 0.98

 MEAN 54.43 44.80 9.63 342.42 421.07 6.04 536.42 493.41 0.98

 HUB 48.96 38.84 10.12 281.25 373.01 6.04 536.42 493.41 0.98

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 328.04 203.01 257.67 1136.79 0.29 2.05 1.78 7.43

 MEAN 15.50 327.15 198.90 259.74 1134.82 0.29 2.13 1.86 5.75

 HUB 12.59 344.29 223.43 261.94 1132.88 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.04 316.06 183.03 0.28 3643.58 0.92 0.91

 MEAN 333.48 292.53 134.58 0.26 3083.88 0.92 0.91 0.91 1.59

 HUB 270.92 266.21 47.48 0.23 2814.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.08 6.36 553.82 1.02 545.18 498.79 0.80

 MEAN 6.66 1.07 6.29 551.89 1.02 543.29 498.00 0.84

 HUB 6.62 1.06 6.21 550.96 1.02 541.44 497.64 0.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.23 35.39 31.50 3.89 0.93 0.47 1.40

 MEAN 37.44 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.46 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 358.3599 202.5514 295.6260 1133.3611 0.3162 -0.1730 2.0437

 

NASA/TM—2013-218094 O–143
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6628 6.2225 541.9119 498.1636 0.8785 34.4174 33.0000 -1.4174

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 302.1308 68.9918 294.1482 1136.4728 0.2658 0.1506 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6607 6.3456 544.8932 498.0957 410.5396 0.0253 0.3844

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 293.8928 0.0000 293.8928 1136.8743 0.2585 0.3076 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3579 545.2874 498.0929 0.0000 0.0600 0.0373 0.1828

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8792 6.6561 1.0663 552.2207 10.9893 231.7475 1.7965

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68454.742 0.459 101.947 259059.953 0.492543E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.36541E-02

 trTOT = 1.1555 Tt4 = 552.2207 T1 = 477.9137

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 462529.56 688.8268 87.1961 1.5608 0.8402 15.1175 1.1555 37.3740

NASA/TM—2013-218094 O–144
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.226 EfDer = 0.957 SH = 0.148941E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.383 2388.222 4.199 471.470 1.000 1.000 0.980

 W Kg/sec = 11.538 Wdry = 25.379 WH2O = 0.004 lbm/sec H2O = 0.057g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.716 2504.974 1.381 0.248 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64343.285 19915.670 3.353 831.557 247.990 619.754 2.499

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 185.70 -0.06 185.70 0.18 0.44 450.96

 MEAN 17.06 0.00 -0.02 185.70 -0.06 185.70 0.18 0.38

 HUB 12.51 0.00 -0.02 185.70 -0.06 185.70 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.64 50.47 16.17 429.95 468.40 4.11 468.70 457.05 2.96

 MEAN 62.43 47.20 15.23 355.55 401.19 4.11 468.70 457.05 2.96

 HUB 54.55 38.62 15.93 260.72 320.15 4.11 468.70 457.05 2.96

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 386.19 295.09 249.14 1066.71 0.36 7.29 6.52 16.04

 MEAN 18.04 391.26 299.09 252.25 1063.77 0.37 7.43 6.80 12.53

 HUB 15.00 424.26 337.89 256.57 1060.14 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 429.95 283.30 134.87 0.27 6088.96 0.92 0.88

 MEAN 375.89 263.68 76.80 0.25 5395.46 0.92 0.88 0.88 1.75

 HUB 312.62 257.81 25.27 0.24 5069.16 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 491.88 1.04 479.88 469.53 2.31

 MEAN 4.73 1.13 4.32 489.55 1.04 477.24 468.23 2.54

 HUB 4.70 1.12 4.21 488.46 1.04 473.99 467.67 2.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.83 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.86 16.93 12.70 4.23 0.95 0.52 2.22

 HUB 52.79 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 402.8463 298.5078 270.5147 1063.3978 0.3788 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7411 4.2994 476.9154 468.4842 2.6153 47.8164 35.4000 -12.4164

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 268.9917 65.8036 260.8188 1071.4232 0.2511 0.5084 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7306 4.5303 484.1455 468.3117 554.9116 0.0339 0.6001

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 267.8201 0.0000 267.8201 1071.4666 0.2500 0.4796 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5112 484.1958 468.2935 0.0000 0.0600 0.0834 0.4649

NASA/TM—2013-218094 O–145
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8191 4.7090 1.1214 489.9621 18.4933 169.1561 1.3113

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 115024.242 0.622 164.993 260140.875 0.196791E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.680 EfDer = 0.961 SH = 0.247763E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.383 2388.222 4.709 489.962 1.000 1.000 0.980

 W Kg/sec = 11.538 Wdry = 25.377 WH2O = 0.006 lbm/sec H2O = 0.101g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.012 2457.263 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60259.551 19914.898 2.619 590.487 225.454 468.502 2.078

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 244.92 -0.08 244.92 0.23 0.46 440.65

 MEAN 18.08 0.00 -0.02 244.92 -0.08 244.92 0.23 0.42

 HUB 15.21 0.00 -0.02 244.92 -0.08 244.92 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.24 46.36 13.88 428.29 493.44 4.54 485.14 468.43 2.67

 MEAN 56.98 42.30 14.68 376.77 449.45 4.54 485.14 468.43 2.67

 HUB 52.32 37.84 14.48 316.99 400.66 4.54 485.14 468.43 2.67

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 355.51 244.08 258.49 1084.99 0.33 2.33 2.04 9.02

 MEAN 18.01 355.61 241.58 260.95 1082.66 0.33 2.40 2.13 7.35

 HUB 15.22 377.39 269.98 263.69 1080.37 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 425.58 315.84 181.50 0.29 4985.78 0.92 0.88

 MEAN 375.35 293.24 133.77 0.27 4352.37 0.92 0.88 0.88 1.69

 HUB 317.27 267.89 47.29 0.25 4111.18 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.24 1.11 4.87 506.67 1.03 496.51 477.54 1.88

 MEAN 5.17 1.10 4.80 504.54 1.03 494.38 476.45 2.01

 HUB 5.14 1.09 4.73 503.74 1.03 492.29 476.07 2.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.36 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.79 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.68 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 380.7180 242.2581 293.6957 1081.5039 0.3520 -0.1095 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1817 4.7615 493.3319 476.7097 2.0948 39.5179 30.6000 -8.9179

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 284.5467 60.3259 278.0784 1087.1234 0.2617 0.3562 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1765 4.9388 498.4737 476.5754 491.5697 0.0235 0.4537

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 294.8640 0.0000 294.8640 1086.5898 0.2714 0.3474 0.5911

NASA/TM—2013-218094 O–146
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9075 497.9932 476.5651 0.0000 0.0600 0.0624 0.2744

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8368 5.1616 1.0961 504.9804 15.0192 191.2932 1.4829

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93451.742 0.516 134.049 236504.031 0.267425E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.609 EfDer = 0.976 SH = 0.293862E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.383 2388.222 5.162 504.980 1.000 1.000 0.980

 W Kg/sec = 11.538 Wdry = 25.376 WH2O = 0.007 lbm/sec H2O = 0.127g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.327 2420.447 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56669.711 19914.537 2.612 545.479 208.820 424.468 2.033

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.34 -0.09 249.34 0.23 0.45 423.91

 MEAN 17.74 0.00 -0.02 249.34 -0.09 249.34 0.23 0.41

 HUB 15.05 0.00 -0.02 249.34 -0.09 249.34 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.21 46.36 12.85 418.28 487.03 4.98 499.98 476.59 1.91

 MEAN 56.01 43.40 12.61 369.69 445.99 4.98 499.98 476.59 1.91

 HUB 51.53 38.84 12.69 313.66 400.75 4.98 499.98 476.59 1.91

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 347.89 227.65 263.06 1100.00 0.32 2.26 1.98 8.75

 MEAN 17.51 350.00 228.37 265.22 1098.02 0.32 2.34 2.07 6.78

 HUB 14.85 373.79 260.97 267.62 1096.08 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 412.86 321.72 185.21 0.29 4511.55 0.92 0.89

 MEAN 364.86 298.28 136.48 0.27 3999.55 0.92 0.89 0.89 1.64

 HUB 309.49 271.98 48.52 0.25 3876.65 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.68 1.10 5.30 520.09 1.03 510.37 484.21 1.42

 MEAN 5.62 1.09 5.24 518.38 1.03 508.53 483.40 1.51

 HUB 5.60 1.09 5.18 517.96 1.03 506.74 483.23 1.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.87 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.73 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.28 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 376.3779 229.8719 298.0255 1096.8129 0.3432 -0.1179 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6304 5.1954 507.4282 483.6375 1.5665 37.6436 31.5000 -6.1436

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 293.6434 64.0563 286.5715 1101.6144 0.2666 0.3018 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6272 5.3595 511.8820 483.5290 451.3937 0.0181 0.4264

 

NASA/TM—2013-218094 O–147
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 298.5545 0.0000 298.5545 1101.3531 0.2711 0.3302 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3390 511.6483 483.5183 0.0000 0.0600 0.0493 0.2497

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8578 5.6149 1.0878 518.8096 13.8301 197.3074 1.5295

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86075.461 0.505 123.469 235328.031 0.316185E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.941 EfDer = 0.987 SH = 0.347596E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.383 2388.222 5.615 518.809 1.000 1.000 0.980

 W Kg/sec = 11.538 Wdry = 25.374 WH2O = 0.009 lbm/sec H2O = 0.159g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.460 2387.970 1.381 0.249 53.360 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53494.066 19914.117 2.638 513.330 194.581 395.845 2.034

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.10 -0.09 250.10 0.23 0.43 401.35

 MEAN 16.97 0.00 -0.02 250.10 -0.09 250.10 0.23 0.39

 HUB 14.32 0.00 -0.02 250.10 -0.09 250.10 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.08 46.36 11.72 401.40 473.02 5.42 513.78 483.54 1.46

 MEAN 54.74 43.80 10.94 353.69 433.25 5.42 513.78 483.54 1.46

 HUB 50.04 37.84 12.20 298.45 389.45 5.42 513.78 483.54 1.46

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 335.31 207.96 263.03 1113.42 0.30 2.16 1.89 8.34

 MEAN 16.57 337.41 208.89 264.98 1111.64 0.30 2.24 1.97 6.35

 HUB 13.89 359.85 241.13 267.10 1109.90 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 393.48 321.87 185.52 0.29 3927.96 0.92 0.90

 MEAN 345.42 298.08 136.53 0.27 3463.59 0.92 0.90 0.90 1.59

 HUB 289.48 271.45 48.35 0.24 3350.55 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.10 1.09 5.73 531.96 1.03 522.93 489.77 1.15

 MEAN 6.04 1.08 5.67 530.41 1.02 521.26 489.07 1.21

 HUB 6.02 1.07 5.61 530.03 1.02 519.63 488.93 1.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.33 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.25 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.07 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.5353 210.0655 290.5513 1110.7858 0.3228 -0.0936 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0476 5.6319 520.4732 489.2746 1.2464 35.8665 32.4000 -3.4665

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.0880 65.5068 284.6476 1114.4829 0.2621 0.2621 2.2705

 

NASA/TM—2013-218094 O–148
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0461 5.7678 523.9457 489.1957 432.2457 0.0141 0.4031

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.7332 0.0000 289.7332 1114.5912 0.2599 0.3140 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7624 524.0557 489.1829 0.0000 0.0600 0.0407 0.2482

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8713 6.0358 1.0750 530.7981 11.9894 213.3271 1.6537

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74641.203 0.482 107.067 241043.453 0.373425E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.416 EfDer = 0.994 SH = 0.411267E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.383 2388.222 6.036 530.798 1.000 1.000 0.980

 W Kg/sec = 11.538 Wdry = 25.373 WH2O = 0.010 lbm/sec H2O = 0.198g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.536 2360.849 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50776.789 19913.621 2.783 509.668 183.103 384.739 2.101

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.10 -0.08 239.10 0.21 0.40 377.42

 MEAN 15.91 0.00 -0.02 239.10 -0.08 239.10 0.21 0.37

 HUB 13.07 0.00 -0.02 239.10 -0.08 239.10 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.95 47.36 10.59 381.81 450.57 5.85 526.21 489.21 1.20

 MEAN 54.22 44.80 9.42 331.65 408.92 5.85 526.21 489.21 1.20

 HUB 48.73 38.84 9.89 272.39 362.51 5.85 526.21 489.21 1.20

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 318.59 194.93 252.00 1125.48 0.28 2.05 1.78 7.43

 MEAN 15.50 317.99 191.45 253.90 1123.64 0.28 2.13 1.86 5.75

 HUB 12.59 334.87 215.94 255.94 1121.83 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 373.89 309.08 178.96 0.27 3498.56 0.92 0.91

 MEAN 322.99 285.95 131.54 0.25 2968.33 0.92 0.91 0.91 1.58

 HUB 262.39 260.12 46.45 0.23 2719.82 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.49 1.07 6.14 542.51 1.02 534.36 494.49 0.99

 MEAN 6.42 1.06 6.07 540.73 1.02 532.61 493.73 1.04

 HUB 6.38 1.06 6.01 539.90 1.02 530.90 493.39 1.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.72 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.02 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.16 10.29 6.50 3.79 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 348.5475 194.9609 288.9215 1122.2338 0.3106 -0.1748 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4222 6.0121 531.2928 493.8884 1.0816 34.0110 33.0000 -1.0110

 

NASA/TM—2013-218094 O–149
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.5288 67.4842 287.7206 1125.1248 0.2627 0.1410 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4206 6.1238 534.0349 493.8250 410.5396 0.0246 0.3775

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.4829 0.0000 287.4829 1125.5137 0.2554 0.3005 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1353 534.4115 493.8227 0.0000 0.0600 0.0370 0.1733

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8799 6.4162 1.0630 541.0474 10.2501 233.7077 1.8117

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63833.563 0.457 91.564 252977.313 0.441434E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1476 Tt4 = 541.0474 T1 = 471.4698

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 433026.19 621.1423 84.7163 1.5279 0.8406 15.2263 1.1476 37.3740

NASA/TM—2013-218094 O–150
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.284 EfDer = 0.956 SH = 0.139870E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.937 2357.693 4.337 469.498 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.933 WH2O = 0.004 lbm/sec H2O = 0.055g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.636 2478.140 1.381 0.248 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 63364.117 20350.178 3.396 831.557 244.828 619.754 2.531

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 182.88 -0.06 182.88 0.17 0.44 446.13

 MEAN 17.06 0.00 -0.02 182.88 -0.06 182.88 0.17 0.38

 HUB 12.51 0.00 -0.02 182.88 -0.06 182.88 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.69 50.47 16.22 424.46 462.24 4.25 466.81 456.14 3.13

 MEAN 62.48 47.20 15.28 351.01 395.85 4.25 466.81 456.14 3.13

 HUB 54.61 38.62 15.99 257.39 315.80 4.25 466.81 456.14 3.13

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 381.17 291.51 245.58 1064.30 0.36 7.29 6.52 16.04

 MEAN 18.04 386.06 295.38 248.58 1061.43 0.36 7.43 6.80 12.53

 HUB 15.00 418.46 333.51 252.74 1057.88 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 424.46 279.26 132.95 0.26 6015.10 0.92 0.87

 MEAN 371.09 259.85 75.71 0.24 5328.56 0.92 0.87 0.87 1.75

 HUB 308.62 253.96 24.89 0.24 5003.49 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 489.40 1.04 477.72 468.60 2.44

 MEAN 4.88 1.12 4.46 487.13 1.04 475.14 467.30 2.68

 HUB 4.84 1.12 4.35 486.05 1.04 471.97 466.73 3.01

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.89 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.92 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.84 -5.62 -9.30 3.68 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.4501 294.8064 266.5629 1061.0652 0.3746 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8842 4.4388 474.8265 467.5498 2.7612 47.8802 35.4000 -12.4802

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 265.2693 64.8930 257.2095 1068.9005 0.2482 0.5092 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8738 4.6720 481.8694 467.3863 554.9116 0.0336 0.6007

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 264.1046 0.0000 264.1046 1068.9435 0.2471 0.4797 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6525 481.9187 467.3685 0.0000 0.0600 0.0838 0.4651

NASA/TM—2013-218094 O–151
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8185 4.8516 1.1186 487.5262 18.0294 168.9084 1.3094

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 112136.742 0.622 164.360 266552.656 0.183403E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.706 EfDer = 0.961 SH = 0.229768E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.937 2357.693 4.852 487.526 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.931 WH2O = 0.006 lbm/sec H2O = 0.097g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.188 2431.904 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59430.684 20349.461 2.647 590.487 223.039 468.502 2.101

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 241.55 -0.08 241.55 0.23 0.46 436.11

 MEAN 18.08 0.00 -0.02 241.55 -0.08 241.55 0.23 0.41

 HUB 15.21 0.00 -0.02 241.55 -0.08 241.55 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.27 46.36 13.91 422.81 487.02 4.68 482.84 467.49 2.81

 MEAN 57.01 42.30 14.71 371.96 443.58 4.68 482.84 467.49 2.81

 HUB 52.34 37.84 14.50 312.94 395.39 4.68 482.84 467.49 2.81

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 350.98 240.97 255.19 1082.14 0.32 2.33 2.04 9.02

 MEAN 18.01 351.05 238.52 257.57 1079.87 0.33 2.40 2.13 7.35

 HUB 15.22 372.52 266.56 260.21 1077.64 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 420.14 311.81 179.17 0.29 4922.29 0.92 0.88 

 MEAN 370.55 289.44 132.03 0.27 4297.26 0.92 0.88 0.88 1.69

 HUB 313.21 264.36 46.65 0.25 4059.17 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.11 5.01 503.81 1.03 493.90 476.60 1.99

 MEAN 5.32 1.10 4.95 501.74 1.03 491.83 475.52 2.13

 HUB 5.29 1.09 4.88 500.95 1.03 489.80 475.13 2.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.36 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.80 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.69 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.8010 239.1908 289.8520 1078.7426 0.3484 -0.1094 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3283 4.9046 490.8150 475.7735 2.2131 39.5300 30.6000 -8.9300

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 280.9769 59.5691 274.5898 1084.2273 0.2591 0.3562 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3232 5.0834 495.8203 475.6465 491.5697 0.0233 0.4536

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 291.1380 0.0000 291.1380 1083.7070 0.2687 0.3471 0.5911

NASA/TM—2013-218094 O–152
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0517 495.3530 475.6363 0.0000 0.0600 0.0624 0.2741

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8365 5.3080 1.0941 502.1650 14.6397 191.1855 1.4821

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91086.313 0.516 133.506 242426.391 0.247674E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.599 EfDer = 0.976 SH = 0.271747E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.937 2357.693 5.308 502.165 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.930 WH2O = 0.007 lbm/sec H2O = 0.121g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.675 2396.195 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55965.797 20349.127 2.636 545.479 206.908 424.468 2.051

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 246.24 -0.08 246.24 0.23 0.44 419.67

 MEAN 17.74 0.00 -0.02 246.24 -0.08 246.24 0.23 0.41

 HUB 15.05 0.00 -0.02 246.24 -0.08 246.24 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.20 46.36 12.84 412.94 480.85 5.12 497.29 475.66 2.02

 MEAN 56.00 43.40 12.60 364.96 440.33 5.12 497.29 475.66 2.02

 HUB 51.52 38.84 12.68 309.65 395.69 5.12 497.29 475.66 2.02

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 343.55 224.52 260.03 1096.79 0.31 2.26 1.98 8.75

 MEAN 17.51 345.66 225.32 262.12 1094.86 0.32 2.34 2.07 6.78

 HUB 14.85 369.17 257.60 264.44 1092.97 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 407.59 318.01 183.06 0.29 4449.51 0.92 0.89

 MEAN 360.19 294.79 134.87 0.27 3946.11 0.92 0.89 0.89 1.64

 HUB 305.54 268.75 47.94 0.25 3826.61 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.83 1.10 5.45 516.88 1.03 507.39 483.28 1.51

 MEAN 5.77 1.09 5.39 515.21 1.03 505.61 482.46 1.60

 HUB 5.75 1.08 5.32 514.82 1.03 503.87 482.30 1.69

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.81 35.15 31.50 3.65 0.93 0.50 1.40

 MEAN 40.68 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.25 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.7148 226.8000 294.5058 1093.6835 0.3399 -0.1180 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7799 5.3414 504.5340 482.7029 1.6607 37.6000 31.5000 -6.1000

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 290.3156 63.3304 283.3239 1098.3650 0.2643 0.3007 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7768 5.5065 508.8640 482.6002 451.3937 0.0179 0.4254

 

NASA/TM—2013-218094 O–153
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 295.1533 0.0000 295.1533 1098.1102 0.2688 0.3292 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4858 508.6363 482.5900 0.0000 0.0600 0.0491 0.2485

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8580 5.7644 1.0860 515.6358 13.4716 197.4312 1.5305

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83839.227 0.505 122.884 241344.547 0.292078E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.898 EfDer = 0.987 SH = 0.320715E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.937 2357.693 5.764 515.636 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.928 WH2O = 0.008 lbm/sec H2O = 0.151g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.946 2364.688 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 52894.801 20348.734 2.659 513.330 193.073 395.845 2.050

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 247.30 -0.09 247.30 0.22 0.42 397.43

 MEAN 16.97 0.00 -0.02 247.30 -0.09 247.30 0.22 0.39

 HUB 14.32 0.00 -0.02 247.30 -0.09 247.30 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.04 46.36 11.68 396.27 467.18 5.57 510.72 482.61 1.55

 MEAN 54.70 43.80 10.90 349.17 427.94 5.57 510.72 482.61 1.55

 HUB 50.00 37.84 12.16 294.63 384.73 5.57 510.72 482.61 1.55

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.26 204.89 260.29 1109.89 0.30 2.16 1.89 8.34

 MEAN 16.57 333.39 205.94 262.18 1108.16 0.30 2.24 1.97 6.35

 HUB 13.89 355.58 237.95 264.23 1106.46 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.45 318.51 183.56 0.29 3869.94 0.92 0.90

 MEAN 341.00 294.92 135.07 0.27 3414.61 0.92 0.90 0.90 1.59

 HUB 285.78 268.53 47.84 0.24 3306.28 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.25 1.08 5.88 528.43 1.02 519.61 488.83 1.23

 MEAN 6.19 1.07 5.82 526.92 1.02 517.99 488.14 1.29

 HUB 6.17 1.07 5.75 526.57 1.02 516.41 488.00 1.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.21 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.15 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.00 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 354.2892 207.0945 287.4590 1107.3170 0.3200 -0.0939 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1993 5.7802 517.2227 488.3372 1.3252 35.7702 32.4000 -3.3702

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 289.0937 64.8353 281.7296 1110.9159 0.2602 0.2600 2.2705

 

NASA/TM—2013-218094 O–154
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1978 5.9164 520.5921 488.2627 432.2457 0.0139 0.4014

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.7560 0.0000 286.7560 1111.0229 0.2581 0.3123 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9111 520.7002 488.2502 0.0000 0.0600 0.0405 0.2461

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8715 6.1875 1.0734 527.3053 11.6703 213.7101 1.6567

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72648.781 0.481 106.482 247322.906 0.344299E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.343 EfDer = 0.994 SH = 0.378845E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.937 2357.693 6.187 527.305 1.000 1.000 0.980

 W Kg/sec = 11.789 Wdry = 25.927 WH2O = 0.010 lbm/sec H2O = 0.188g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.129 2338.376 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50262.887 20348.270 2.802 509.668 181.906 384.739 2.115 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.68 -0.08 236.68 0.21 0.40 373.83

 MEAN 15.91 0.00 -0.02 236.68 -0.08 236.68 0.21 0.36

 HUB 13.07 0.00 -0.02 236.68 -0.08 236.68 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.88 47.36 10.52 376.93 445.15 6.00 522.81 488.28 1.28

 MEAN 54.14 44.80 9.34 327.41 404.06 6.00 522.81 488.28 1.28

 HUB 48.66 38.84 9.82 268.91 358.30 6.00 522.81 488.28 1.28

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.82 191.82 249.63 1121.65 0.28 2.05 1.78 7.43

 MEAN 15.50 314.32 188.57 251.47 1119.86 0.28 2.13 1.86 5.75

 HUB 12.59 331.11 213.09 253.44 1118.10 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 369.11 306.18 177.29 0.27 3442.81 0.92 0.91

 MEAN 318.86 283.22 130.29 0.25 2923.65 0.92 0.91 0.91 1.58

 HUB 259.04 257.57 45.95 0.23 2683.81 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.64 1.07 6.29 538.68 1.02 530.72 493.54 1.06

 MEAN 6.57 1.06 6.22 536.97 1.02 529.03 492.78 1.11

 HUB 6.54 1.06 6.16 536.17 1.02 527.37 492.45 1.16

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.54 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.86 27.39 23.50 3.89 0.93 0.44 1.64

 HUB 40.06 10.28 6.50 3.78 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 344.5861 192.0255 286.1220 1118.4822 0.3081 -0.1752 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5751 6.1617 527.7392 492.9431 1.1525 33.8668 33.0000 -0.8668

 

NASA/TM—2013-218094 O–155
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 292.7637 66.8528 285.0286 1121.2882 0.2611 0.1377 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5736 6.2733 530.3916 492.8835 410.5396 0.0243 0.3751

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 284.7992 0.0000 284.7992 1121.6714 0.2539 0.2978 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2849 530.7610 492.8810 0.0000 0.0600 0.0369 0.1700

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8801 6.5691 1.0617 537.2744 9.9698 234.3922 1.8170

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 62081.262 0.456 90.993 259680.266 0.406420E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1444 Tt4 = 537.2744 T1 = 469.4978

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 421792.31 618.2261 83.6365 1.5146 0.8406 15.2843 1.1444 37.3740

NASA/TM—2013-218094 O–156
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.387 EfDer = 0.955 SH = 0.158906E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.773 2283.422 4.829 471.208 1.000 1.000 0.980

 W Kg/sec = 12.624 Wdry = 27.769 WH2O = 0.004 lbm/sec H2O = 0.070g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.588 2395.718 1.381 0.248 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61098.543 21790.787 3.525 831.557 235.910 619.754 2.627

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 176.34 -0.06 176.34 0.17 0.42 431.29

 MEAN 17.06 0.00 -0.02 176.34 -0.06 176.34 0.17 0.36

 HUB 12.51 0.00 -0.02 176.34 -0.06 176.34 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.79 50.47 16.32 411.09 447.37 4.74 468.71 458.15 3.64

 MEAN 62.59 47.20 15.39 339.95 383.02 4.74 468.71 458.15 3.64

 HUB 54.73 38.62 16.11 249.28 305.40 4.74 468.71 458.15 3.64

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 369.11 282.56 237.50 1065.64 0.35 7.29 6.52 16.04

 MEAN 18.04 373.68 286.26 240.19 1062.95 0.35 7.43 6.80 12.53

 HUB 15.00 404.70 322.92 243.93 1059.64 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 411.09 270.04 128.53 0.25 5830.47 0.92 0.87

 MEAN 359.40 251.08 73.14 0.24 5163.97 0.92 0.87 0.87 1.75

 HUB 298.90 245.11 24.02 0.23 4844.55 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 489.89 1.04 478.94 470.00 2.84

 MEAN 5.39 1.12 4.95 487.75 1.04 476.53 468.76 3.10

 HUB 5.35 1.11 4.85 486.73 1.03 473.56 468.20 3.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.95 28.42 24.20 4.22 0.93 0.57 1.80

 MEAN 50.00 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.93 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 384.6293 285.7010 257.5163 1062.6146 0.3620 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3960 4.9346 476.2311 468.9951 3.1849 47.9701 35.4000 -12.5701

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.8732 62.8390 249.0685 1069.9351 0.2401 0.5100 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3856 5.1765 482.8195 468.8299 554.9116 0.0327 0.6008

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.7067 0.0000 255.7067 1069.9767 0.2390 0.4791 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1557 482.8673 468.8122 0.0000 0.0600 0.0844 0.4645

NASA/TM—2013-218094 O–157
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8172 5.3619 1.1105 488.1231 16.9163 168.4832 1.3061

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 105227.867 0.623 165.153 284326.656 0.199698E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.705 EfDer = 0.961 SH = 0.242537E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.773 2283.422 5.362 488.123 1.000 1.000 0.980

 W Kg/sec = 12.624 Wdry = 27.766 WH2O = 0.007 lbm/sec H2O = 0.113g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.863 2353.854 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57560.180 21790.072 2.731 590.487 216.236 468.502 2.167 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.95 -0.08 233.95 0.22 0.44 422.11

 MEAN 18.08 0.00 -0.02 233.95 -0.08 233.95 0.22 0.40

 HUB 15.21 0.00 -0.02 233.95 -0.08 233.95 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.26 46.36 13.90 409.49 471.68 5.19 483.72 468.93 3.17

 MEAN 57.00 42.30 14.70 360.24 429.61 5.19 483.72 468.93 3.17

 HUB 52.34 37.84 14.50 303.08 382.94 5.19 483.72 468.93 3.17

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 340.16 232.90 247.93 1082.30 0.31 2.33 2.04 9.02

 MEAN 18.01 340.26 230.73 250.07 1080.18 0.31 2.40 2.13 7.35

 HUB 15.22 361.04 258.09 252.47 1078.10 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.90 302.89 174.00 0.28 4757.54 0.92 0.88

 MEAN 358.88 280.99 128.14 0.26 4156.96 0.92 0.88 0.88 1.68

 HUB 303.34 256.49 45.25 0.24 3930.16 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.91 1.10 5.53 503.36 1.03 494.06 477.63 2.29

 MEAN 5.84 1.09 5.46 501.44 1.03 492.13 476.60 2.44

 HUB 5.82 1.08 5.39 500.71 1.03 490.23 476.23 2.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.21 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.70 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.63 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.2392 231.3813 281.3056 1079.1207 0.3375 -0.1098 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8537 5.4154 491.1746 476.8454 2.5287 39.4382 30.6000 -8.8382

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 273.1549 57.9108 266.9456 1084.2319 0.2519 0.3537 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8488 5.5994 495.8401 476.7208 491.5697 0.0224 0.4510

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 282.9497 0.0000 282.9497 1083.7446 0.2611 0.3446 0.5911

NASA/TM—2013-218094 O–158
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5665 495.4023 476.7120 0.0000 0.0600 0.0619 0.2712

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8367 5.8330 1.0879 501.8358 13.7135 191.3649 1.4834

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85332.875 0.515 133.928 258936.109 0.259021E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.491 EfDer = 0.977 SH = 0.281051E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.773 2283.422 5.833 501.836 1.000 1.000 0.980

 W Kg/sec = 12.624 Wdry = 27.765 WH2O = 0.008 lbm/sec H2O = 0.138g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.845 2321.472 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54424.145 21789.744 2.706 545.479 201.554 424.468 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 239.46 -0.08 239.46 0.22 0.43 406.58

 MEAN 17.74 0.00 -0.02 239.46 -0.08 239.46 0.22 0.39

 HUB 15.05 0.00 -0.02 239.46 -0.08 239.46 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.09 46.36 12.73 399.93 466.20 5.64 497.23 476.73 2.31

 MEAN 55.89 43.40 12.49 353.47 427.01 5.64 497.23 476.73 2.31

 HUB 51.40 38.84 12.56 299.90 383.83 5.64 497.23 476.73 2.31

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.30 216.30 253.58 1095.96 0.30 2.26 1.98 8.75

 MEAN 17.51 335.49 217.47 255.47 1094.17 0.31 2.34 2.07 6.78

 HUB 14.85 358.42 249.25 257.57 1092.42 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 394.75 310.07 178.45 0.28 4286.57 0.92 0.89

 MEAN 348.85 287.27 131.38 0.26 3808.53 0.92 0.89 0.89 1.63

 HUB 295.91 261.76 46.66 0.24 3702.66 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 515.56 1.03 506.64 484.02 1.76

 MEAN 6.31 1.08 5.91 514.03 1.02 504.99 483.25 1.85

 HUB 6.29 1.08 5.85 513.69 1.02 503.37 483.11 1.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.46 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.41 27.22 23.50 3.72 0.94 0.48 1.62

 HUB 44.06 10.27 6.50 3.77 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 360.8957 218.8919 286.9355 1093.0502 0.3302 -0.1190 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3175 5.8639 503.9639 483.4860 1.9177 37.3386 31.5000 -5.8386

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 283.2784 61.7953 276.4561 1097.3966 0.2581 0.2946 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3146 6.0324 507.9809 483.3861 451.3937 0.0170 0.4203

 

NASA/TM—2013-218094 O–159
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 287.9428 0.0000 287.9428 1097.1567 0.2624 0.3244 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0110 507.7667 483.3771 0.0000 0.0600 0.0481 0.2425

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8590 6.3018 1.0804 514.4279 12.5929 198.3307 1.5374

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 78377.758 0.503 123.013 258202.016 0.299532E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.687 EfDer = 0.988 SH = 0.325364E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.773 2283.422 6.302 514.428 1.000 1.000 0.980

 W Kg/sec = 12.624 Wdry = 27.764 WH2O = 0.009 lbm/sec H2O = 0.169g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.518 2292.884 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51629.563 21789.363 2.718 513.330 188.892 395.845 2.096

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.39 -0.08 241.39 0.22 0.41 385.37

 MEAN 16.97 0.00 -0.02 241.39 -0.08 241.39 0.22 0.38

 HUB 14.32 0.00 -0.02 241.39 -0.08 241.39 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.84 46.36 11.48 383.79 453.46 6.10 509.75 483.40 1.79

 MEAN 54.49 43.80 10.69 338.17 415.55 6.10 509.75 483.40 1.79

 HUB 49.78 37.84 11.94 285.35 373.82 6.10 509.75 483.40 1.79

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 321.78 196.66 254.70 1108.15 0.29 2.16 1.89 8.34

 MEAN 16.57 324.08 198.21 256.40 1106.56 0.29 2.24 1.97 6.35

 HUB 13.89 345.88 230.07 258.27 1104.99 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.21 311.63 179.56 0.28 3714.45 0.92 0.90

 MEAN 330.26 288.41 132.06 0.26 3286.45 0.92 0.90 0.90 1.58

 HUB 276.78 262.46 46.71 0.24 3196.88 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.08 6.41 526.32 1.02 518.00 489.35 1.44

 MEAN 6.73 1.07 6.35 524.95 1.02 516.51 488.70 1.50

 HUB 6.72 1.07 6.29 524.66 1.02 515.05 488.59 1.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.67 35.18 31.50 3.68 0.93 0.47 1.40

 MEAN 37.71 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.70 10.25 6.50 3.75 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 344.5717 199.3202 281.0714 1105.7515 0.3116 -0.0951 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7459 6.3123 515.7729 488.8912 1.5400 35.3421 32.4000 -2.9421

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 283.0228 63.4737 275.8134 1109.0706 0.2552 0.2506 2.2705

 

NASA/TM—2013-218094 O–160
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7446 6.4499 518.8756 488.8194 432.2457 0.0132 0.3939

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.7107 0.0000 280.7107 1109.1748 0.2531 0.3048 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4445 518.9802 488.8078 0.0000 0.0600 0.0396 0.2372

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8729 6.7341 1.0686 525.3094 10.8824 215.4838 1.6704

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67748.234 0.479 106.330 264994.438 0.346497E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.040 EfDer = 0.995 SH = 0.377345E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.773 2283.422 6.734 525.309 1.000 1.000 0.980

 W Kg/sec = 12.624 Wdry = 27.763 WH2O = 0.010 lbm/sec H2O = 0.205g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.012 2269.011 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49224.090 21788.920 2.853 509.668 178.636 384.739 2.154

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.79 -0.08 231.79 0.21 0.39 362.74

 MEAN 15.91 0.00 -0.02 231.79 -0.08 231.79 0.21 0.35

 HUB 13.07 0.00 -0.02 231.79 -0.08 231.79 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.59 47.36 10.23 365.06 432.49 6.54 520.99 488.83 1.48

 MEAN 53.84 44.80 9.04 317.09 392.84 6.54 520.99 488.83 1.48

 HUB 48.34 38.84 9.50 260.44 348.71 6.54 520.99 488.83 1.48

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 306.11 183.50 245.01 1119.10 0.27 2.05 1.78 7.43

 MEAN 15.50 305.97 181.01 246.69 1117.46 0.27 2.13 1.86 5.75

 HUB 12.59 322.64 205.81 248.47 1115.84 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 357.48 300.51 173.99 0.27 3293.38 0.92 0.91

 MEAN 308.81 277.83 127.81 0.25 2806.44 0.92 0.91 0.91 1.56

 HUB 250.88 252.53 45.06 0.23 2592.21 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.19 1.07 6.83 535.85 1.02 528.32 493.86 1.23

 MEAN 7.12 1.06 6.77 534.29 1.02 526.77 493.15 1.29

 HUB 7.09 1.05 6.70 533.61 1.02 525.25 492.85 1.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.83 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.27 27.39 23.50 3.89 0.93 0.43 1.64

 HUB 39.64 10.28 6.50 3.78 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 335.7235 184.3259 280.5962 1116.1302 0.3008 -0.1775 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1278 6.6997 525.5311 493.3092 1.3414 33.3012 33.0000 -0.3012

 

NASA/TM—2013-218094 O–161
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 287.4154 65.6316 279.8216 1118.6934 0.2569 0.1244 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1264 6.8109 527.9484 493.2528 410.5396 0.0236 0.3657

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 279.6118 0.0000 279.6118 1119.0631 0.2499 0.2878 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8229 528.3036 493.2493 0.0000 0.0600 0.0366 0.1569

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8807 7.1216 1.0575 534.5817 9.2731 237.1873 1.8387

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57745.070 0.452 90.630 278613.563 0.401814E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1345 Tt4 = 534.5817 T1 = 471.2078

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 394431.81 619.0540 80.5881 1.4749 0.8412 15.3875 1.1345 37.3740

NASA/TM—2013-218094 O–162
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.922 EfDer = 0.967 SH = 0.252956E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.662 2156.069 5.592 480.736 1.000 1.000 0.980

 W Kg/sec = 14.392 Wdry = 31.654 WH2O = 0.008 lbm/sec H2O = 0.126g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.125 2239.577 1.381 0.249 53.356 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61352.113 24841.418 3.545 831.557 234.573 619.754 2.642 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 177.07 -0.06 177.07 0.17 0.40 403.18

 MEAN 17.06 0.00 -0.02 177.07 -0.06 177.07 0.17 0.34

 HUB 12.51 0.00 -0.02 177.07 -0.06 177.07 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.48 50.47 15.01 388.16 426.70 5.49 478.22 465.35 4.41

 MEAN 61.12 47.20 13.92 320.99 366.64 5.49 478.22 465.35 4.41

 HUB 53.05 38.62 14.43 235.38 294.59 5.49 478.22 465.35 4.41

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 352.86 258.83 239.83 1074.40 0.33 7.29 6.52 16.04

 MEAN 18.04 359.71 265.99 242.15 1072.15 0.34 7.43 6.80 12.53

 HUB 15.00 392.83 306.68 245.47 1069.27 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.16 272.48 129.33 0.25 5340.95 0.92 0.88

 MEAN 339.35 253.02 73.36 0.24 4798.44 0.92 0.88 0.88 1.66

 HUB 282.23 246.69 24.45 0.23 4601.00 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 496.89 1.03 486.88 475.31 3.57

 MEAN 6.15 1.10 5.70 495.25 1.03 484.85 474.39 3.83

 HUB 6.13 1.10 5.59 494.65 1.03 482.25 474.12 4.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.18 28.34 24.20 4.14 0.93 0.53 1.80

 MEAN 47.69 16.85 12.70 4.15 0.95 0.48 2.22

 HUB 51.33 -5.69 -9.30 3.61 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.967 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 371.3320 265.4731 259.6372 1071.7732 0.3465 -0.0422 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1620 5.6771 484.5144 474.6158 3.9139 45.6367 35.4000 -10.2367

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 260.2864 63.6740 252.3779 1077.9845 0.2415 0.4696 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1543 5.9128 490.1504 474.4316 554.9116 0.0259 0.5586

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 258.8356 0.0000 258.8356 1078.0403 0.2401 0.4499 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8953 490.2108 474.4204 0.0000 0.0600 0.0698 0.4329

NASA/TM—2013-218094 O–163
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8349 6.1333 1.0968 495.5938 14.8588 175.6454 1.3616

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92468.031 0.614 165.450 319237.875 0.296948E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.862 EfDer = 0.975 SH = 0.340708E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.662 2156.069 6.133 495.594 1.000 1.000 0.980

 W Kg/sec = 14.392 Wdry = 31.652 WH2O = 0.011 lbm/sec H2O = 0.178g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.177 2205.758 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58261.898 24840.563 2.719 590.487 217.173 468.502 2.157

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.80 -0.08 236.80 0.22 0.42 395.55

 MEAN 18.08 0.00 -0.02 236.80 -0.08 236.80 0.22 0.38

 HUB 15.21 0.00 -0.02 236.80 -0.08 236.80 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.52 46.36 12.16 386.65 453.47 5.93 491.09 474.52 3.76

 MEAN 55.16 42.30 12.86 340.15 414.52 5.93 491.09 474.52 3.76

 HUB 50.40 37.84 12.56 286.18 371.51 5.93 491.09 474.52 3.76

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 326.68 207.39 252.41 1088.55 0.30 2.33 2.04 9.02

 MEAN 18.01 328.99 208.85 254.20 1086.86 0.30 2.40 2.13 7.35

 HUB 15.22 351.55 240.72 256.20 1085.19 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.21 308.18 176.81 0.28 4236.64 0.92 0.89

 MEAN 338.86 285.52 130.02 0.26 3762.78 0.92 0.89 0.89 1.59

 HUB 286.42 260.25 45.71 0.24 3665.71 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.66 1.09 6.26 508.40 1.03 499.83 481.73 2.87

 MEAN 6.60 1.08 6.20 506.97 1.02 498.27 480.97 3.02

 HUB 6.59 1.07 6.13 506.68 1.02 496.75 480.86 3.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.41 35.01 31.50 3.51 0.93 0.48 1.40

 MEAN 39.41 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.22 10.11 6.50 3.61 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 354.4812 209.4322 285.9984 1085.7366 0.3265 -0.1230 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6127 6.1480 497.2542 481.2200 3.1318 36.2147 30.6000 -5.6147

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 278.8639 59.1211 272.5247 1089.9274 0.2559 0.2898 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6100 6.3196 501.1013 481.0921 491.5697 0.0165 0.3976

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 288.6503 0.0000 288.6503 1089.4342 0.2650 0.2991 0.5911

NASA/TM—2013-218094 O–164
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2870 500.6551 481.0949 0.0000 0.0600 0.0472 0.2119

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8563 6.5971 1.0756 507.3477 11.7546 204.0037 1.5814

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73174.367 0.496 130.929 291925.313 0.357371E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.414 EfDer = 0.989 SH = 0.379174E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.662 2156.069 6.597 507.348 1.000 1.000 0.980

 W Kg/sec = 14.392 Wdry = 31.650 WH2O = 0.012 lbm/sec H2O = 0.208g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.775 2180.057 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55503.820 24840.188 2.670 545.479 204.293 424.468 2.078

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 244.21 -0.08 244.21 0.22 0.41 381.81

 MEAN 17.74 0.00 -0.02 244.21 -0.08 244.21 0.22 0.38

 HUB 15.05 0.00 -0.02 244.21 -0.08 244.21 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.12 46.36 10.76 377.62 449.78 6.37 502.56 481.09 2.86

 MEAN 53.81 43.40 10.41 333.75 413.62 6.37 502.56 481.09 2.86

 HUB 49.23 38.84 10.39 283.17 373.99 6.37 502.56 481.09 2.86

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.00 189.77 260.14 1099.96 0.29 2.26 1.98 8.75

 MEAN 17.51 326.27 194.89 261.67 1098.59 0.30 2.34 2.07 6.78

 HUB 14.85 350.80 231.72 263.37 1097.25 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 372.73 318.03 182.96 0.29 3761.06 0.92 0.91

 MEAN 329.39 294.21 134.50 0.27 3413.31 0.92 0.91 0.91 1.53

 HUB 279.41 267.66 47.69 0.24 3442.25 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.10 1.08 6.69 518.71 1.02 510.39 487.12 2.29

 MEAN 7.05 1.07 6.64 517.66 1.02 509.11 486.60 2.38

 HUB 7.05 1.07 6.58 517.75 1.02 507.87 486.69 2.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.11 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.68 27.20 23.50 3.70 0.94 0.43 1.62

 HUB 41.34 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.989 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.4229 196.1670 293.9834 1097.3906 0.3221 -0.1336 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0610 6.5776 508.0116 486.8365 2.4650 33.7141 31.5000 -2.2141

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 291.4090 63.5689 284.3909 1100.8534 0.2647 0.2185 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0596 6.7283 511.2231 486.7365 451.3937 0.0132 0.3619

 

NASA/TM—2013-218094 O–165
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 296.0705 0.0000 296.0705 1100.6094 0.2690 0.2688 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7076 511.0031 486.7349 0.0000 0.0600 0.0383 0.1704

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8741 7.0488 1.0685 518.0428 10.6957 213.6908 1.6565

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66596.984 0.479 119.160 292183.750 0.396996E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.364 EfDer = 0.998 SH = 0.421408E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.662 2156.069 7.049 518.043 1.000 1.000 0.980

 W Kg/sec = 14.392 Wdry = 31.649 WH2O = 0.013 lbm/sec H2O = 0.242g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.989 2157.436 1.381 0.249 53.362 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53058.012 24839.775 2.657 513.330 193.216 395.845 2.049

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 248.06 -0.09 248.06 0.22 0.40 362.60

 MEAN 16.97 0.00 -0.02 248.06 -0.09 248.06 0.22 0.37

 HUB 14.32 0.00 -0.02 248.06 -0.09 248.06 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.61 46.36 9.25 362.38 439.22 6.81 513.10 486.73 2.28

 MEAN 52.16 43.80 8.36 319.31 404.41 6.81 513.10 486.73 2.28

 HUB 47.37 37.84 9.53 269.43 366.30 6.81 513.10 486.73 2.28

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 313.12 169.52 263.27 1110.08 0.28 2.16 1.89 8.34

 MEAN 16.57 317.49 175.46 264.61 1108.90 0.29 2.24 1.97 6.35

 HUB 13.89 340.87 213.04 266.09 1107.74 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.23 322.18 185.71 0.29 3202.14 0.92 0.91

 MEAN 311.84 297.69 136.38 0.27 2909.48 0.92 0.91 0.91 1.48

 HUB 261.34 270.43 48.30 0.24 2960.39 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.49 1.06 7.10 527.72 1.02 519.85 491.62 1.91

 MEAN 7.45 1.06 7.05 526.83 1.02 518.74 491.20 1.97

 HUB 7.46 1.06 6.99 526.99 1.02 517.66 491.31 2.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.78 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.55 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.68 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 339.6028 176.4451 290.1675 1108.0128 0.3065 -0.1078 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4649 7.0001 517.9197 491.3979 2.0262 31.3030 32.4000 1.0970

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 293.2854 65.7753 285.8145 1110.5267 0.2641 0.1660 2.2705

 

NASA/TM—2013-218094 O–166
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4640 7.1153 520.2734 491.3289 432.2457 0.0122 0.3309

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 290.8304 0.0000 290.8304 1110.6438 0.2619 0.2385 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1110 520.3885 491.3173 0.0000 0.0600 0.0370 0.1558

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.4534 1.0574 527.1797 9.1375 235.0787 1.8223

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 56907.566 0.451 101.823 300898.750 0.440848E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.496 EfDer = 1.000 SH = 0.468809E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.662 2156.069 7.453 527.180 1.000 1.000 0.980

 W Kg/sec = 14.392 Wdry = 31.648 WH2O = 0.015 lbm/sec H2O = 0.281g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.955 2138.658 1.381 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50960.211 24839.313 2.765 509.668 184.338 384.739 2.087

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.97 -0.08 239.97 0.22 0.38 341.90

 MEAN 15.91 0.00 -0.02 239.97 -0.08 239.97 0.22 0.34

 HUB 13.07 0.00 -0.02 239.97 -0.08 239.97 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.16 47.36 7.80 344.70 420.07 7.22 522.56 491.32 1.92

 MEAN 51.30 44.80 6.50 299.41 383.77 7.22 522.56 491.32 1.92

 HUB 45.71 38.84 6.87 245.92 343.66 7.22 522.56 491.32 1.92

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.09 156.14 255.10 1119.22 0.27 2.05 1.78 7.43

 MEAN 15.50 301.45 158.50 256.42 1117.99 0.27 2.13 1.86 5.75

 HUB 12.59 320.21 189.86 257.85 1116.79 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.55 313.02 181.41 0.28 2802.67 0.92 0.91

 MEAN 291.59 288.90 133.09 0.26 2457.63 0.92 0.91 0.91 1.46

 HUB 236.88 262.10 47.03 0.23 2391.40 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.86 1.05 7.48 535.65 1.02 528.46 495.43 1.66

 MEAN 7.81 1.05 7.43 534.60 1.01 527.31 494.95 1.71

 HUB 7.80 1.05 7.37 534.40 1.01 526.17 494.88 1.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.47 35.42 31.50 3.92 0.93 0.39 1.40

 MEAN 31.72 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.37 10.34 6.50 3.84 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 333.4774 161.4028 291.8156 1116.5494 0.2987 -0.1964 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8135 7.3507 525.9575 495.1151 1.7831 28.9469 33.0000 4.0531

 

NASA/TM—2013-218094 O–167
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 300.0257 68.5111 292.0987 1118.3541 0.2683 0.0186 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8107 7.4346 527.6586 495.0622 410.5396 0.0270 0.2999

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 291.8581 0.0000 291.8581 1118.7605 0.2609 0.2120 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4488 528.0466 495.0525 0.0000 0.0600 0.0422 0.0545

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8742 7.8047 1.0471 534.8843 7.7051 261.7662 2.0292

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47997.977 0.421 85.881 317274.844 0.490530E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1126 Tt4 = 534.8843 T1 = 480.7357

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 337144.94 603.2435 80.1248 1.3956 0.8547 13.9217 1.1126 37.3740

NASA/TM—2013-218094 O–168
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.173 EfDer = 0.995 SH = 0.394919E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.679 1971.979 6.513 491.411 1.000 1.000 0.980

 W Kg/sec = 18.036 Wdry = 39.663 WH2O = 0.016 lbm/sec H2O = 0.223g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.171 2025.989 1.381 0.249 53.361 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67668.234 31129.043 3.258 831.557 255.229 619.754 2.428

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 195.30 -0.07 195.30 0.18 0.38 364.73

 MEAN 17.06 0.00 -0.02 195.30 -0.07 195.30 0.18 0.33

 HUB 12.51 0.00 -0.02 195.30 -0.07 195.30 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.19 50.47 10.72 355.02 405.25 6.37 488.35 473.18 5.23

 MEAN 56.37 47.20 9.17 293.58 352.67 6.37 488.35 473.18 5.23

 HUB 47.79 38.62 9.17 215.28 290.72 6.37 488.35 473.18 5.23

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 340.74 211.36 267.27 1082.33 0.31 7.29 6.52 16.04

 MEAN 18.04 353.47 229.22 269.07 1080.86 0.33 7.43 6.80 12.53

 HUB 15.00 394.39 285.49 272.10 1078.61 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.02 303.43 143.66 0.28 4361.78 0.92 0.91

 MEAN 310.38 281.04 81.16 0.26 4135.32 0.92 0.91 0.91 1.42

 HUB 258.13 273.47 27.36 0.25 4283.16 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.06 1.08 6.59 503.47 1.02 494.14 480.47 4.57

 MEAN 7.03 1.08 6.53 502.84 1.02 492.81 480.15 4.78

 HUB 7.05 1.08 6.43 503.25 1.02 490.76 480.50 5.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.34 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.43 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.38 -5.74 -9.30 3.56 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.3911 228.7721 288.7479 1080.2843 0.3410 -0.0596 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0376 6.5004 492.2885 480.3896 4.8996 38.3894 35.4000 -2.9894

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 291.7550 71.3722 282.8904 1084.7297 0.2690 0.3356 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0353 6.6948 496.3515 480.2141 554.9116 0.0145 0.4358

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 289.6225 0.0000 289.6225 1084.8303 0.2670 0.3476 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6871 496.4511 480.2142 0.0000 0.0600 0.0397 0.3209

NASA/TM—2013-218094 O–169
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8755 7.0221 1.0782 503.1871 11.7761 200.7722 1.5564

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73326.125 0.582 164.418 394567.313 0.438348E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.321 EfDer = 0.999 SH = 0.478142E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.679 1971.979 7.022 503.187 1.000 1.000 0.980

 W Kg/sec = 18.036 Wdry = 39.660 WH2O = 0.019 lbm/sec H2O = 0.281g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.812 2002.145 1.381 0.249 53.364 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65114.793 31128.029 2.465 590.487 239.550 468.502 1.956

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 264.65 -0.09 264.65 0.24 0.41 359.04

 MEAN 18.08 0.00 -0.02 264.65 -0.09 264.65 0.24 0.38 

 HUB 15.21 0.00 -0.02 264.65 -0.09 264.65 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.20 46.36 6.84 353.64 441.78 6.74 497.56 480.28 4.63 

 MEAN 49.62 42.30 7.32 311.10 408.52 6.74 497.56 480.28 4.63

 HUB 44.69 37.84 6.85 261.75 372.29 6.74 497.56 480.28 4.63

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.94 151.38 285.26 1092.34 0.30 2.33 2.04 9.02

 MEAN 18.01 329.60 163.24 286.33 1091.51 0.30 2.40 2.13 7.35

 HUB 15.22 356.30 210.36 287.58 1090.70 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.40 348.40 200.02 0.32 3093.15 0.92 0.91

 MEAN 309.93 321.72 146.69 0.29 2941.59 0.92 0.91 0.91 1.38

 HUB 261.97 292.17 51.61 0.27 3203.66 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.43 1.06 6.99 511.73 1.02 503.36 485.06 3.89

 MEAN 7.41 1.05 6.96 511.32 1.02 502.59 484.86 3.99

 HUB 7.44 1.06 6.92 512.04 1.02 501.85 485.31 4.08

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.95 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.69 27.13 23.50 3.63 0.93 0.34 1.63

 HUB 36.18 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 361.9185 163.6983 322.7815 1089.9659 0.3320 -0.1638 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4194 6.8811 501.1804 485.1365 4.1794 26.8918 30.6000 3.7082

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 317.0435 67.2155 309.8365 1092.6239 0.2902 0.0965 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4172 7.0016 503.6266 485.0248 491.5697 0.0147 0.2551

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 328.3152 0.0000 328.3152 1091.9851 0.3007 0.1476 0.5911

NASA/TM—2013-218094 O–170
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9605 503.0426 485.0411 0.0000 0.0600 0.0413 0.0086

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8714 7.4048 1.0545 511.6965 8.5098 251.2283 1.9475

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 53003.070 0.429 118.848 363729.719 0.492958E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.396 EfDer = 0.995 SH = 0.511833E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.679 1971.979 7.405 511.696 1.000 1.000 0.980

 W Kg/sec = 18.036 Wdry = 39.658 WH2O = 0.020 lbm/sec H2O = 0.311g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.237 1985.428 1.381 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62938.246 31127.615 2.381 545.479 229.090 424.468 1.853

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 276.92 -0.10 276.92 0.25 0.40 347.73

 MEAN 17.74 0.00 -0.02 276.92 -0.10 276.92 0.25 0.38

 HUB 15.05 0.00 -0.02 276.92 -0.10 276.92 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.29 46.36 4.93 345.38 442.76 7.09 505.54 484.98 3.83

 MEAN 47.80 43.40 4.40 305.26 412.22 7.09 505.54 484.98 3.83

 HUB 43.09 38.84 4.25 258.99 379.22 7.09 505.54 484.98 3.83

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 325.88 129.98 298.83 1099.82 0.30 2.26 1.98 8.75

 MEAN 17.51 333.43 146.57 299.48 1099.36 0.30 2.34 2.07 6.78

 HUB 14.85 361.09 200.48 300.32 1098.92 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 340.91 365.78 210.93 0.33 2576.75 0.92 0.91

 MEAN 301.27 337.08 154.69 0.31 2567.67 0.92 0.91 0.91 1.32

 HUB 255.55 305.33 55.07 0.28 2978.60 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.75 1.05 7.30 518.82 1.01 510.29 488.80 3.35

 MEAN 7.75 1.05 7.28 518.79 1.01 509.87 488.81 3.39

 HUB 7.81 1.05 7.25 519.93 1.02 509.46 489.45 3.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.51 35.22 31.50 3.72 0.93 0.28 1.40

 MEAN 26.08 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.73 10.39 6.50 3.89 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 368.1359 147.5341 337.2799 1097.6588 0.3354 -0.1766 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7635 7.1894 508.2985 489.0867 3.5619 23.6257 31.5000 7.8743

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 336.9844 73.5109 328.8688 1099.5629 0.3065 0.0007 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7583 7.2755 510.0616 489.0021 451.3937 0.0205 0.2129

 

NASA/TM—2013-218094 O–171
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 342.8217 0.0000 342.8217 1099.2157 0.3119 0.0918 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2421 509.7431 488.9945 0.0000 0.0600 0.0570 -0.0668

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8408 7.7403 1.0453 519.1772 7.4810 272.0184 2.1087

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46603.504 0.401 104.498 366373.344 0.526634E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.799 EfDer = 0.974 SH = 0.546503E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.679 1971.979 7.740 519.177 1.000 1.000 0.980

 W Kg/sec = 18.036 Wdry = 39.657 WH2O = 0.022 lbm/sec H2O = 0.341g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.390 1971.072 1.381 0.249 53.366 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61193.102 31127.193 2.325 513.330 220.761 395.845 1.793

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 286.10 -0.10 286.10 0.26 0.40 331.28

 MEAN 16.97 0.00 -0.02 286.10 -0.10 286.10 0.26 0.37

 HUB 14.32 0.00 -0.02 286.10 -0.10 286.10 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.21 46.36 2.85 331.44 437.92 7.39 512.61 488.92 3.28

 MEAN 45.60 43.80 1.80 292.04 408.90 7.39 512.61 488.92 3.28

 HUB 40.75 37.84 2.91 246.43 377.66 7.39 512.61 488.92 3.28

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 325.87 106.43 308.00 1106.16 0.29 2.16 1.89 8.34

 MEAN 16.57 332.75 125.12 308.33 1105.96 0.30 2.24 1.97 6.35

 HUB 13.89 358.50 181.95 308.90 1105.77 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.90 377.62 218.47 0.34 2011.27 0.92 0.89

 MEAN 285.22 347.42 160.09 0.31 2075.45 0.92 0.89 0.89 1.26

 HUB 239.03 314.13 57.08 0.28 2528.70 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.01 1.04 7.55 524.73 1.01 516.21 491.80 2.97

 MEAN 8.02 1.04 7.54 524.91 1.01 516.02 491.90 2.99

 HUB 8.08 1.04 7.52 526.16 1.01 515.85 492.58 3.00

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.06 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 22.09 27.44 23.50 3.94 0.91 0.24 1.62

 HUB 30.50 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 361.4981 125.8272 338.8929 1104.6166 0.3273 -0.1442 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0331 7.4662 514.7802 492.1421 3.1066 20.3694 32.4000 12.0306

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 345.3789 77.4584 336.5810 1105.5992 0.3124 -0.0616 2.2705

 

NASA/TM—2013-218094 O–172
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0238 7.5058 515.6945 492.0886 432.2457 0.0284 0.1764

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 343.1112 0.0000 343.1112 1105.7314 0.3103 0.0380 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4878 515.8198 492.0448 0.0000 0.0600 0.0809 -0.0976

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7713 7.9975 1.0332 525.2684 6.0916 312.8703 2.4254

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37953.840 0.360 85.103 379626.594 0.561437E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.608 EfDer = 0.940 SH = 0.582993E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.679 1971.979 7.998 525.268 1.000 1.000 0.980

 W Kg/sec = 18.036 Wdry = 39.656 WH2O = 0.023 lbm/sec H2O = 0.372g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.393 1959.610 1.380 0.249 53.367 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59838.434 31126.746 2.371 509.668 214.918 384.739 1.790

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 281.78 -0.10 281.78 0.25 0.38 313.28

 MEAN 15.91 0.00 -0.02 281.78 -0.10 281.78 0.25 0.35

 HUB 13.07 0.00 -0.02 281.78 -0.10 281.78 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.22 47.36 0.86 315.26 422.91 7.65 518.90 491.97 2.88

 MEAN 44.19 44.80 -0.61 273.84 392.99 7.65 518.90 491.97 2.88

 HUB 38.61 38.84 -0.23 224.92 360.60 7.65 518.90 491.97 2.88

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 317.33 90.95 304.01 1112.00 0.29 2.05 1.78 7.43

 MEAN 15.50 322.68 107.27 304.33 1111.80 0.29 2.13 1.86 5.75

 HUB 12.59 344.24 159.80 304.90 1111.60 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 308.73 373.96 217.77 0.34 1633.49 0.92 0.86 

 MEAN 266.69 343.56 159.43 0.31 1663.92 0.92 0.86 0.86 1.23

 HUB 216.66 310.16 56.86 0.28 2013.11 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.21 1.03 7.77 529.78 1.01 521.70 494.23 2.68

 MEAN 8.22 1.03 7.76 529.86 1.01 521.51 494.28 2.70

 HUB 8.26 1.03 7.74 530.83 1.01 521.32 494.79 2.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.66 35.61 31.50 4.11 0.93 0.19 1.40

 MEAN 19.42 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.66 10.56 6.50 4.06 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.940 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 364.3662 109.2335 347.6073 1109.6553 0.3284 -0.2487 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2228 7.6388 519.5035 494.5084 2.8599 17.4450 33.0000 15.5550

 

NASA/TM—2013-218094 O–173
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 361.0741 82.4516 351.5341 1109.8638 0.3253 -0.2725 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1973 7.6254 519.6949 494.4554 410.5396 0.0734 0.1443

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 351.2930 0.0000 351.2930 1110.4604 0.3163 0.0044 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6414 520.2540 494.4146 0.0000 0.0600 0.1043 -0.2389

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6795 8.1826 1.0231 530.1571 4.8891 364.8164 2.8280

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30466.850 0.320 68.315 402282.625 0.598936E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0788 Tt4 = 530.1571 T1 = 491.4115

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 241353.39 541.1817 87.1710 1.2564 0.8236 9.1730 1.0788 37.3740

NASA/TM—2013-218094 O–174
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.590 EfDer = 0.999 SH = 0.688537E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.713 1794.313 7.939 506.409 1.000 1.000 0.980

 W Kg/sec = 22.142 Wdry = 48.680 WH2O = 0.034 lbm/sec H2O = 0.460g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 89.122 1815.957 1.380 0.249 53.371 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70298.039 38212.375 3.186 831.557 260.997 619.754 2.375

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.89 -0.07 202.89 0.19 0.35 326.92

 MEAN 17.06 0.00 -0.02 202.89 -0.07 202.89 0.19 0.31

 HUB 12.51 0.00 -0.02 202.89 -0.07 202.89 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.87 50.47 7.40 323.03 381.52 7.75 503.11 483.83 6.18

 MEAN 52.79 47.20 5.59 267.13 335.50 7.75 503.11 483.83 6.18

 HUB 44.00 38.62 5.38 195.89 282.07 7.75 503.11 483.83 6.18

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.04 172.01 280.50 1095.83 0.30 7.29 6.52 16.04

 MEAN 18.04 343.81 197.20 281.64 1094.99 0.31 7.43 6.80 12.53

 HUB 15.00 387.30 263.22 284.12 1093.29 0.35 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 323.03 318.57 151.02 0.29 3549.96 0.92 0.91

 MEAN 282.41 294.25 85.22 0.27 3557.83 0.92 0.91 0.91 1.27

 HUB 234.87 285.53 28.34 0.26 3949.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.41 1.06 7.91 515.33 1.02 506.64 489.05 5.75

 MEAN 8.41 1.06 7.87 515.35 1.02 505.86 489.11 5.89

 HUB 8.47 1.07 7.77 516.33 1.02 504.30 489.80 6.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.52 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 35.00 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.81 -5.70 -9.30 3.60 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 360.7892 196.8131 302.3797 1094.2927 0.3297 -0.0736 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4253 7.8224 505.2271 489.3439 6.0307 33.0593 35.4000 2.3407

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.5804 75.2435 298.2350 1097.3756 0.2803 0.2283 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4232 7.9819 508.0801 489.1663 554.9116 0.0136 0.3489

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 305.2665 0.0000 305.2665 1097.4921 0.2781 0.2526 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9747 508.1939 489.1609 0.0000 0.0600 0.0385 0.2158

NASA/TM—2013-218094 O–175
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8729 8.4087 1.0592 515.6691 9.2599 222.7984 1.7271

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57722.855 0.553 158.901 474058.188 0.734674E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.146 EfDer = 0.987 SH = 0.774873E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.713 1794.313 8.409 515.669 1.000 1.000 0.980

 W Kg/sec = 22.142 Wdry = 48.675 WH2O = 0.038 lbm/sec H2O = 0.530g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.910 1799.578 1.380 0.249 53.373 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68595.227 38211.082 2.375 590.487 248.674 468.502 1.884

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.80 -0.10 278.80 0.25 0.39 322.71

 MEAN 18.08 0.00 -0.02 278.80 -0.10 278.80 0.25 0.36

 HUB 15.21 0.00 -0.02 278.80 -0.10 278.80 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.10 46.36 2.74 321.78 425.83 8.05 509.43 489.19 5.68

 MEAN 45.45 42.30 3.15 283.08 397.39 8.05 509.43 489.19 5.68

 HUB 40.52 37.84 2.68 238.16 366.74 8.05 509.43 489.19 5.68

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.94 105.88 304.03 1102.43 0.29 2.33 2.04 9.02

 MEAN 18.01 329.14 125.46 304.29 1102.29 0.30 2.40 2.13 7.35

 HUB 15.22 355.49 183.04 304.75 1102.16 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.74 371.72 213.87 0.34 2163.94 0.92 0.90

 MEAN 282.01 342.19 156.54 0.31 2261.31 0.92 0.90 0.90 1.25

 HUB 238.37 309.73 55.33 0.28 2787.88 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.70 1.03 8.21 521.10 1.01 512.79 492.15 5.17

 MEAN 8.72 1.04 8.20 521.35 1.01 512.66 492.29 5.19

 HUB 8.79 1.05 8.19 522.67 1.01 512.54 493.06 5.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.20 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.41 27.22 23.50 3.72 0.91 0.24 1.63

 HUB 30.99 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.7633 125.8148 343.4434 1100.4768 0.3324 -0.1937 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7307 8.0963 510.9787 492.6060 5.4631 20.1195 30.6000 10.4805

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 339.2822 71.9302 331.5697 1102.0911 0.3079 -0.0439 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7224 8.1750 512.4758 492.4968 491.5697 0.0254 0.1611

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 351.9464 0.0000 351.9464 1101.3326 0.3196 0.0238 0.5911

NASA/TM—2013-218094 O–176
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1114 511.7739 492.5134 0.0000 0.0600 0.0713 -0.1622

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7986 8.6978 1.0344 521.7078 6.0389 303.2032 2.3504

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37654.613 0.368 103.656 439598.813 0.789535E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.241 EfDer = 0.946 SH = 0.808111E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.713 1794.313 8.698 521.708 1.000 1.000 0.980

 W Kg/sec = 22.142 Wdry = 48.674 WH2O = 0.039 lbm/sec H2O = 0.563g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.568 1789.133 1.380 0.249 53.375 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67346.086 38210.586 2.256 545.479 241.822 424.468 1.755

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 296.31 -0.10 296.31 0.27 0.39 313.35

 MEAN 17.74 0.00 -0.02 296.31 -0.10 296.31 0.27 0.37

 HUB 15.05 0.00 -0.02 296.31 -0.10 296.31 0.27 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.69 46.36 0.33 314.26 432.00 8.28 514.67 492.38 5.03

 MEAN 43.16 43.40 -0.24 277.76 406.21 8.28 514.67 492.38 5.03

 HUB 38.51 38.84 -0.33 235.66 378.66 8.28 514.67 492.38 5.03

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.81 80.55 323.95 1106.70 0.30 2.26 1.98 8.75

 MEAN 17.51 340.57 105.96 323.67 1107.01 0.31 2.34 2.07 6.78

 HUB 14.85 366.71 172.27 323.73 1107.31 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 310.19 397.09 229.64 0.36 1597.71 0.92 0.87

 MEAN 274.12 364.75 168.17 0.33 1856.72 0.92 0.87 0.87 1.19

 HUB 232.53 329.29 60.25 0.30 2559.77 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.91 1.02 8.37 525.72 1.01 516.78 494.51 4.75

 MEAN 8.94 1.03 8.38 526.37 1.01 517.07 494.85 4.71

 HUB 9.04 1.04 8.39 528.14 1.01 517.35 495.81 4.66

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.96 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.13 27.45 23.50 3.95 0.90 0.18 1.62

 HUB 28.02 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.946 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.4621 106.6506 365.2083 1104.9287 0.3443 -0.2081 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9588 8.2625 515.1348 495.1776 4.9886 16.2792 31.5000 15.2208

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 367.1439 80.0900 358.3019 1105.7891 0.3320 -0.1489 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9426 8.2941 515.9330 495.1003 451.3937 0.0377 0.1167

 

NASA/TM—2013-218094 O–177
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 374.4215 0.0000 374.4215 1105.3236 0.3387 -0.0407 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2341 515.5003 495.0758 0.0000 0.0600 0.1021 -0.2517

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6744 8.9051 1.0238 526.7420 5.0344 344.3147 2.6691

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31395.598 0.326 86.426 445163.406 0.822079E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.329 EfDer = 0.887 SH = 0.840718E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.713 1794.313 8.905 526.742 1.000 1.000 0.980

 W Kg/sec = 22.142 Wdry = 48.672 WH2O = 0.041 lbm/sec H2O = 0.592g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.034 1780.563 1.380 0.249 53.376 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 66642.461 38210.090 2.163 513.330 237.335 395.845 1.668

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 311.58 -0.11 311.58 0.28 0.39 299.26

 MEAN 16.97 0.00 -0.02 311.58 -0.11 311.58 0.28 0.37

 HUB 14.32 0.00 -0.02 311.58 -0.11 311.58 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.08 46.36 -2.28 301.58 433.70 8.44 518.96 494.90 4.57

 MEAN 40.47 43.80 -3.33 265.73 409.57 8.44 518.96 494.90 4.57

 HUB 35.75 37.84 -2.09 224.23 383.93 8.44 518.96 494.90 4.57

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 344.08 53.31 339.93 1109.89 0.31 2.16 1.89 8.34

 MEAN 16.57 349.07 82.20 339.26 1110.55 0.31 2.24 1.97 6.35

 HUB 13.89 372.35 153.85 339.08 1111.19 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.63 417.46 242.32 0.38 1008.49 0.92 0.81

 MEAN 259.52 382.80 177.32 0.34 1364.19 0.92 0.81 0.81 1.14

 HUB 217.49 345.00 63.65 0.31 2138.45 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.03 1.01 8.46 529.27 1.00 519.78 496.24 4.48

 MEAN 9.08 1.02 8.48 530.17 1.01 520.40 496.68 4.40

 HUB 9.18 1.03 8.50 532.11 1.01 521.00 497.68 4.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.91 35.48 31.50 3.98 0.93 0.08 1.40

 MEAN 13.62 27.59 23.50 4.09 0.89 0.13 1.62

 HUB 24.40 10.63 6.50 4.13 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.887 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.7030 82.6618 373.6691 1108.8140 0.3451 -0.1708 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0886 8.3791 518.7747 496.9691 4.6124 12.4739 32.4000 19.9261

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 383.2201 85.9451 373.4583 1108.7844 0.3456 -0.2025 2.2705

 

NASA/TM—2013-218094 O–178
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0650 8.3554 518.7427 496.9339 432.2457 0.0484 0.0806

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 381.6469 0.0000 381.6469 1108.8878 0.3442 -0.0913 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3143 518.8391 496.8490 0.0000 0.0600 0.1310 -0.2694

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4690 9.0142 1.0123 530.5175 3.7757 424.9605 3.2943

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23548.902 0.269 64.826 463782.625 0.854072E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.195 EfDer = 0.824 SH = 0.873315E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.713 1794.313 9.014 530.517 1.000 1.000 0.980

 W Kg/sec = 22.142 Wdry = 48.671 WH2O = 0.043 lbm/sec H2O = 0.618g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.339 1774.216 1.380 0.249 53.377 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66300.391 38209.602 2.166 509.668 235.305 384.739 1.635 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 312.20 -0.11 312.20 0.28 0.38 283.64

 MEAN 15.91 0.00 -0.02 312.20 -0.11 312.20 0.28 0.36

 HUB 13.07 0.00 -0.02 312.20 -0.11 312.20 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.59 47.36 -4.77 286.86 424.05 8.54 522.70 496.65 4.21

 MEAN 38.61 44.80 -6.19 249.17 399.51 8.54 522.70 496.65 4.21

 HUB 33.26 38.84 -5.58 204.65 373.36 8.54 522.70 496.65 4.21

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 342.94 35.23 341.12 1112.97 0.31 2.05 1.78 7.43

 MEAN 15.50 346.24 63.06 340.44 1113.70 0.31 2.13 1.86 5.75

 HUB 12.59 365.23 132.60 340.31 1114.40 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.91 420.39 245.68 0.38 633.95 0.92 0.75

 MEAN 242.67 384.91 179.60 0.35 979.04 0.92 0.75 0.75 1.10

 HUB 197.14 346.38 64.54 0.31 1670.82 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.09 1.01 8.52 532.11 1.00 522.68 497.51 4.23

 MEAN 9.13 1.01 8.55 532.98 1.00 523.36 497.92 4.14

 HUB 9.21 1.02 8.56 534.71 1.01 524.02 498.78 4.06

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.90 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.49 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.29 10.74 6.50 4.24 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.824 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 395.4791 64.2194 390.2301 1110.8884 0.3560 -0.2830 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1308 8.3749 520.7271 498.2248 4.4661 9.3453 33.0000 23.6547

 

NASA/TM—2013-218094 O–179
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 408.6673 93.3195 397.8698 1109.9882 0.3682 -0.4399 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0763 8.2757 519.8764 498.1911 410.5396 0.1105 0.0537

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 397.4555 0.0000 397.4555 1110.7642 0.3578 -0.1009 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2987 520.6008 498.1150 0.0000 0.0600 0.1449 -0.4017

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2435 9.0556 1.0046 533.2656 2.7481 537.8539 4.1694

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17141.920 0.217 47.189 493746.625 0.887122E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0530 Tt4 = 533.2656 T1 = 506.4094

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 167463.89 460.9982 89.1219 1.1406 0.6959 5.5902 1.0530 37.3740

NASA/TM—2013-218094 O–180
 50μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.147 EfDer = 0.957 SH = 0.515696E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.817 2405.768 4.265 457.735 1.000 1.000 0.980

 W Kg/sec = 12.190 Wdry = 26.816 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.835 2560.957 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65033.578 21041.752 3.272 831.557 254.177 619.754 2.438

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 187.70 -0.06 187.70 0.18 0.45 461.04

 MEAN 17.06 0.00 -0.02 187.70 -0.06 187.70 0.18 0.39

 HUB 12.51 0.00 -0.02 187.70 -0.06 187.70 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.57 50.47 16.10 433.11 472.09 4.17 454.90 448.23 1.97

 MEAN 62.35 47.20 15.15 358.17 404.42 4.17 454.90 448.23 1.97

 HUB 54.45 38.62 15.83 262.64 322.87 4.17 454.90 448.23 1.97

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 389.08 297.05 251.29 1051.48 0.37 7.29 6.52 16.04

 MEAN 18.04 394.32 301.13 254.57 1048.44 0.38 7.43 6.80 12.53

 HUB 15.00 427.86 340.46 259.15 1044.69 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 433.11 285.76 136.06 0.27 6129.53 0.92 0.88

 MEAN 378.65 266.12 77.52 0.25 5432.31 0.92 0.88 0.88 1.74

 HUB 314.91 260.40 25.54 0.25 5107.65 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 478.43 1.05 466.26 462.24 1.32

 MEAN 4.83 1.13 4.39 476.08 1.04 463.57 460.75 1.46

 HUB 4.80 1.12 4.28 474.98 1.04 460.26 460.08 1.66

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.77 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.79 16.94 12.70 4.24 0.95 0.51 2.22

 HUB 52.72 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 406.0566 300.5462 273.0456 1048.0590 0.3874 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8413 4.3709 463.2381 461.0217 1.4924 47.7449 35.4000 -12.3449

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 271.0554 66.3084 262.8197 1056.3395 0.2566 0.5078 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8299 4.6165 470.5901 460.9368 554.9116 0.0344 0.5999

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 269.8990 0.0000 269.8990 1056.3860 0.2555 0.4799 1.3089

NASA/TM—2013-218094 O–181
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5967 470.6402 460.8972 0.0000 0.0600 0.0830 0.4652

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8202 4.8073 1.1272 476.4986 18.7650 169.4940 1.3139

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 116670.711 0.622 176.811 281303.063 0.568022E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.676 EfDer = 0.961 SH = 0.621298E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.817 2405.768 4.807 476.498 1.000 1.000 0.980

 W Kg/sec = 12.190 Wdry = 26.816 WH2O = 0.002 lbm/sec H2O = 0.026g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.597 2510.043 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60710.441 21041.664 2.567 590.487 230.065 468.502 2.036

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 246.75 -0.08 246.75 0.23 0.47 450.12

 MEAN 18.08 0.00 -0.02 246.75 -0.08 246.75 0.23 0.43

 HUB 15.21 0.00 -0.02 246.75 -0.08 246.75 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.24 46.36 13.88 431.43 497.09 4.63 471.60 460.91 1.22

 MEAN 56.98 42.30 14.68 379.54 452.77 4.63 471.60 460.91 1.22

 HUB 52.31 37.84 14.47 319.32 403.62 4.63 471.60 460.91 1.22

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 357.96 246.20 259.85 1070.36 0.33 2.33 2.04 9.02

 MEAN 18.01 358.03 243.52 262.45 1067.95 0.34 2.40 2.13 7.35

 HUB 15.22 379.98 272.00 265.33 1065.58 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 428.70 317.54 182.51 0.30 5029.10 0.92 0.88

 MEAN 378.11 294.94 134.58 0.28 4387.40 0.92 0.88 0.88 1.69

 HUB 319.60 269.57 47.60 0.25 4141.93 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 493.48 1.04 483.18 471.17 0.81

 MEAN 5.30 1.10 4.91 491.31 1.03 481.00 469.92 0.88

 HUB 5.27 1.10 4.83 490.48 1.03 478.87 469.46 0.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.45 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.86 27.15 23.50 3.65 0.95 0.51 1.63

 HUB 45.71 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 383.3200 244.2081 295.4601 1066.7651 0.3593 -0.1093 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3121 4.8642 479.9434 470.1864 0.9100 39.5749 30.6000 -8.9749

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 285.9149 60.6160 279.4156 1072.5736 0.2666 0.3579 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3064 5.0539 485.1855 470.1341 491.5697 0.0241 0.4554

 

NASA/TM—2013-218094 O–182
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.3416 0.0000 296.3416 1072.0258 0.2764 0.3491 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0205 484.6972 470.1063 0.0000 0.0600 0.0627 0.2763

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8368 5.2906 1.1005 491.7590 15.2611 191.2021 1.4822

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 94898.828 0.516 143.816 255436.703 0.642974E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.682 EfDer = 0.976 SH = 0.673551E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.817 2405.768 5.291 491.759 1.000 1.000 0.980

 W Kg/sec = 12.190 Wdry = 26.815 WH2O = 0.002 lbm/sec H2O = 0.031g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.551 2470.790 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56928.914 21041.623 2.568 545.479 212.373 424.468 1.999

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.48 -0.09 250.48 0.23 0.46 432.73

 MEAN 17.74 0.00 -0.02 250.48 -0.09 250.48 0.23 0.42

 HUB 15.05 0.00 -0.02 250.48 -0.09 250.48 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.28 46.36 12.92 421.36 490.26 5.10 486.71 470.10 0.76

 MEAN 56.08 43.40 12.68 372.41 448.88 5.10 486.71 470.10 0.76

 HUB 51.60 38.84 12.76 315.96 403.27 5.10 486.71 470.10 0.76

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 350.05 230.16 263.74 1085.88 0.32 2.26 1.98 8.75

 MEAN 17.51 352.07 230.62 266.02 1083.83 0.32 2.34 2.07 6.78

 HUB 14.85 375.93 263.08 268.54 1081.81 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.90 322.58 185.74 0.30 4561.18 0.92 0.89

 MEAN 367.54 299.19 136.92 0.28 4038.85 0.92 0.89 0.89 1.64

 HUB 311.77 272.91 48.69 0.25 3908.00 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.85 1.11 5.45 507.16 1.03 497.31 478.63 0.54

 MEAN 5.78 1.09 5.38 505.40 1.03 495.43 477.70 0.58

 HUB 5.76 1.09 5.31 504.95 1.03 493.59 477.47 0.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.11 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.92 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.41 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 378.5203 232.1311 298.9862 1082.5967 0.3496 -0.1172 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7930 5.3291 494.3152 477.9323 0.5983 37.8255 31.5000 -6.3255

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 294.2763 64.1944 287.1892 1087.5746 0.2706 0.3060 2.3726

 

NASA/TM—2013-218094 O–183
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7893 5.5058 498.8726 477.8939 451.3937 0.0187 0.4300

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 299.2383 0.0000 299.2383 1087.3080 0.2752 0.3336 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4839 498.6356 477.8678 0.0000 0.0600 0.0500 0.2538

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8571 5.7762 1.0918 505.8353 14.0771 196.6945 1.5248

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87547.023 0.506 132.675 253826.672 0.697809E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.087 EfDer = 0.986 SH = 0.733208E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.817 2405.768 5.776 505.835 1.000 1.000 0.980

 W Kg/sec = 12.190 Wdry = 26.815 WH2O = 0.002 lbm/sec H2O = 0.035g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.396 2436.169 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53596.461 21041.572 2.602 513.330 197.287 395.845 2.006

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.58 -0.09 250.58 0.23 0.44 409.45

 MEAN 16.97 0.00 -0.02 250.58 -0.09 250.58 0.23 0.40

 HUB 14.32 0.00 -0.02 250.58 -0.09 250.58 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.22 46.36 11.86 404.35 475.77 5.57 500.79 477.86 0.52

 MEAN 54.89 43.80 11.09 356.29 435.65 5.57 500.79 477.86 0.52

 HUB 50.20 37.84 12.36 300.64 391.44 5.57 500.79 477.86 0.52

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 337.10 210.79 263.07 1099.77 0.31 2.16 1.89 8.34

 MEAN 16.57 339.05 211.34 265.12 1097.92 0.31 2.24 1.97 6.35

 HUB 13.89 361.42 243.20 267.36 1096.10 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 396.37 321.95 185.58 0.29 3981.35 0.92 0.90

 MEAN 347.96 298.25 136.62 0.27 3504.12 0.92 0.90 0.90 1.60

 HUB 291.61 271.71 48.41 0.25 3379.25 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.29 1.09 5.90 519.28 1.03 510.14 484.79 0.39

 MEAN 6.23 1.08 5.84 517.66 1.02 508.42 483.99 0.41

 HUB 6.21 1.08 5.77 517.24 1.02 506.74 483.79 0.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.70 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.56 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.29 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 360.1412 212.5247 290.7489 1097.0591 0.3283 -0.0927 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2416 5.7983 507.6334 484.1851 0.4236 36.1652 32.4000 -3.7652

 

NASA/TM—2013-218094 O–184
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.0272 65.4932 284.5883 1100.9097 0.2653 0.2686 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2397 5.9457 511.2046 484.1598 432.2457 0.0146 0.4084

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.6907 0.0000 289.6907 1101.0194 0.2631 0.3191 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9398 511.3137 484.1360 0.0000 0.0600 0.0414 0.2543

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8703 6.2287 1.0783 518.0604 12.2260 212.1157 1.6443

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76044.797 0.484 115.244 259676.750 0.761153E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.627 EfDer = 0.993 SH = 0.803521E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.817 2405.768 6.229 518.060 1.000 1.000 0.980

 W Kg/sec = 12.190 Wdry = 26.815 WH2O = 0.002 lbm/sec H2O = 0.041g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.251 2407.253 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50754.027 21041.516 2.753 509.668 185.156 384.739 2.078

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.00 -0.08 239.00 0.22 0.41 384.84

 MEAN 15.91 0.00 -0.02 239.00 -0.08 239.00 0.22 0.37

 HUB 13.07 0.00 -0.02 239.00 -0.08 239.00 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.15 47.36 10.79 384.62 452.89 6.03 513.47 484.13 0.38

 MEAN 54.43 44.80 9.63 334.08 410.84 6.03 513.47 484.13 0.38

 HUB 48.95 38.84 10.11 274.40 363.95 6.03 513.47 484.13 0.38

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 320.09 198.02 251.49 1112.27 0.29 2.05 1.78 7.43

 MEAN 15.50 319.23 194.03 253.49 1110.35 0.29 2.13 1.86 5.75

 HUB 12.59 335.94 217.96 255.63 1108.46 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.64 308.47 178.62 0.28 3553.90 0.92 0.91

 MEAN 325.36 285.49 131.33 0.26 3008.31 0.92 0.91 0.91 1.59

 HUB 264.32 259.80 46.36 0.23 2745.20 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.08 6.35 530.06 1.02 521.82 489.97 0.30

 MEAN 6.64 1.07 6.27 528.21 1.02 520.02 489.10 0.32

 HUB 6.60 1.06 6.20 527.33 1.02 518.25 488.68 0.34

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.22 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.43 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.45 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 349.6824 197.5881 288.5078 1108.9304 0.3153 -0.1731 2.0437

 

NASA/TM—2013-218094 O–185
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6459 6.2089 518.7028 489.2415 0.3320 34.4058 33.0000 -1.4058

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.8816 67.3365 287.0905 1111.9606 0.2652 0.1503 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6439 6.3310 521.5421 489.2215 410.5396 0.0252 0.3841

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.8435 0.0000 286.8435 1112.3541 0.2579 0.3074 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3432 521.9178 489.2111 0.0000 0.0600 0.0373 0.1824

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 6.6393 1.0659 528.5317 10.4721 231.8113 1.7970

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65144.352 0.459 98.724 272237.719 0.836582E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1547 Tt4 = 528.5317 T1 = 457.7346

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 440305.72 667.2701 86.8351 1.5568 0.8402 15.1475 1.1547 37.3740

NASA/TM—2013-218094 O–186
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.252 EfDer = 0.956 SH = 0.497073E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.841 2330.631 4.199 451.561 1.000 1.000 0.980

 W Kg/sec = 11.746 Wdry = 25.839 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.401 2497.877 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62724.348 20275.496 3.366 831.557 247.052 619.754 2.509

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 181.03 -0.06 181.03 0.18 0.44 449.68

 MEAN 17.06 0.00 -0.02 181.03 -0.06 181.03 0.18 0.38

 HUB 12.51 0.00 -0.02 181.03 -0.06 181.03 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.67 50.47 16.20 419.59 457.03 4.11 448.92 443.85 2.51

 MEAN 62.45 47.20 15.25 346.98 391.42 4.11 448.92 443.85 2.51

 HUB 54.57 38.62 15.95 254.44 312.32 4.11 448.92 443.85 2.51

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 376.82 288.06 242.93 1043.93 0.36 7.29 6.52 16.04

 MEAN 18.04 381.73 291.93 245.95 1041.07 0.37 7.43 6.80 12.53

 HUB 15.00 413.86 329.71 250.13 1037.53 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 419.59 276.25 131.52 0.26 5943.98 0.92 0.88

 MEAN 366.83 257.10 74.89 0.25 5266.39 0.92 0.88 0.88 1.75

 HUB 305.08 251.34 24.63 0.24 4946.48 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 471.01 1.04 459.59 457.68 1.69

 MEAN 4.73 1.13 4.32 468.79 1.04 457.07 456.21 1.87

 HUB 4.70 1.12 4.21 467.74 1.04 453.97 455.53 2.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.86 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.89 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.81 -5.62 -9.30 3.68 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 393.0105 291.3670 263.7471 1040.7058 0.3776 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7380 4.2992 456.7578 456.4719 1.9051 47.8484 35.4000 -12.4484

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.3156 64.1704 254.3455 1048.5208 0.2502 0.5089 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7276 4.5287 463.6464 456.3914 554.9116 0.0338 0.6005

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.1715 0.0000 261.1715 1048.5664 0.2491 0.4798 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5097 463.6944 456.3574 0.0000 0.0600 0.0836 0.4651

NASA/TM—2013-218094 O–187
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8189 4.7060 1.1207 469.1802 17.6201 169.0573 1.3105

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 109550.539 0.622 159.975 273634.031 0.542353E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.699 EfDer = 0.961 SH = 0.588898E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.841 2330.631 4.706 469.180 1.000 1.000 0.980

 W Kg/sec = 11.746 Wdry = 25.839 WH2O = 0.002 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.769 2450.540 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58763.699 20275.422 2.628 590.487 224.714 468.502 2.085

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.84 -0.08 238.84 0.23 0.46 439.45

 MEAN 18.08 0.00 -0.02 238.84 -0.08 238.84 0.23 0.42

 HUB 15.21 0.00 -0.02 238.84 -0.08 238.84 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.26 46.36 13.90 417.96 481.46 4.54 464.59 456.37 1.56

 MEAN 57.00 42.30 14.70 367.69 438.52 4.54 464.59 456.37 1.56

 HUB 52.34 37.84 14.50 309.35 390.89 4.54 464.59 456.37 1.56

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 346.91 238.26 252.14 1061.74 0.33 2.33 2.04 9.02

 MEAN 18.01 346.97 235.81 254.53 1059.48 0.33 2.40 2.13 7.35

 HUB 15.22 368.20 263.48 257.18 1057.24 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.31 308.09 177.05 0.29 4867.06 0.92 0.88

 MEAN 366.30 286.03 130.49 0.27 4248.38 0.92 0.88 0.88 1.69

 HUB 309.61 261.29 46.13 0.25 4012.28 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.23 1.11 4.87 485.10 1.03 475.42 466.54 1.04

 MEAN 5.17 1.10 4.80 483.08 1.03 473.40 465.31 1.13

 HUB 5.14 1.09 4.73 482.31 1.03 471.40 464.85 1.21

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.38 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.81 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.69 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.4494 236.4698 286.4554 1058.3539 0.3510 -0.1094 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1758 4.7584 472.3992 465.5714 1.1687 39.5398 30.6000 -8.9398

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 277.5713 58.8471 271.2616 1063.8274 0.2609 0.3566 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1707 4.9347 477.2991 465.5215 491.5697 0.0235 0.4540

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 287.6291 0.0000 287.6291 1063.3107 0.2705 0.3476 0.5911

NASA/TM—2013-218094 O–188
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9035 476.8418 465.4977 0.0000 0.0600 0.0625 0.2746

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8366 5.1558 1.0956 483.4948 14.3153 191.1999 1.4822

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89013.930 0.516 129.985 248709.438 0.606838E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.619 EfDer = 0.976 SH = 0.632465E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.841 2330.631 5.156 483.495 1.000 1.000 0.980

 W Kg/sec = 11.746 Wdry = 25.839 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.131 2413.991 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55282.051 20275.385 2.620 545.479 208.215 424.468 2.039 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.23 -0.08 243.23 0.23 0.45 422.78

 MEAN 17.74 0.00 -0.02 243.23 -0.08 243.23 0.23 0.41

 HUB 15.05 0.00 -0.02 243.23 -0.08 243.23 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.22 46.36 12.86 408.20 475.24 4.97 478.74 465.49 0.98

 MEAN 56.02 43.40 12.62 360.78 435.18 4.97 478.74 465.49 0.98

 HUB 51.54 38.84 12.70 306.10 391.03 4.97 478.74 465.49 0.98

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.50 222.20 256.68 1076.37 0.32 2.26 1.98 8.75

 MEAN 17.51 341.55 222.90 258.78 1074.45 0.32 2.34 2.07 6.78

 HUB 14.85 364.74 254.67 261.10 1072.56 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.91 313.91 180.70 0.29 4403.53 0.92 0.89

 MEAN 356.06 291.03 133.15 0.27 3903.78 0.92 0.89 0.89 1.64

 HUB 302.03 265.36 47.35 0.25 3783.16 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.67 1.10 5.30 497.90 1.03 488.63 473.95 0.70

 MEAN 5.61 1.09 5.24 496.26 1.03 486.88 473.03 0.74

 HUB 5.60 1.09 5.17 495.87 1.03 485.17 472.82 0.79

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.88 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.74 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.29 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 367.2739 224.3675 290.7737 1073.2749 0.3422 -0.1179 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6216 5.1895 485.8306 473.2668 0.7704 37.6546 31.5000 -6.1546

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.5322 62.5051 279.6316 1077.9525 0.2658 0.3019 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6184 5.3526 490.0754 473.2302 451.3937 0.0181 0.4265

 

NASA/TM—2013-218094 O–189
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.3202 0.0000 291.3202 1077.7006 0.2703 0.3303 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3322 489.8528 473.2079 0.0000 0.0600 0.0493 0.2498

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8578 5.6062 1.0874 496.6769 13.1829 197.2580 1.5291

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 81980.789 0.505 119.715 247448.453 0.652609E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.943 EfDer = 0.987 SH = 0.682491E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.841 2330.631 5.606 496.677 1.000 1.000 0.980

 W Kg/sec = 11.746 Wdry = 25.839 WH2O = 0.002 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.302 2381.741 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52200.066 20275.346 2.645 513.330 194.083 395.845 2.040

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.05 -0.08 244.05 0.23 0.43 400.30

 MEAN 16.97 0.00 -0.02 244.05 -0.08 244.05 0.23 0.39

 HUB 14.32 0.00 -0.02 244.05 -0.08 244.05 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.08 46.36 11.72 391.72 461.60 5.41 491.89 473.20 0.67

 MEAN 54.74 43.80 10.94 345.16 422.80 5.41 491.89 473.20 0.67

 HUB 50.05 37.84 12.21 291.25 380.05 5.41 491.89 473.20 0.67

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.24 202.93 256.72 1089.46 0.30 2.16 1.89 8.34

 MEAN 16.57 329.30 203.85 258.61 1087.73 0.30 2.24 1.97 6.35

 HUB 13.89 351.17 235.30 260.68 1086.03 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.99 314.15 181.06 0.29 3833.01 0.92 0.90

 MEAN 337.09 290.91 133.23 0.27 3380.08 0.92 0.90 0.90 1.59

 HUB 282.50 264.92 47.20 0.24 3269.56 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.08 1.09 5.72 509.21 1.03 500.60 480.06 0.51

 MEAN 6.03 1.07 5.66 507.73 1.02 499.01 479.27 0.53

 HUB 6.01 1.07 5.60 507.37 1.02 497.45 479.09 0.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.33 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.25 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.07 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.9051 205.0009 283.5635 1086.8979 0.3219 -0.0937 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0360 5.6230 498.2610 479.4725 0.5467 35.8649 32.4000 -3.4649

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 285.0901 63.9374 277.8280 1090.4998 0.2614 0.2620 2.2705

 

NASA/TM—2013-218094 O–190
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0344 5.7580 501.5701 479.4485 432.2457 0.0140 0.4031

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 282.7902 0.0000 282.7902 1090.6073 0.2593 0.3139 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7526 501.6749 479.4274 0.0000 0.0600 0.0407 0.2480

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8713 6.0242 1.0746 508.1045 11.4285 213.3331 1.6537

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71078.508 0.482 103.795 253440.516 0.706065E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.411 EfDer = 0.994 SH = 0.742500E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.841 2330.631 6.024 508.104 1.000 1.000 0.980

 W Kg/sec = 11.746 Wdry = 25.839 WH2O = 0.002 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.408 2354.806 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49561.477 20275.299 2.790 509.668 182.685 384.739 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 233.38 -0.08 233.38 0.21 0.40 376.46

 MEAN 15.91 0.00 -0.02 233.38 -0.08 233.38 0.21 0.37

 HUB 13.07 0.00 -0.02 233.38 -0.08 233.38 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.94 47.36 10.58 372.60 439.73 5.84 503.73 479.42 0.49

 MEAN 54.21 44.80 9.41 323.65 399.08 5.84 503.73 479.42 0.49

 HUB 48.73 38.84 9.89 265.83 353.80 5.84 503.73 479.42 0.49

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 310.93 190.15 246.01 1101.22 0.28 2.05 1.78 7.43

 MEAN 15.50 310.35 186.77 247.86 1099.43 0.28 2.13 1.86 5.75

 HUB 12.59 326.87 210.78 249.84 1097.67 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 364.87 301.75 174.72 0.27 3412.78 0.92 0.91

 MEAN 315.20 279.16 128.43 0.25 2895.80 0.92 0.91 0.91 1.58

 HUB 256.06 253.91 45.29 0.23 2654.72 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.47 1.07 6.13 519.27 1.02 511.49 485.18 0.39

 MEAN 6.40 1.06 6.06 517.57 1.02 509.83 484.34 0.41

 HUB 6.37 1.06 6.00 516.79 1.02 508.20 483.94 0.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.70 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.00 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.15 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 340.1734 190.1966 282.0340 1098.0653 0.3098 -0.1747 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4079 6.0005 508.5720 484.4815 0.4286 33.9947 33.0000 -0.9947

 

NASA/TM—2013-218094 O–191
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 288.5071 65.8808 280.8844 1100.8802 0.2621 0.1408 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4063 6.1114 511.1832 484.4628 410.5396 0.0245 0.3772

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 280.6543 0.0000 280.6543 1101.2611 0.2548 0.3001 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1228 511.5423 484.4529 0.0000 0.0600 0.0369 0.1730

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 6.4019 1.0627 517.8745 9.7708 233.7758 1.8122

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 60776.020 0.457 88.750 265976.906 0.770010E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1469 Tt4 = 517.8745 T1 = 451.5609

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 412399.78 602.2197 84.4009 1.5245 0.8406 15.2515 1.1469 37.3740

NASA/TM—2013-218094 O–192
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.298 EfDer = 0.956 SH = 0.472075E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.431 2302.165 4.337 449.672 1.000 1.000 0.980

 W Kg/sec = 12.014 Wdry = 26.430 WH2O = 0.001 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.410 2472.547 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 61835.391 20739.000 3.406 831.557 244.153 619.754 2.538

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 178.47 -0.06 178.47 0.17 0.44 445.12

 MEAN 17.06 0.00 -0.02 178.47 -0.06 178.47 0.17 0.38

 HUB 12.51 0.00 -0.02 178.47 -0.06 178.47 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.71 50.47 16.24 414.46 451.31 4.25 447.11 442.66 2.70

 MEAN 62.50 47.20 15.30 342.74 386.48 4.25 447.11 442.66 2.70

 HUB 54.63 38.62 16.01 251.33 308.30 4.25 447.11 442.66 2.70

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 372.17 284.69 239.71 1041.57 0.36 7.29 6.52 16.04

 MEAN 18.04 376.93 288.47 242.62 1038.77 0.36 7.43 6.80 12.53

 HUB 15.00 408.51 325.64 246.66 1035.31 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 414.46 272.58 129.77 0.26 5874.38 0.92 0.87

 MEAN 362.35 253.62 73.88 0.24 5203.92 0.92 0.87 0.87 1.75

 HUB 301.35 247.85 24.28 0.24 4885.31 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 468.66 1.04 457.52 456.46 1.82

 MEAN 4.87 1.12 4.45 466.49 1.04 455.06 454.99 2.01

 HUB 4.84 1.12 4.35 465.46 1.04 452.04 454.30 2.28

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.90 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.93 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.86 -5.62 -9.30 3.68 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 388.0429 287.9110 260.1626 1038.4196 0.3737 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8818 4.4385 454.7571 455.2484 2.0504 47.8984 35.4000 -12.4984

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 258.9405 63.3447 251.0729 1046.0585 0.2475 0.5095 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8714 4.6707 461.4750 455.1718 554.9116 0.0336 0.6009

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.8015 0.0000 257.8015 1046.1035 0.2464 0.4798 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6512 461.5221 455.1398 0.0000 0.0600 0.0839 0.4651

NASA/TM—2013-218094 O–193
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8184 4.8493 1.1181 466.8672 17.1965 168.8572 1.3090

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 106918.133 0.622 159.700 280686.469 0.513031E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.714 EfDer = 0.961 SH = 0.555060E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.431 2302.165 4.849 466.867 1.000 1.000 0.980

 W Kg/sec = 12.014 Wdry = 26.430 WH2O = 0.001 lbm/sec H2O = 0.024g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.015 2426.598 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58011.930 20738.930 2.654 590.487 222.507 468.502 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 235.79 -0.08 235.79 0.23 0.45 435.16

 MEAN 18.08 0.00 -0.02 235.79 -0.08 235.79 0.23 0.41

 HUB 15.21 0.00 -0.02 235.79 -0.08 235.79 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.27 46.36 13.91 412.85 475.51 4.68 462.40 455.15 1.68

 MEAN 57.01 42.30 14.71 363.20 433.09 4.68 462.40 455.15 1.68

 HUB 52.35 37.84 14.51 305.57 386.03 4.68 462.40 455.15 1.68

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 342.72 235.32 249.16 1058.98 0.32 2.33 2.04 9.02

 MEAN 18.01 342.77 232.93 251.47 1056.77 0.32 2.40 2.13 7.35

 HUB 15.22 363.70 260.28 254.04 1054.58 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.24 304.43 174.92 0.29 4806.88 0.92 0.88

 MEAN 361.82 282.57 128.89 0.27 4196.55 0.92 0.88 0.88 1.69

 HUB 305.83 258.09 45.55 0.24 3963.50 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.11 5.01 482.40 1.03 472.95 465.33 1.13

 MEAN 5.31 1.10 4.94 480.43 1.03 470.98 464.10 1.21

 HUB 5.29 1.09 4.87 479.67 1.03 469.04 463.64 1.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.36 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.81 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.70 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.9269 233.5853 282.9722 1055.6670 0.3476 -0.1094 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3236 4.9021 470.0067 464.3621 1.2610 39.5387 30.6000 -8.9387

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.3383 58.1617 268.1021 1061.0145 0.2586 0.3563 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3185 5.0800 474.7815 464.3145 491.5697 0.0233 0.4536

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.2540 0.0000 284.2540 1060.5099 0.2680 0.3471 0.5911

NASA/TM—2013-218094 O–194
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0484 474.3359 464.2922 0.0000 0.0600 0.0625 0.2742

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8365 5.3035 1.0937 480.8336 13.9671 191.1492 1.4818

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86849.578 0.516 129.724 255215.109 0.571186E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.601 EfDer = 0.976 SH = 0.593576E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.431 2302.165 5.303 480.833 1.000 1.000 0.980

 W Kg/sec = 12.014 Wdry = 26.430 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.537 2391.097 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54644.211 20738.898 2.642 545.479 206.476 424.468 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.42 -0.08 240.42 0.23 0.44 418.77

 MEAN 17.74 0.00 -0.02 240.42 -0.08 240.42 0.23 0.40

 HUB 15.05 0.00 -0.02 240.42 -0.08 240.42 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.20 46.36 12.84 403.21 469.52 5.12 476.19 464.29 1.06

 MEAN 56.00 43.40 12.60 356.37 429.96 5.12 476.19 464.29 1.06

 HUB 51.52 38.84 12.68 302.36 386.36 5.12 476.19 464.29 1.06

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.47 219.21 253.94 1073.27 0.31 2.26 1.98 8.75

 MEAN 17.51 337.53 220.01 255.97 1071.39 0.32 2.34 2.07 6.78

 HUB 14.85 360.51 251.57 258.22 1069.55 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 397.99 310.56 178.77 0.29 4344.31 0.92 0.89

 MEAN 351.71 287.87 131.70 0.27 3853.06 0.92 0.89 0.89 1.64

 HUB 298.34 262.42 46.77 0.25 3737.03 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.82 1.10 5.45 494.87 1.03 485.82 472.76 0.76

 MEAN 5.76 1.09 5.38 493.28 1.03 484.12 471.84 0.80

 HUB 5.75 1.08 5.32 492.91 1.03 482.46 471.63 0.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.80 35.15 31.50 3.65 0.93 0.50 1.40

 MEAN 40.68 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.25 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 362.9698 221.4523 287.5865 1070.2441 0.3391 -0.1180 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7729 5.3367 483.0930 472.0768 0.8330 37.5976 31.5000 -6.0976

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 283.5226 61.8485 276.6944 1074.8085 0.2638 0.3006 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7698 5.5008 487.2230 472.0417 451.3937 0.0178 0.4253

 

NASA/TM—2013-218094 O–195
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.2435 0.0000 288.2435 1074.5621 0.2682 0.3291 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4802 487.0058 472.0206 0.0000 0.0600 0.0491 0.2484

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8580 5.7575 1.0856 493.6865 12.8537 197.4301 1.5305

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79933.883 0.505 119.394 254044.656 0.611115E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.894 EfDer = 0.987 SH = 0.637775E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.431 2302.165 5.758 493.686 1.000 1.000 0.980

 W Kg/sec = 12.014 Wdry = 26.430 WH2O = 0.002 lbm/sec H2O = 0.031g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.837 2359.766 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51657.770 20738.863 2.664 513.330 192.721 395.845 2.054

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.52 -0.08 241.52 0.22 0.42 396.61

 MEAN 16.97 0.00 -0.02 241.52 -0.08 241.52 0.22 0.39

 HUB 14.32 0.00 -0.02 241.52 -0.08 241.52 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.03 46.36 11.67 386.94 456.20 5.56 489.00 472.02 0.72

 MEAN 54.69 43.80 10.89 340.94 417.89 5.56 489.00 472.02 0.72

 HUB 49.99 37.84 12.15 287.69 375.69 5.56 489.00 472.02 0.72

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.49 200.00 254.25 1086.05 0.30 2.16 1.89 8.34

 MEAN 16.57 325.57 201.05 256.08 1084.36 0.30 2.24 1.97 6.35

 HUB 13.89 347.24 232.31 258.08 1082.71 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 379.30 311.11 179.30 0.29 3777.69 0.92 0.90

 MEAN 332.97 288.06 131.92 0.27 3333.61 0.92 0.90 0.90 1.59

 HUB 279.05 262.28 46.74 0.24 3227.99 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.24 1.08 5.87 505.89 1.02 497.48 478.88 0.55

 MEAN 6.18 1.07 5.81 504.46 1.02 495.93 478.10 0.58

 HUB 6.17 1.07 5.75 504.12 1.02 494.42 477.92 0.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.19 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.14 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 41.99 10.27 6.50 3.77 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 345.9894 202.1821 280.7687 1083.5482 0.3193 -0.0940 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1900 5.7730 495.1957 478.2976 0.5914 35.7577 32.4000 -3.3577

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 282.3878 63.3313 275.1945 1087.0568 0.2598 0.2596 2.2705

 

NASA/TM—2013-218094 O–196
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1885 5.9084 498.4090 478.2747 432.2457 0.0138 0.4011

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.1028 0.0000 280.1028 1087.1633 0.2576 0.3120 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9031 498.5121 478.2549 0.0000 0.0600 0.0405 0.2457

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8716 6.1782 1.0731 504.8202 11.1345 213.7678 1.6571

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 69250.086 0.481 103.436 260313.141 0.658880E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.333 EfDer = 0.994 SH = 0.691973E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.431 2302.165 6.178 504.820 1.000 1.000 0.980

 W Kg/sec = 12.014 Wdry = 26.430 WH2O = 0.002 lbm/sec H2O = 0.036g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.042 2333.599 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49097.445 20738.818 2.806 509.668 181.613 384.739 2.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.20 -0.08 231.20 0.21 0.40 373.07

 MEAN 15.91 0.00 -0.02 231.20 -0.08 231.20 0.21 0.36

 HUB 13.07 0.00 -0.02 231.20 -0.08 231.20 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.87 47.36 10.51 368.05 434.71 5.99 500.52 478.25 0.53

 MEAN 54.13 44.80 9.33 319.70 394.60 5.99 500.52 478.25 0.53

 HUB 48.65 38.84 9.81 262.58 349.92 5.99 500.52 478.25 0.53

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 307.46 187.22 243.88 1097.54 0.28 2.05 1.78 7.43

 MEAN 15.50 306.98 184.07 245.67 1095.79 0.28 2.13 1.86 5.75

 HUB 12.59 323.37 208.03 247.58 1094.08 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 360.42 299.12 173.20 0.27 3360.23 0.92 0.91

 MEAN 311.35 276.68 127.28 0.25 2853.97 0.92 0.91 0.91 1.58

 HUB 252.94 251.62 44.91 0.23 2620.08 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.63 1.07 6.28 515.67 1.02 508.07 484.01 0.42

 MEAN 6.56 1.06 6.21 514.04 1.02 506.46 483.17 0.45

 HUB 6.53 1.06 6.15 513.28 1.02 504.88 482.78 0.47

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.51 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.84 27.39 23.50 3.89 0.93 0.44 1.64

 HUB 40.04 10.28 6.50 3.78 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 336.5471 187.4491 279.5118 1094.4478 0.3075 -0.1753 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5637 6.1523 505.2266 483.3167 0.4642 33.8470 33.0000 -0.8470

 

NASA/TM—2013-218094 O–197
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 286.0184 65.3126 278.4615 1097.1830 0.2607 0.1372 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5621 6.2632 507.7556 483.2990 410.5396 0.0243 0.3747

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.2385 0.0000 278.2385 1097.5588 0.2535 0.2975 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2747 508.1083 483.2895 0.0000 0.0600 0.0368 0.1695

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8802 6.5577 1.0614 514.3320 9.5126 234.5021 1.8178

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59169.270 0.455 88.379 273301.875 0.716709E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1438 Tt4 = 514.3320 T1 = 449.6716

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 402120.97 600.6329 83.4104 1.5120 0.8407 15.2981 1.1438 37.3740

NASA/TM—2013-218094 O–198
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.362 EfDer = 0.955 SH = 0.427622E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.404 2235.554 4.829 451.605 1.000 1.000 0.980

 W Kg/sec = 12.911 Wdry = 28.403 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.685 2395.861 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59883.668 22286.887 3.521 831.557 236.177 619.754 2.624

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.83 -0.06 172.83 0.17 0.42 431.32

 MEAN 17.06 0.00 -0.02 172.83 -0.06 172.83 0.17 0.36

 HUB 12.51 0.00 -0.02 172.83 -0.06 172.83 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.76 50.47 16.29 402.47 438.06 4.74 449.20 444.63 2.45

 MEAN 62.56 47.20 15.36 332.82 375.08 4.74 449.20 444.63 2.45

 HUB 54.70 38.62 16.08 244.06 299.11 4.74 449.20 444.63 2.45

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 361.44 276.50 232.77 1043.24 0.35 7.29 6.52 16.04

 MEAN 18.04 365.95 280.18 235.42 1040.62 0.35 7.43 6.80 12.53

 HUB 15.00 396.41 316.19 239.08 1037.37 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.47 264.67 125.96 0.25 5705.52 0.92 0.87

 MEAN 351.86 246.09 71.69 0.24 5054.27 0.92 0.87 0.87 1.75

 HUB 292.63 240.24 23.56 0.23 4743.66 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 469.51 1.04 459.00 457.76 1.72

 MEAN 5.39 1.12 4.95 467.47 1.04 456.69 456.34 1.89

 HUB 5.35 1.11 4.85 466.49 1.03 453.85 455.68 2.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.91 28.42 24.20 4.22 0.93 0.57 1.80

 MEAN 49.96 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.91 -5.63 -9.30 3.67 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 376.6910 279.6312 252.3935 1040.2882 0.3621 -0.0369 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3962 4.9345 456.4097 456.5923 1.9249 47.9308 35.4000 -12.5308

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 251.7657 61.5896 244.1161 1047.4563 0.2404 0.5094 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3858 5.1762 462.7237 456.5270 554.9116 0.0327 0.6001

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 250.6189 0.0000 250.6189 1047.5006 0.2393 0.4787 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1555 462.7698 456.4971 0.0000 0.0600 0.0842 0.4640

NASA/TM—2013-218094 O–199
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8177 5.3622 1.1105 467.8209 16.2163 168.6145 1.3071

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 100831.609 0.622 161.849 300347.875 0.470083E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.678 EfDer = 0.961 SH = 0.511898E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.404 2235.554 5.362 467.821 1.000 1.000 0.980

 W Kg/sec = 12.911 Wdry = 28.403 WH2O = 0.001 lbm/sec H2O = 0.025g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.949 2353.984 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56412.555 22286.813 2.728 590.487 216.463 468.502 2.164

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 229.29 -0.08 229.29 0.22 0.44 422.13

 MEAN 18.08 0.00 -0.02 229.29 -0.08 229.29 0.22 0.40

 HUB 15.21 0.00 -0.02 229.29 -0.08 229.29 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.24 46.36 13.88 400.91 461.91 5.19 463.59 456.51 1.62

 MEAN 56.98 42.30 14.68 352.69 420.73 5.19 463.59 456.51 1.62

 HUB 52.31 37.84 14.47 296.73 375.06 5.19 463.59 456.51 1.62

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 333.10 227.85 242.98 1059.58 0.31 2.33 2.04 9.02

 MEAN 18.01 333.23 225.77 245.09 1057.51 0.32 2.40 2.13 7.35

 HUB 15.22 353.64 252.66 247.43 1055.47 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.37 296.85 170.52 0.28 4654.34 0.92 0.88

 MEAN 351.35 275.39 125.58 0.26 4067.52 0.92 0.88 0.88 1.68

 HUB 296.98 251.37 44.32 0.24 3847.49 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.91 1.10 5.53 482.42 1.03 473.50 466.24 1.12

 MEAN 5.84 1.09 5.46 480.58 1.03 471.65 465.07 1.20

 HUB 5.82 1.08 5.39 479.89 1.03 469.84 464.63 1.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.16 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.65 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.60 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 356.7454 226.4029 275.6974 1056.4663 0.3377 -0.1099 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8541 5.4153 470.7327 465.3173 1.2458 39.3929 30.6000 -8.7929

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 267.7132 56.7571 261.6276 1061.4703 0.2522 0.3529 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8491 5.5992 475.2034 465.2762 491.5697 0.0223 0.4503

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 277.3115 0.0000 277.3115 1060.9939 0.2614 0.3440 0.5911

NASA/TM—2013-218094 O–200
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5662 474.7827 465.2555 0.0000 0.0600 0.0617 0.2705

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8370 5.8334 1.0879 480.9664 13.1462 191.5391 1.4848

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 81750.703 0.515 131.221 273447.406 0.528030E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.464 EfDer = 0.977 SH = 0.550729E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.404 2235.554 5.833 480.966 1.000 1.000 0.980

 W Kg/sec = 12.911 Wdry = 28.403 WH2O = 0.002 lbm/sec H2O = 0.028g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.925 2321.592 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53337.668 22286.777 2.704 545.479 201.759 424.468 2.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 234.68 -0.08 234.68 0.22 0.43 406.60

 MEAN 17.74 0.00 -0.02 234.68 -0.08 234.68 0.22 0.39 

 HUB 15.05 0.00 -0.02 234.68 -0.08 234.68 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.07 46.36 12.71 391.54 456.55 5.64 476.54 465.25 1.06 

 MEAN 55.86 43.40 12.46 346.06 418.19 5.64 476.54 465.25 1.06

 HUB 51.37 38.84 12.53 293.61 375.93 5.64 476.54 465.25 1.06

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 326.39 211.60 248.52 1072.96 0.30 2.26 1.98 8.75

 MEAN 17.51 328.57 212.78 250.37 1071.22 0.31 2.34 2.07 6.78

 HUB 14.85 351.08 244.01 252.42 1069.50 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.47 303.88 174.87 0.28 4193.35 0.92 0.89

 MEAN 341.53 281.54 128.75 0.26 3726.46 0.92 0.89 0.89 1.63

 HUB 289.71 256.53 45.70 0.24 3624.73 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 494.12 1.03 485.56 473.37 0.78

 MEAN 6.31 1.08 5.91 492.66 1.02 483.98 472.50 0.82

 HUB 6.29 1.08 5.85 492.34 1.02 482.43 472.32 0.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.41 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.36 27.21 23.50 3.71 0.94 0.48 1.62

 HUB 44.03 10.26 6.50 3.76 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.4825 214.1753 281.2096 1070.1180 0.3303 -0.1192 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3178 5.8638 482.9926 472.7309 0.8537 37.2937 31.5000 -5.7937

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 277.6305 60.5632 270.9443 1074.3729 0.2584 0.2937 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3150 6.0321 486.8416 472.7005 451.3937 0.0169 0.4196

 

NASA/TM—2013-218094 O–201
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 282.2006 0.0000 282.2006 1074.1394 0.2627 0.3238 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0108 486.6357 472.6815 0.0000 0.0600 0.0479 0.2417

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8593 6.3023 1.0804 493.0389 12.0732 198.5133 1.5389

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75085.180 0.503 120.522 272615.688 0.568567E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.660 EfDer = 0.988 SH = 0.594804E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.404 2235.554 6.302 493.039 1.000 1.000 0.980

 W Kg/sec = 12.911 Wdry = 28.402 WH2O = 0.002 lbm/sec H2O = 0.032g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.593 2292.993 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50597.902 22286.740 2.715 513.330 189.079 395.845 2.094

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 236.56 -0.08 236.56 0.22 0.41 385.38

 MEAN 16.97 0.00 -0.02 236.56 -0.08 236.56 0.22 0.38

 HUB 14.32 0.00 -0.02 236.56 -0.08 236.56 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.81 46.36 11.45 375.74 444.08 6.10 488.54 472.68 0.75

 MEAN 54.46 43.80 10.66 331.08 406.98 6.10 488.54 472.68 0.75

 HUB 49.75 37.84 11.91 279.37 366.13 6.10 488.54 472.68 0.75

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 315.12 192.34 249.61 1084.92 0.29 2.16 1.89 8.34

 MEAN 16.57 317.41 193.93 251.28 1083.36 0.29 2.24 1.97 6.35

 HUB 13.89 338.77 225.17 253.10 1081.82 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 368.33 305.41 175.99 0.28 3633.00 0.92 0.90

 MEAN 323.34 282.64 129.41 0.26 3215.55 0.92 0.90 0.90 1.58

 HUB 270.98 257.22 45.81 0.24 3128.75 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.08 6.41 504.44 1.02 496.45 479.26 0.58

 MEAN 6.74 1.07 6.35 503.13 1.02 495.03 478.53 0.61

 HUB 6.72 1.07 6.29 502.85 1.02 493.63 478.38 0.64

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.62 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 37.66 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.66 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 337.5070 195.0206 275.4596 1082.5686 0.3118 -0.0954 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7463 6.3122 494.3134 478.7225 0.6252 35.2978 32.4000 -2.8978

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 277.3774 62.2076 270.3117 1085.8176 0.2555 0.2497 2.2705

 

NASA/TM—2013-218094 O–202
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7450 6.4495 497.2859 478.7025 432.2457 0.0132 0.3932

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 275.1102 0.0000 275.1102 1085.9216 0.2533 0.3042 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4442 497.3864 478.6845 0.0000 0.0600 0.0395 0.2364

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8731 6.7344 1.0686 503.4713 10.4332 215.7059 1.6721

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64891.836 0.478 104.161 279739.000 0.615183E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.013 EfDer = 0.996 SH = 0.646304E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.404 2235.554 6.734 503.471 1.000 1.000 0.980

 W Kg/sec = 12.911 Wdry = 28.402 WH2O = 0.002 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.084 2269.112 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48239.906 22286.697 2.850 509.668 178.811 384.739 2.152

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 227.16 -0.08 227.16 0.21 0.39 362.76

 MEAN 15.91 0.00 -0.02 227.16 -0.08 227.16 0.21 0.35

 HUB 13.07 0.00 -0.02 227.16 -0.08 227.16 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.57 47.36 10.21 357.40 423.55 6.54 499.32 478.68 0.57

 MEAN 53.81 44.80 9.01 310.44 384.74 6.54 499.32 478.68 0.57

 HUB 48.31 38.84 9.47 254.98 341.55 6.54 499.32 478.68 0.57

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.78 179.48 240.12 1095.66 0.27 2.05 1.78 7.43

 MEAN 15.50 299.69 177.11 241.76 1094.05 0.27 2.13 1.86 5.75

 HUB 12.59 316.01 201.42 243.51 1092.46 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.99 294.50 170.51 0.27 3221.22 0.92 0.91

 MEAN 302.34 272.27 125.24 0.25 2745.96 0.92 0.91 0.91 1.56

 HUB 245.62 247.48 44.20 0.23 2536.84 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.19 1.07 6.83 513.58 1.02 506.35 484.21 0.46

 MEAN 7.12 1.06 6.77 512.08 1.02 504.86 483.42 0.48

 HUB 7.09 1.05 6.70 511.43 1.02 503.40 483.07 0.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.78 35.38 31.50 3.88 0.93 0.45 1.40

 MEAN 36.23 27.39 23.50 3.89 0.93 0.43 1.64

 HUB 39.60 10.29 6.50 3.79 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.8590 180.3536 274.9923 1092.7461 0.3009 -0.1778 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1280 6.6994 503.6685 483.5599 0.5011 33.2589 33.0000 -0.2589

 

NASA/TM—2013-218094 O–203
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 281.6812 64.3221 274.2389 1095.2546 0.2572 0.1233 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1267 6.8104 505.9839 483.5446 410.5396 0.0236 0.3651

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 274.0316 0.0000 274.0316 1095.6194 0.2501 0.2871 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8225 506.3254 483.5354 0.0000 0.0600 0.0366 0.1559

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 7.1218 1.0575 512.3621 8.8916 237.4342 1.8406

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55309.219 0.452 88.779 294074.031 0.669547E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1345 Tt4 = 512.3621 T1 = 451.6053

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 377868.56 606.5325 80.6848 1.4749 0.8416 15.3617 1.1345 37.3740

NASA/TM—2013-218094 O–204
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.847 EfDer = 0.967 SH = 0.800268E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.558 2121.632 5.592 461.414 1.000 1.000 0.980

 W Kg/sec = 14.799 Wdry = 32.556 WH2O = 0.003 lbm/sec H2O = 0.041g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.718 2249.476 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60557.699 25546.125 3.519 831.557 236.284 619.754 2.623

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.78 -0.06 174.78 0.17 0.40 404.96

 MEAN 17.06 0.00 -0.02 174.78 -0.06 174.78 0.17 0.35

 HUB 12.51 0.00 -0.02 174.78 -0.06 174.78 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.42 50.47 14.95 381.96 420.10 5.49 458.96 452.62 3.32

 MEAN 61.05 47.20 13.85 315.86 361.05 5.49 458.96 452.62 3.32

 HUB 52.97 38.62 14.35 231.62 290.21 5.49 458.96 452.62 3.32

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 347.43 254.36 236.66 1052.64 0.33 7.29 6.52 16.04

 MEAN 18.04 354.29 261.56 238.97 1050.42 0.34 7.43 6.80 12.53

 HUB 15.00 387.09 301.89 242.28 1047.58 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 381.96 268.87 127.60 0.26 5248.64 0.92 0.89

 MEAN 333.93 249.69 72.37 0.24 4718.49 0.92 0.89 0.89 1.65

 HUB 277.72 243.48 24.17 0.23 4529.14 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 477.04 1.03 467.34 463.68 2.48

 MEAN 6.16 1.10 5.70 475.46 1.03 465.37 462.62 2.67

 HUB 6.13 1.10 5.59 474.90 1.03 462.85 462.28 2.94

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.06 28.33 24.20 4.13 0.93 0.53 1.80

 MEAN 47.58 16.85 12.70 4.15 0.94 0.48 2.22

 HUB 51.25 -5.70 -9.30 3.60 0.94 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.967 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.7888 261.0498 256.2313 1050.0513 0.3484 -0.0424 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1673 5.6769 465.0422 462.8574 2.7148 45.5337 35.4000 -10.1337

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.8127 62.8242 249.0098 1056.1892 0.2432 0.4679 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1597 5.9146 470.4975 462.7751 554.9116 0.0258 0.5570

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.3782 0.0000 255.3782 1056.2473 0.2418 0.4489 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8971 470.5564 462.7498 0.0000 0.0600 0.0692 0.4318

NASA/TM—2013-218094 O–205
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8359 6.1387 1.0977 475.8000 14.3870 176.0046 1.3644

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89477.086 0.613 164.629 338683.875 0.854465E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.793 EfDer = 0.975 SH = 0.904918E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.558 2121.632 6.139 475.800 1.000 1.000 0.980

 W Kg/sec = 14.799 Wdry = 32.555 WH2O = 0.003 lbm/sec H2O = 0.049g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.672 2215.215 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57477.879 25546.021 2.701 590.487 218.589 468.502 2.143

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.62 -0.08 233.62 0.22 0.42 397.25

 MEAN 18.08 0.00 -0.02 233.62 -0.08 233.62 0.22 0.39

 HUB 15.21 0.00 -0.02 233.62 -0.08 233.62 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.46 46.36 12.10 380.48 446.54 5.94 471.41 462.76 2.30

 MEAN 55.09 42.30 12.79 334.71 408.24 5.94 471.41 462.76 2.30

 HUB 50.33 37.84 12.49 281.61 365.96 5.94 471.41 462.76 2.30

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.63 203.67 248.93 1066.65 0.30 2.33 2.04 9.02

 MEAN 18.01 324.00 205.22 250.72 1064.98 0.30 2.40 2.13 7.35

 HUB 15.22 346.29 236.76 252.70 1063.33 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.07 303.95 174.41 0.28 4160.50 0.92 0.89

 MEAN 333.45 281.60 128.23 0.26 3697.47 0.92 0.89 0.89 1.59

 HUB 281.85 256.69 45.09 0.24 3605.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.09 6.27 488.19 1.03 479.87 470.81 1.70

 MEAN 6.61 1.08 6.20 486.81 1.02 478.37 469.95 1.79

 HUB 6.60 1.07 6.14 486.53 1.02 476.89 469.80 1.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.29 35.02 31.50 3.52 0.93 0.48 1.40

 MEAN 39.30 27.09 23.50 3.59 0.94 0.46 1.63

 HUB 43.14 10.12 6.50 3.62 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 349.1887 205.7966 282.1001 1063.8613 0.3282 -0.1235 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6223 6.1521 477.3729 470.1964 1.8605 36.1114 30.6000 -5.5114

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 275.0253 58.3073 268.7735 1067.9998 0.2575 0.2878 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6196 6.3251 481.0946 470.1473 491.5697 0.0165 0.3961

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.6855 0.0000 284.6855 1067.5111 0.2667 0.2978 0.5911

NASA/TM—2013-218094 O–206
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2922 480.6599 470.1350 0.0000 0.0600 0.0468 0.2101

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8569 6.6067 1.0763 487.1754 11.3759 204.4742 1.5851

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 70758.695 0.495 130.189 309608.000 0.925147E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.356 EfDer = 0.990 SH = 0.951627E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.558 2121.632 6.607 487.175 1.000 1.000 0.980

 W Kg/sec = 14.799 Wdry = 32.555 WH2O = 0.003 lbm/sec H2O = 0.055g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.207 2189.200 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54733.125 25545.975 2.654 545.479 205.518 424.468 2.065

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.82 -0.08 240.82 0.23 0.41 383.41

 MEAN 17.74 0.00 -0.02 240.82 -0.08 240.82 0.23 0.38

 HUB 15.05 0.00 -0.02 240.82 -0.08 240.82 0.23 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.06 46.36 10.70 371.59 442.87 6.38 482.51 470.12 1.61

 MEAN 53.76 43.40 10.36 328.42 407.32 6.38 482.51 470.12 1.61

 HUB 49.17 38.84 10.33 278.65 368.35 6.38 482.51 470.12 1.61

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 317.05 186.41 256.46 1077.93 0.29 2.26 1.98 8.75

 MEAN 17.51 321.29 191.50 257.98 1076.58 0.30 2.34 2.07 6.78

 HUB 14.85 345.51 227.92 259.67 1075.25 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.78 313.53 180.36 0.29 3694.53 0.92 0.91

 MEAN 324.13 290.07 132.63 0.27 3354.00 0.92 0.91 0.91 1.53

 HUB 274.94 263.89 47.02 0.25 3385.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.11 1.08 6.70 498.17 1.02 490.09 476.83 1.25

 MEAN 7.06 1.07 6.64 497.16 1.02 488.86 476.24 1.30

 HUB 7.07 1.07 6.58 497.25 1.02 487.66 476.31 1.35

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.01 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.59 27.21 23.50 3.71 0.94 0.43 1.62

 HUB 41.27 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 348.0999 192.7577 289.8586 1075.3873 0.3237 -0.1338 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0749 6.5857 487.7880 476.4654 1.3504 33.6241 31.5000 -2.1241

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 287.2917 62.6708 280.3728 1078.8054 0.2663 0.2168 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0735 6.7376 490.8939 476.4293 451.3937 0.0132 0.3606

 

NASA/TM—2013-218094 O–207
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.8932 0.0000 291.8932 1078.5643 0.2706 0.2676 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7166 490.6795 476.4160 0.0000 0.0600 0.0382 0.1687

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8745 7.0626 1.0690 497.5285 10.3537 214.1171 1.6598

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64406.418 0.479 118.502 309785.125 0.972222E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.316 EfDer = 0.998 SH = 0.100093E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.558 2121.632 7.063 497.528 1.000 1.000 0.980

 W Kg/sec = 14.799 Wdry = 32.555 WH2O = 0.003 lbm/sec H2O = 0.060g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.369 2166.302 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52301.340 25545.926 2.642 513.330 194.287 395.845 2.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.53 -0.08 244.53 0.23 0.40 364.09

 MEAN 16.97 0.00 -0.02 244.53 -0.08 244.53 0.23 0.37

 HUB 14.32 0.00 -0.02 244.53 -0.08 244.53 0.23 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.57 46.36 9.21 356.59 432.45 6.82 492.72 476.40 1.19

 MEAN 52.12 43.80 8.32 314.21 398.21 6.82 492.72 476.40 1.19

 HUB 47.32 37.84 9.48 265.13 360.74 6.82 492.72 476.40 1.19

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 308.30 166.53 259.46 1087.94 0.28 2.16 1.89 8.34

 MEAN 16.57 312.64 172.44 260.79 1086.78 0.29 2.24 1.97 6.35

 HUB 13.89 335.70 209.57 262.25 1085.64 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.56 317.52 183.03 0.29 3145.67 0.92 0.91

 MEAN 306.86 293.39 134.42 0.27 2859.37 0.92 0.91 0.91 1.48

 HUB 257.17 266.54 47.60 0.25 2912.09 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.51 1.06 7.11 506.89 1.02 499.25 481.81 0.97

 MEAN 7.47 1.06 7.06 506.04 1.02 498.18 481.34 1.00

 HUB 7.48 1.06 7.00 506.20 1.02 497.14 481.44 1.03

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.69 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.47 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.63 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 334.4577 173.4062 285.9935 1085.8969 0.3080 -0.1080 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4827 7.0123 497.3841 481.5294 1.0281 31.2297 32.4000 1.1703

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 289.0483 64.8251 281.6854 1088.3778 0.2656 0.1646 2.2705

 

NASA/TM—2013-218094 O–208
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4817 7.1284 499.6599 481.5054 432.2457 0.0122 0.3299

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.6303 0.0000 286.6303 1088.4951 0.2633 0.2374 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1240 499.7716 481.4883 0.0000 0.0600 0.0371 0.1544

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.4711 1.0578 506.3752 8.8473 235.4862 1.8255

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55040.887 0.450 101.270 318937.031 0.102265E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.457 EfDer = 1.000 SH = 0.105491E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.558 2121.632 7.471 506.375 1.000 1.000 0.980

 W Kg/sec = 14.799 Wdry = 32.555 WH2O = 0.003 lbm/sec H2O = 0.066g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.296 2147.296 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 50216.844 25545.873 2.751 509.668 185.293 384.739 2.076

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.47 -0.08 236.47 0.22 0.38 343.28

 MEAN 15.91 0.00 -0.02 236.47 -0.08 236.47 0.22 0.35

 HUB 13.07 0.00 -0.02 236.47 -0.08 236.47 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.12 47.36 7.76 339.19 413.55 7.23 501.88 481.48 0.93

 MEAN 51.26 44.80 6.46 294.62 377.85 7.23 501.88 481.48 0.93

 HUB 45.67 38.84 6.83 241.99 338.40 7.23 501.88 481.48 0.93

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.46 153.42 251.34 1096.98 0.27 2.05 1.78 7.43

 MEAN 15.50 296.82 155.81 252.64 1095.78 0.27 2.13 1.86 5.75

 HUB 12.59 315.33 186.78 254.06 1094.59 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 332.15 308.41 178.73 0.28 2753.84 0.92 0.91

 MEAN 286.93 284.64 131.13 0.26 2415.94 0.92 0.91 0.91 1.46

 HUB 233.10 258.25 46.32 0.24 2352.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.88 1.05 7.50 514.57 1.02 507.60 486.00 0.78

 MEAN 7.83 1.05 7.44 513.57 1.01 506.48 485.46 0.81

 HUB 7.82 1.05 7.39 513.38 1.01 505.39 485.37 0.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.40 35.42 31.50 3.92 0.93 0.39 1.40

 MEAN 31.66 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.32 10.33 6.50 3.83 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.4128 158.6647 287.5421 1094.3456 0.3001 -0.1968 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8347 7.3661 505.1691 485.6094 0.8431 28.8898 33.0000 4.1102

 

NASA/TM—2013-218094 O–209
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.6235 67.5059 287.8128 1096.1260 0.2697 0.0171 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8318 7.4507 506.8135 485.5893 410.5396 0.0272 0.2991

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.5697 0.0000 287.5697 1096.5305 0.2623 0.2111 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4651 507.1909 485.5774 0.0000 0.0600 0.0424 0.0532

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 7.8257 1.0475 513.8374 7.4628 262.1428 2.0321

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46431.535 0.421 85.430 336209.719 0.107832E-03

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1136 Tt4 = 513.8374 T1 = 461.4136

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 326114.63 600.0198 80.7181 1.3994 0.8552 13.8473 1.1136 37.3740

NASA/TM—2013-218094 O–210
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.024 EfDer = 0.995 SH = 0.143364E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.182 6.513 472.323 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.059 WH2O = 0.006 lbm/sec H2O = 0.084g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.444 2044.727 1.381 0.249 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67332.570 32219.582 3.212 831.557 258.914 619.754 2.394

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 194.33 -0.07 194.33 0.18 0.38 368.10

 MEAN 17.06 0.00 -0.02 194.33 -0.07 194.33 0.18 0.33

 HUB 12.51 0.00 -0.02 194.33 -0.07 194.33 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.05 50.47 10.58 351.27 401.50 6.36 469.29 461.23 4.29

 MEAN 56.22 47.20 9.02 290.49 349.55 6.36 469.29 461.23 4.29

 HUB 47.63 38.62 9.01 213.01 288.39 6.36 469.29 461.23 4.29

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 337.80 208.37 265.88 1061.11 0.32 7.29 6.52 16.04

 MEAN 18.04 350.56 226.35 267.69 1059.66 0.33 7.43 6.80 12.53

 HUB 15.00 391.42 282.66 270.76 1057.41 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.27 301.85 142.91 0.28 4299.95 0.92 0.91 

 MEAN 307.10 279.60 80.75 0.26 4083.68 0.92 0.91 0.91 1.41

 HUB 255.41 272.13 27.25 0.26 4240.78 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.06 1.08 6.59 484.09 1.02 474.92 469.28 3.56

 MEAN 7.04 1.08 6.53 483.50 1.02 473.62 468.91 3.73

 HUB 7.06 1.08 6.43 483.93 1.02 471.62 469.25 4.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.09 28.26 24.20 4.06 0.93 0.39 1.80

 MEAN 40.22 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.23 -5.75 -9.30 3.55 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.4806 225.9149 287.2952 1059.0789 0.3451 -0.0601 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0473 6.4969 473.1054 469.1504 3.8147 38.1798 35.4000 -2.7798

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 290.1944 70.9904 281.3773 1063.5082 0.2729 0.3319 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0449 6.6942 477.0732 469.0620 554.9116 0.0145 0.4328

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 288.0711 0.0000 288.0711 1063.6115 0.2708 0.3447 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6866 477.1718 469.0469 0.0000 0.0600 0.0393 0.3178

NASA/TM—2013-218094 O–211
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8762 7.0316 1.0796 483.8418 11.5189 201.6011 1.5628

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71662.883 0.581 166.301 420892.781 0.149537E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.179 EfDer = 1.000 SH = 0.154933E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.182 7.032 483.842 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.058 WH2O = 0.006 lbm/sec H2O = 0.095g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.913 2020.246 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64752.371 32219.434 2.433 590.487 242.726 468.502 1.930

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 263.18 -0.09 263.18 0.25 0.41 362.29

 MEAN 18.08 0.00 -0.02 263.18 -0.09 263.18 0.25 0.38

 HUB 15.21 0.00 -0.02 263.18 -0.09 263.18 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.06 46.36 6.70 349.91 437.91 6.74 478.27 469.04 3.31

 MEAN 49.48 42.30 7.18 307.82 405.06 6.74 478.27 469.04 3.31

 HUB 44.55 37.84 6.71 258.98 369.30 6.74 478.27 469.04 3.31

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 320.26 148.82 283.58 1071.10 0.30 2.33 2.04 9.02

 MEAN 18.01 326.94 160.81 284.65 1070.29 0.31 2.40 2.13 7.35

 HUB 15.22 353.49 207.90 285.90 1069.49 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 347.70 346.37 198.88 0.32 3040.75 0.92 0.91

 MEAN 306.66 319.84 145.85 0.30 2897.79 0.92 0.91 0.91 1.37

 HUB 259.21 290.46 51.31 0.27 3166.22 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.44 1.06 7.00 492.16 1.02 483.92 474.37 2.73

 MEAN 7.42 1.06 6.96 491.77 1.02 483.18 474.13 2.80

 HUB 7.46 1.06 6.92 492.51 1.02 482.46 474.62 2.87

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.69 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.46 27.13 23.50 3.63 0.93 0.33 1.63

 HUB 36.02 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.2011 161.2596 320.9685 1068.7241 0.3361 -0.1650 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4353 6.8830 481.7785 474.3982 2.9373 26.6757 30.6000 3.9243

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 315.2218 66.8293 308.0562 1071.3660 0.2942 0.0920 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4329 7.0050 484.1623 474.3461 491.5697 0.0151 0.2521

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 326.4772 0.0000 326.4772 1070.7195 0.3049 0.1440 0.5911

NASA/TM—2013-218094 O–212
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9625 483.5818 474.3416 0.0000 0.0600 0.0419 0.0034

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8706 7.4200 1.0552 492.1482 8.3067 252.6154 1.9583

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 51684.289 0.428 119.939 387942.500 0.156938E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.265 EfDer = 0.994 SH = 0.159584E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.182 7.420 492.148 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.058 WH2O = 0.007 lbm/sec H2O = 0.101g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.245 2003.125 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62560.309 32219.375 2.351 545.479 231.988 424.468 1.830

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 275.25 -0.09 275.25 0.26 0.41 350.82

 MEAN 17.74 0.00 -0.02 275.25 -0.09 275.25 0.26 0.38

 HUB 15.05 0.00 -0.02 275.25 -0.09 275.25 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.16 46.36 4.80 341.74 438.88 7.09 486.06 474.30 2.59

 MEAN 47.67 43.40 4.27 302.04 408.72 7.09 486.06 474.30 2.59

 HUB 42.96 38.84 4.12 256.26 376.14 7.09 486.06 474.30 2.59

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 323.27 127.67 296.99 1078.54 0.30 2.26 1.98 8.75

 MEAN 17.51 330.77 144.31 297.63 1078.10 0.31 2.34 2.07 6.78

 HUB 14.85 358.20 198.06 298.46 1077.68 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.31 363.53 209.64 0.34 2531.06 0.92 0.91

 MEAN 298.09 335.01 153.78 0.31 2528.00 0.92 0.91 0.91 1.31

 HUB 252.86 303.45 54.79 0.28 2942.69 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.77 1.05 7.31 499.08 1.01 490.68 478.54 2.22

 MEAN 7.77 1.05 7.28 499.07 1.01 490.27 478.54 2.25

 HUB 7.83 1.05 7.26 500.20 1.02 489.89 479.24 2.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.26 35.22 31.50 3.72 0.93 0.27 1.40

 MEAN 25.87 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.57 10.40 6.50 3.90 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.3934 145.2538 335.2815 1076.3812 0.3395 -0.1777 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7842 7.1950 488.7182 478.7959 2.3687 23.4237 31.5000 8.0763

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 334.9804 73.0737 326.9130 1078.2666 0.3107 -0.0038 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7786 7.2815 490.4298 478.7549 451.3937 0.0211 0.2102

 

NASA/TM—2013-218094 O–213
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 340.8293 0.0000 340.8293 1077.9143 0.3162 0.0883 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2470 490.1122 478.7353 0.0000 0.0600 0.0580 -0.0720

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8384 7.7599 1.0458 499.4477 7.2998 273.5561 2.1206

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45422.605 0.399 105.408 390656.844 0.161491E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.675 EfDer = 0.973 SH = 0.164151E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.182 7.760 499.448 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.058 WH2O = 0.007 lbm/sec H2O = 0.107g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.333 1988.433 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60809.891 32219.318 2.297 513.330 223.468 395.845 1.771 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 284.31 -0.10 284.31 0.26 0.40 334.20

 MEAN 16.97 0.00 -0.02 284.31 -0.10 284.31 0.26 0.38

 HUB 14.32 0.00 -0.02 284.31 -0.10 284.31 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.09 46.36 2.73 327.95 434.10 7.40 492.95 478.69 2.10

 MEAN 45.48 43.80 1.68 288.96 405.45 7.40 492.95 478.69 2.10

 HUB 40.63 37.84 2.79 243.83 374.61 7.40 492.95 478.69 2.10

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.36 104.34 306.06 1084.85 0.30 2.16 1.89 8.34

 MEAN 16.57 330.18 123.07 306.38 1084.66 0.30 2.24 1.97 6.35

 HUB 13.89 355.69 179.74 306.93 1084.49 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.47 375.26 217.13 0.35 1971.84 0.92 0.89

 MEAN 282.21 345.24 159.13 0.32 2041.46 0.92 0.89 0.89 1.26

 HUB 236.51 312.14 56.77 0.29 2497.96 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.03 1.04 7.56 504.84 1.01 496.44 481.86 1.87

 MEAN 8.04 1.04 7.55 505.03 1.01 496.27 481.97 1.88

 HUB 8.11 1.04 7.53 506.28 1.01 496.12 482.71 1.89

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.82 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 21.89 27.45 23.50 3.95 0.91 0.24 1.62

 HUB 30.35 10.48 6.50 3.98 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.8385 123.7652 336.8193 1083.3096 0.3312 -0.1450 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0567 7.4747 495.0397 482.1978 1.9608 20.1760 32.4000 12.2240

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 343.2986 76.9919 334.5537 1084.2703 0.3166 -0.0658 2.2705

 

NASA/TM—2013-218094 O–214
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0468 7.5135 495.9164 482.1674 432.2457 0.0292 0.1739

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 341.0775 0.0000 341.0775 1084.4022 0.3145 0.0346 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4948 496.0384 482.1255 0.0000 0.0600 0.0822 -0.1023

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7669 8.0195 1.0335 505.3870 5.9397 314.7934 2.4403

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 36961.523 0.358 85.773 404697.938 0.166070E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.728 EfDer = 0.938 SH = 0.168891E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.182 8.020 505.387 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.058 WH2O = 0.007 lbm/sec H2O = 0.112g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.300 1976.714 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59455.668 32219.258 2.343 509.668 217.518 384.739 1.769

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 279.97 -0.10 279.97 0.26 0.39 316.01

 MEAN 15.91 0.00 -0.02 279.97 -0.10 279.97 0.26 0.36

 HUB 13.07 0.00 -0.02 279.97 -0.10 279.97 0.26 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.10 47.36 0.74 311.94 419.23 7.66 499.09 482.08 1.75

 MEAN 44.07 44.80 -0.73 270.96 389.68 7.66 499.09 482.08 1.75

 HUB 38.49 38.84 -0.35 222.55 357.71 7.66 499.09 482.08 1.75

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.94 89.05 302.09 1090.67 0.29 2.05 1.78 7.43

 MEAN 15.50 320.25 105.45 302.39 1090.48 0.29 2.13 1.86 5.75

 HUB 12.59 341.60 157.84 302.95 1090.30 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 305.47 371.61 216.41 0.34 1599.41 0.92 0.86

 MEAN 263.88 341.38 158.43 0.31 1635.76 0.92 0.86 0.86 1.23

 HUB 214.37 308.18 56.53 0.28 1988.51 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.24 1.03 7.78 509.76 1.01 501.79 484.56 1.61

 MEAN 8.24 1.03 7.77 509.86 1.01 501.62 484.62 1.62

 HUB 8.29 1.03 7.75 510.83 1.01 501.45 485.17 1.63

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.43 35.62 31.50 4.12 0.93 0.19 1.40

 MEAN 19.22 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.52 10.57 6.50 4.07 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.938 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.8074 107.3836 345.5045 1088.3141 0.3324 -0.2500 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2475 7.6476 499.6328 484.8044 1.7231 17.2654 33.0000 15.7346

 

NASA/TM—2013-218094 O–215
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 358.9940 81.9766 349.5090 1088.4951 0.3298 -0.2782 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2205 7.6316 499.7955 484.7602 410.5396 0.0752 0.1421

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 349.2418 0.0000 349.2418 1089.0994 0.3207 0.0015 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6485 500.3503 484.7290 0.0000 0.0600 0.1055 -0.2436

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6735 8.2057 1.0232 510.1514 4.7648 367.2036 2.8465

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 29652.002 0.318 68.811 428747.406 0.170934E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0801 Tt4 = 510.1514 T1 = 472.3232

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 235383.31 546.2313 88.4438 1.2599 0.8218 9.0242 1.0801 37.3740

NASA/TM—2013-218094 O–216
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.395 EfDer = 0.998 SH = 0.285462E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.407 7.939 487.555 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.856 WH2O = 0.015 lbm/sec H2O = 0.198g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 91.317 1848.769 1.381 0.249 53.358 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 70721.133 39910.879 3.110 831.557 267.358 619.754 2.318

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 204.11 -0.07 204.11 0.19 0.36 332.83

 MEAN 17.06 0.00 -0.02 204.11 -0.07 204.11 0.19 0.31

 HUB 12.51 0.00 -0.02 204.11 -0.07 204.11 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.69 50.47 7.22 322.69 381.88 7.74 484.21 472.76 5.45

 MEAN 52.60 47.20 5.40 266.85 336.02 7.74 484.21 472.76 5.45

 HUB 43.80 38.62 5.18 195.68 282.81 7.74 484.21 472.76 5.45

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.80 170.75 282.16 1075.20 0.31 7.29 6.52 16.04

 MEAN 18.04 344.71 196.34 283.32 1074.36 0.32 7.43 6.80 12.53

 HUB 15.00 388.55 263.11 285.91 1072.63 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.69 320.46 151.94 0.30 3524.06 0.92 0.91

 MEAN 282.11 296.02 85.77 0.28 3542.39 0.92 0.91 0.91 1.27

 HUB 234.63 287.32 28.48 0.27 3947.46 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.90 496.41 1.02 487.67 478.51 4.90

 MEAN 8.43 1.06 7.86 496.46 1.02 486.91 478.57 5.03

 HUB 8.49 1.07 7.76 497.47 1.02 485.35 479.29 5.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.18 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 34.72 16.84 12.70 4.14 0.92 0.25 2.22

 HUB 42.62 -5.69 -9.30 3.61 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.8986 195.9587 304.2545 1073.6359 0.3371 -0.0744 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4420 7.8116 486.2603 478.7998 5.1500 32.7840 35.4000 2.6160

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 309.3628 75.6796 299.9633 1076.7568 0.2873 0.2231 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4396 7.9756 489.0931 478.6949 554.9116 0.0141 0.3451

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 307.0494 0.0000 307.0494 1076.8777 0.2851 0.2481 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9680 489.2078 478.6761 0.0000 0.0600 0.0390 0.2108

NASA/TM—2013-218094 O–217
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8717 8.4244 1.0611 496.7807 9.2258 224.0747 1.7370

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57433.105 0.552 165.104 509677.063 0.292932E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 2.959 EfDer = 0.985 SH = 0.299217E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.407 8.424 496.781 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.855 WH2O = 0.015 lbm/sec H2O = 0.213g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.869 1831.523 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68969.898 39910.664 2.322 590.487 254.336 468.502 1.842 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 280.32 -0.10 280.32 0.26 0.40 328.44

 MEAN 18.08 0.00 -0.02 280.32 -0.10 280.32 0.26 0.37

 HUB 15.21 0.00 -0.02 280.32 -0.10 280.32 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.92 46.36 2.56 321.44 426.57 8.04 490.47 478.65 4.59

 MEAN 45.26 42.30 2.96 282.77 398.24 8.04 490.47 478.65 4.59

 HUB 40.33 37.84 2.49 237.91 367.73 8.04 490.47 478.65 4.59

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.96 104.34 305.64 1081.87 0.30 2.33 2.04 9.02

 MEAN 18.01 330.16 124.29 305.87 1081.76 0.31 2.40 2.13 7.35

 HUB 15.22 356.58 182.51 306.33 1081.65 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.40 373.72 215.06 0.35 2132.61 0.92 0.90

 MEAN 281.71 344.00 157.41 0.32 2240.27 0.92 0.90 0.90 1.24

 HUB 238.11 311.34 55.60 0.29 2779.88 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.21 502.14 1.01 493.76 481.94 4.12

 MEAN 8.74 1.04 8.20 502.41 1.01 493.65 482.11 4.13

 HUB 8.82 1.05 8.19 503.77 1.01 493.55 482.95 4.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.85 35.13 31.50 3.63 0.93 0.21 1.40

 MEAN 22.11 27.23 23.50 3.73 0.91 0.23 1.63

 HUB 30.79 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 367.2188 124.6425 345.4185 1079.8727 0.3401 -0.1955 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7557 8.0909 491.9405 482.3877 4.3696 19.8417 30.6000 10.7583

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 341.2077 72.3385 333.4514 1081.4988 0.3155 -0.0500 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7464 8.1708 493.4204 482.3230 491.5697 0.0266 0.1575

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 354.0768 0.0000 354.0768 1080.7083 0.3276 0.0189 0.5911

NASA/TM—2013-218094 O–218
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1035 492.7018 482.3155 0.0000 0.0600 0.0730 -0.1696

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7932 8.7203 1.0351 502.7715 5.9910 305.8755 2.3711

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37299.227 0.366 107.225 472679.750 0.301475E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.420 EfDer = 0.943 SH = 0.304381E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.407 8.720 502.771 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.855 WH2O = 0.015 lbm/sec H2O = 0.220g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.426 1820.579 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67697.500 39910.586 2.207 545.479 247.185 424.468 1.717

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 297.86 -0.10 297.86 0.27 0.40 318.85

 MEAN 17.74 0.00 -0.02 297.86 -0.10 297.86 0.27 0.38

 HUB 15.05 0.00 -0.02 297.86 -0.10 297.86 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.51 46.36 0.15 313.93 432.82 8.28 495.65 482.23 3.90

 MEAN 42.98 43.40 -0.42 277.46 407.14 8.28 495.65 482.23 3.90

 HUB 38.33 38.84 -0.51 235.41 379.71 8.28 495.65 482.23 3.90

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.12 78.95 325.69 1086.16 0.31 2.26 1.98 8.75

 MEAN 17.51 341.80 104.73 325.36 1086.50 0.31 2.34 2.07 6.78

 HUB 14.85 367.90 171.67 325.40 1086.84 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 309.86 399.24 230.92 0.37 1565.96 0.92 0.86

 MEAN 273.83 366.68 169.10 0.34 1835.29 0.92 0.86 0.86 1.18

 HUB 232.28 331.00 60.61 0.30 2550.80 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.94 1.02 8.37 506.71 1.01 497.69 484.56 3.66

 MEAN 8.97 1.03 8.39 507.38 1.01 498.00 484.96 3.62

 HUB 9.07 1.04 8.39 509.18 1.01 498.31 486.02 3.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.63 35.34 31.50 3.84 0.93 0.14 1.40

 MEAN 17.84 27.46 23.50 3.96 0.90 0.18 1.62

 HUB 27.81 10.55 6.50 4.05 0.90 0.24 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.943 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 382.1664 105.4175 367.3394 1084.3396 0.3524 -0.2100 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9880 8.2576 496.0262 485.2428 3.8521 16.0122 31.5000 15.4878

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 369.3477 80.5707 360.4526 1085.1892 0.3404 -0.1554 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9701 8.2879 496.7997 485.1917 451.3937 0.0392 0.1133

 

NASA/TM—2013-218094 O–219
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 376.8034 0.0000 376.8034 1084.6998 0.3474 -0.0453 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2245 496.3528 485.1547 0.0000 0.0600 0.1039 -0.2591

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6650 8.9306 1.0241 507.7563 4.9850 347.8241 2.6963

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31037.631 0.323 89.225 478580.594 0.306566E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.510 EfDer = 0.883 SH = 0.309443E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.407 8.931 507.756 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.855 WH2O = 0.016 lbm/sec H2O = 0.226g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.846 1811.620 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66999.406 39910.504 2.116 513.330 242.560 395.845 1.632

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 313.25 -0.11 313.25 0.29 0.40 304.48

 MEAN 16.97 0.00 -0.02 313.25 -0.11 313.25 0.29 0.38

 HUB 14.32 0.00 -0.02 313.25 -0.11 313.25 0.29 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.89 46.36 -2.47 301.26 434.68 8.44 499.88 485.05 3.43

 MEAN 40.29 43.80 -3.51 265.45 410.66 8.44 499.88 485.05 3.43

 HUB 35.58 37.84 -2.26 223.99 385.15 8.44 499.88 485.05 3.43

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.75 51.55 341.89 1089.33 0.32 2.16 1.89 8.34

 MEAN 16.57 350.61 80.89 341.15 1090.04 0.32 2.24 1.97 6.35

 HUB 13.89 373.76 153.16 340.94 1090.72 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.32 419.89 243.77 0.39 975.29 0.92 0.81

 MEAN 259.24 384.96 178.36 0.35 1342.45 0.92 0.81 0.81 1.13

 HUB 217.26 346.91 64.11 0.32 2128.88 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.06 1.01 8.45 510.21 1.00 500.61 486.47 3.35

 MEAN 9.11 1.02 8.48 511.13 1.01 501.26 486.99 3.28

 HUB 9.21 1.03 8.50 513.11 1.01 501.89 488.11 3.20

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.57 35.49 31.50 3.99 0.93 0.08 1.40

 MEAN 13.34 27.60 23.50 4.10 0.89 0.12 1.62

 HUB 24.19 10.65 6.50 4.15 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.883 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 384.6544 81.3421 375.9554 1088.2306 0.3535 -0.1724 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1177 8.3727 499.5972 487.2399 3.4506 12.2084 32.4000 20.1916

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 385.7287 86.5077 375.9030 1088.1622 0.3545 -0.2086 2.2705

 

NASA/TM—2013-218094 O–220
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0919 8.3449 499.5305 487.2065 432.2457 0.0501 0.0773

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 384.2361 0.0000 384.2361 1088.2634 0.3531 -0.0951 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3018 499.6227 487.1301 0.0000 0.0600 0.1323 -0.2754

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4538 9.0389 1.0121 511.4801 3.7240 430.6164 3.3381

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23187.092 0.266 66.657 498555.781 0.311606E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.382 EfDer = 0.820 SH = 0.314625E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.407 9.039 511.480 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.854 WH2O = 0.016 lbm/sec H2O = 0.231g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.153 1805.014 1.381 0.249 53.358 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66675.250 39910.422 2.119 509.668 240.533 384.739 1.600

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 313.97 -0.11 313.97 0.29 0.39 288.56

 MEAN 15.91 0.00 -0.02 313.97 -0.11 313.97 0.29 0.37

 HUB 13.07 0.00 -0.02 313.97 -0.11 313.97 0.29 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.40 47.36 -4.96 286.56 425.15 8.54 503.56 487.01 3.06

 MEAN 38.42 44.80 -6.38 248.91 400.73 8.54 503.56 487.01 3.06

 HUB 33.08 38.84 -5.76 204.44 374.72 8.54 503.56 487.01 3.06

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 344.85 33.39 343.23 1092.40 0.32 2.05 1.78 7.43

 MEAN 15.50 348.00 61.74 342.48 1093.19 0.32 2.13 1.86 5.75

 HUB 12.59 366.90 132.04 342.32 1093.93 0.34 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.61 423.00 247.23 0.39 600.92 0.92 0.75

 MEAN 242.41 387.21 180.67 0.35 958.50 0.92 0.75 0.75 1.10

 HUB 196.93 348.41 64.89 0.32 1663.77 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.11 1.01 8.51 512.99 1.00 503.44 487.88 3.07

 MEAN 9.16 1.01 8.54 513.89 1.00 504.16 488.37 3.00

 HUB 9.24 1.02 8.56 515.66 1.01 504.85 489.35 2.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.56 35.76 31.50 4.26 0.93 0.03 1.40

 MEAN 10.22 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.09 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.820 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 397.9093 62.8693 392.9112 1090.2577 0.3650 -0.2853 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1568 8.3619 501.4636 488.6062 3.2593 9.0908 33.0000 23.9092

 

NASA/TM—2013-218094 O–221
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 411.8700 94.0509 400.9879 1089.2764 0.3781 -0.4489 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0976 8.2534 500.5551 488.5530 410.5396 0.1137 0.0508

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 400.4403 0.0000 400.4403 1090.0905 0.3673 -0.1033 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2798 501.3005 488.4997 0.0000 0.0600 0.1453 -0.4071

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2234 9.0776 1.0043 514.1791 2.6993 546.8223 4.2389

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 16807.424 0.213 48.317 530684.063 0.316846E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0546 Tt4 = 514.1791 T1 = 487.5552

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 165764.47 476.5276 91.3174 1.1434 0.6893 5.3951 1.0546 37.3740

NASA/TM—2013-218094 O–222
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.466 EfDer = 1.000 SH = 0.480206E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.710 1582.167 9.337 500.813 1.000 1.000 0.980

 W Kg/sec = 22.595 Wdry = 49.686 WH2O = 0.024 lbm/sec H2O = 0.383g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.899 1610.175 1.380 0.249 53.364 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60040.625 38997.648 3.693 831.557 225.177 619.754 2.752

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.29 -0.06 173.29 0.16 0.31 289.87

 MEAN 17.06 0.00 -0.02 173.29 -0.06 173.29 0.16 0.27

 HUB 12.51 0.00 -0.02 173.29 -0.06 173.29 0.16 0.23

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.69 50.47 8.22 284.84 333.46 9.18 498.40 482.36 6.12

 MEAN 53.67 47.20 6.47 235.55 292.47 9.18 498.40 482.36 6.12

 HUB 44.92 38.62 6.30 172.73 244.71 9.18 498.40 482.36 6.12

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 286.13 155.80 239.99 1090.11 0.26 7.29 6.52 16.04

 MEAN 18.04 298.46 176.32 240.80 1089.40 0.27 7.43 6.80 12.53

 HUB 15.00 335.12 231.35 242.45 1088.07 0.31 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 284.84 272.48 129.04 0.25 3215.33 0.92 0.91

 MEAN 249.02 251.54 72.70 0.23 3181.21 0.92 0.91 0.91 1.30

 HUB 207.11 243.66 24.25 0.22 3471.05 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.33 507.94 1.01 501.37 486.78 5.63

 MEAN 9.78 1.05 9.29 507.86 1.01 500.71 486.76 5.75

 HUB 9.82 1.05 9.20 508.51 1.02 499.49 487.23 5.97

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.99 28.27 24.20 4.07 0.93 0.31 1.80

 MEAN 36.21 16.80 12.70 4.10 0.93 0.28 2.22

 HUB 43.66 -5.71 -9.30 3.59 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 312.4942 175.9819 258.2306 1088.9086 0.2870 -0.0701 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7911 9.2541 500.2648 486.9299 5.8338 34.2741 35.4000 1.1259

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 263.3908 64.4334 255.3881 1091.3743 0.2413 0.2503 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7904 9.4067 502.5345 486.8222 554.9116 0.0114 0.3650

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.3514 0.0000 261.3514 1091.4628 0.2395 0.2711 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.3997 502.6204 486.8069 0.0000 0.0600 0.0370 0.2369

NASA/TM—2013-218094 O–223
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8771 9.7770 1.0471 508.1025 7.2902 217.3152 1.6846

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45420.363 0.560 127.593 485533.563 0.490412E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.941 EfDer = 0.992 SH = 0.498929E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.710 1582.167 9.777 508.103 1.000 1.000 0.980

 W Kg/sec = 22.595 Wdry = 49.685 WH2O = 0.025 lbm/sec H2O = 0.406g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.973 1598.581 1.380 0.249 53.364 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58828.102 38997.359 2.726 590.487 216.611 468.502 2.163

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 239.10 -0.08 239.10 0.22 0.34 286.67

 MEAN 18.08 0.00 -0.02 239.10 -0.08 239.10 0.22 0.32

 HUB 15.21 0.00 -0.02 239.10 -0.08 239.10 0.22 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.89 46.36 3.53 283.73 371.11 9.46 503.51 486.79 5.38

 MEAN 46.24 42.30 3.94 249.61 345.71 9.46 503.51 486.79 5.38

 HUB 41.30 37.84 3.46 210.00 318.29 9.46 503.51 486.79 5.38

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 279.17 98.39 261.26 1095.45 0.25 2.33 2.04 9.02

 MEAN 18.01 285.41 114.33 261.51 1095.26 0.26 2.40 2.13 7.35

 HUB 15.22 308.39 162.84 261.89 1095.09 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 281.94 319.29 183.55 0.29 2010.72 0.92 0.91

 MEAN 248.66 294.00 134.34 0.27 2060.49 0.92 0.91 0.91 1.27

 HUB 210.18 266.14 47.35 0.24 2480.09 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.06 1.03 9.62 512.56 1.01 506.30 489.41 4.94

 MEAN 10.07 1.03 9.61 512.67 1.01 506.13 489.49 4.97

 HUB 10.13 1.04 9.59 513.60 1.01 505.97 490.06 4.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 20.64 35.09 31.50 3.59 0.93 0.23 1.40

 MEAN 23.61 27.19 23.50 3.69 0.92 0.25 1.63

 HUB 31.87 10.25 6.50 3.75 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 315.9296 114.6465 294.3937 1093.9612 0.2888 -0.1855 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0825 9.5228 504.9318 489.7029 5.1520 21.2776 30.6000 9.3224

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 291.0976 61.7148 284.4804 1095.2732 0.2658 -0.0179 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0778 9.6013 506.1415 489.6407 491.5697 0.0200 0.1761

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 301.4290 0.0000 301.4290 1094.7389 0.2753 0.0438 0.5911

NASA/TM—2013-218094 O–224
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5474 505.6502 489.6387 0.0000 0.0600 0.0646 -0.1310

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8185 10.0565 1.0286 512.9421 4.8396 292.4637 2.2672

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30155.584 0.379 84.712 449813.875 0.501972E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.477 EfDer = 0.957 SH = 0.505905E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.710 1582.167 10.056 512.942 1.000 1.000 0.980

 W Kg/sec = 22.595 Wdry = 49.685 WH2O = 0.025 lbm/sec H2O = 0.418g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.259 1591.022 1.380 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57911.512 38997.254 2.578 545.479 211.594 424.468 2.006

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 254.80 -0.09 254.80 0.23 0.34 278.65

 MEAN 17.74 0.00 -0.02 254.80 -0.09 254.80 0.23 0.32

 HUB 15.05 0.00 -0.02 254.80 -0.09 254.80 0.23 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.41 46.36 1.05 277.11 376.51 9.69 507.73 489.56 4.76

 MEAN 43.88 43.40 0.48 244.92 353.48 9.69 507.73 489.56 4.76

 HUB 39.21 38.84 0.37 207.80 328.84 9.69 507.73 489.56 4.76

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 288.90 76.17 278.68 1098.99 0.26 2.26 1.98 8.75

 MEAN 17.51 295.04 97.17 278.58 1099.14 0.27 2.34 2.07 6.78

 HUB 14.85 318.10 153.38 278.68 1099.30 0.29 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 273.52 341.48 197.35 0.31 1510.70 0.92 0.88

 MEAN 241.71 313.85 144.54 0.29 1702.66 0.92 0.88 0.88 1.20

 HUB 205.03 283.43 51.65 0.26 2279.01 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.27 1.02 9.79 516.29 1.01 509.59 491.48 4.50

 MEAN 10.29 1.02 9.80 516.72 1.01 509.73 491.72 4.48

 HUB 10.37 1.03 9.80 517.99 1.01 509.87 492.47 4.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 15.29 35.30 31.50 3.80 0.93 0.16 1.40

 MEAN 19.23 27.42 23.50 3.92 0.90 0.20 1.62

 HUB 28.83 10.50 6.50 4.00 0.90 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 328.3019 97.8074 313.3941 1097.6493 0.2991 -0.1996 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3065 9.6944 508.3495 491.9494 4.6733 17.3327 31.5000 14.1673

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 314.9732 68.7093 307.3877 1098.3950 0.2868 -0.1221 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2959 9.7321 509.0375 491.9045 451.3937 0.0304 0.1304

 

NASA/TM—2013-218094 O–225
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 320.6797 0.0000 320.6797 1098.0795 0.2920 -0.0227 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6805 508.7464 491.8766 0.0000 0.0600 0.0950 -0.2221

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7088 10.2626 1.0205 516.9990 4.0571 331.1993 2.5674

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25281.209 0.338 71.019 455880.500 0.508749E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.639 EfDer = 0.902 SH = 0.512608E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.710 1582.167 10.263 516.999 1.000 1.000 0.980

 W Kg/sec = 22.595 Wdry = 49.685 WH2O = 0.025 lbm/sec H2O = 0.428g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.087 1584.767 1.380 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57350.238 38997.156 2.466 513.330 208.165 395.845 1.902

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 268.13 -0.09 268.13 0.24 0.34 266.35

 MEAN 16.97 0.00 -0.02 268.13 -0.09 268.13 0.24 0.32

 HUB 14.32 0.00 -0.02 268.13 -0.09 268.13 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.77 46.36 -1.59 265.92 377.70 9.85 511.23 491.78 4.31

 MEAN 41.16 43.80 -2.64 234.31 356.15 9.85 511.23 491.78 4.31

 HUB 36.42 37.84 -1.42 197.72 333.20 9.85 511.23 491.78 4.31

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 296.91 52.51 292.23 1101.71 0.27 2.16 1.89 8.34

 MEAN 16.57 301.73 76.45 291.88 1102.12 0.27 2.24 1.97 6.35

 HUB 13.89 322.41 137.07 291.82 1102.53 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 260.68 358.80 208.17 0.33 993.12 0.92 0.82

 MEAN 228.84 329.26 152.38 0.30 1268.72 0.92 0.82 0.82 1.15

 HUB 191.78 296.90 54.71 0.27 1905.27 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.39 1.01 9.89 519.20 1.00 512.13 493.02 4.19

 MEAN 10.43 1.02 9.91 519.81 1.01 512.50 493.36 4.14

 HUB 10.52 1.02 9.92 521.22 1.01 512.88 494.15 4.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.19 35.46 31.50 3.96 0.93 0.10 1.40

 MEAN 14.68 27.57 23.50 4.07 0.89 0.14 1.62

 HUB 25.16 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.902 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 329.7492 76.8848 320.6607 1100.8795 0.2995 -0.1641 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4413 9.8195 511.3513 493.5552 4.2885 13.4833 32.4000 18.9167

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 328.3388 73.6368 319.9750 1100.9626 0.2982 -0.1769 2.2705

 

NASA/TM—2013-218094 O–226
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4249 9.8093 511.4256 493.5310 432.2457 0.0403 0.0936

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 326.6136 0.0000 326.6136 1101.0605 0.2966 -0.0762 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7721 511.5163 493.4676 0.0000 0.0600 0.1255 -0.2454

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5221 10.3788 1.0113 520.0768 3.0780 405.4368 3.1429

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 19180.783 0.282 53.882 475180.688 0.515355E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.506 EfDer = 0.839 SH = 0.519332E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.710 1582.167 10.379 520.077 1.000 1.000 0.980

 W Kg/sec = 22.595 Wdry = 49.684 WH2O = 0.026 lbm/sec H2O = 0.436g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.500 1580.071 1.380 0.249 53.365 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57041.832 38997.051 2.469 509.668 206.447 384.739 1.864

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 268.61 -0.09 268.61 0.24 0.33 252.60

 MEAN 15.91 0.00 -0.02 268.61 -0.09 268.61 0.24 0.31

 HUB 13.07 0.00 -0.02 268.61 -0.09 268.61 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.29 47.36 -4.07 252.94 369.02 9.97 514.29 493.36 3.95

 MEAN 39.29 44.80 -5.51 219.71 347.08 9.97 514.29 493.36 3.95

 HUB 33.91 38.84 -4.93 180.46 323.65 9.97 514.29 493.36 3.95

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 295.28 36.84 292.97 1104.31 0.27 2.05 1.78 7.43

 MEAN 15.50 298.65 59.76 292.61 1104.77 0.27 2.13 1.86 5.75

 HUB 12.59 315.68 118.53 292.58 1105.21 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 247.70 360.96 210.86 0.33 662.63 0.92 0.77

 MEAN 213.98 330.76 154.21 0.30 927.64 0.92 0.77 0.77 1.12

 HUB 173.83 297.76 55.30 0.27 1493.51 0.92 0.77

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.46 1.01 9.96 521.55 1.00 514.55 494.18 3.92

 MEAN 10.49 1.01 9.98 522.13 1.00 514.97 494.49 3.86

 HUB 10.56 1.02 9.99 523.39 1.01 515.39 495.18 3.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.17 35.74 31.50 4.24 0.93 0.06 1.40

 MEAN 11.54 27.79 23.50 4.29 0.87 0.10 1.64

 HUB 22.05 10.70 6.50 4.20 0.87 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.839 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.5083 60.8576 334.0093 1102.7614 0.3079 -0.2727 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4955 9.8366 513.1051 494.6881 4.0802 10.3262 33.0000 22.6738

 

NASA/TM—2013-218094 O–227
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 348.3787 79.5526 339.1741 1102.2400 0.3161 -0.3988 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4563 9.7660 512.6152 494.6588 410.5396 0.0940 0.0656

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 339.2462 0.0000 339.2462 1102.7836 0.3076 -0.0906 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7768 513.1190 494.6032 0.0000 0.0600 0.1424 -0.3783

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3140 10.4307 1.0050 522.3544 2.2777 506.7790 3.9285

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14194.210 0.231 39.874 506347.438 0.522120E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0430 Tt4 = 522.3544 T1 = 500.8125 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 134232.14 377.0799 76.8988 1.1171 0.7204 6.4662 1.0430 37.3740

NASA/TM—2013-218094 O–228
 50μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.098 EfDer = 0.958 SH = 0.105546E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.369 2465.203 4.265 477.915 1.000 1.000 0.980

 W Kg/sec = 11.986 Wdry = 26.367 WH2O = 0.003 lbm/sec H2O = 0.040g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.249 2568.224 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66781.359 20689.877 3.256 831.557 255.398 619.754 2.427 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 192.74 -0.07 192.74 0.18 0.46 462.35

 MEAN 17.06 0.00 -0.02 192.74 -0.07 192.74 0.18 0.39

 HUB 12.51 0.00 -0.02 192.74 -0.07 192.74 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.53 50.47 16.06 443.81 483.92 4.17 474.93 460.68 1.61

 MEAN 62.30 47.20 15.10 367.01 414.60 4.17 474.93 460.68 1.61

 HUB 54.40 38.62 15.78 269.13 331.08 4.17 474.93 460.68 1.61

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 398.80 304.13 257.97 1074.42 0.37 7.29 6.52 16.04

 MEAN 18.04 404.25 308.40 261.36 1071.30 0.38 7.43 6.80 12.53

 HUB 15.00 438.81 348.93 266.09 1067.45 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 443.81 293.36 139.69 0.27 6275.51 0.92 0.88

 MEAN 388.01 273.22 79.61 0.26 5563.44 0.92 0.88 0.88 1.74

 HUB 322.69 267.38 26.23 0.25 5234.73 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 499.63 1.05 486.84 473.19 1.11

 MEAN 4.84 1.13 4.39 497.16 1.04 484.02 471.88 1.23

 HUB 4.80 1.13 4.28 496.03 1.04 480.54 471.30 1.39

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.69 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.72 16.94 12.70 4.24 0.95 0.51 2.22

 HUB 52.67 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 416.3300 307.8007 280.3380 1070.9047 0.3888 -0.0371 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8446 4.3708 483.6684 472.1181 1.2516 47.6734 35.4000 -12.2734

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 278.2403 68.0661 269.7863 1079.4044 0.2578 0.5067 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8332 4.6177 491.3810 471.9942 554.9116 0.0344 0.5989

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 277.0504 0.0000 277.0504 1079.4501 0.2567 0.4793 1.3089

NASA/TM—2013-218094 O–229
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5979 491.4340 471.9433 0.0000 0.0600 0.0825 0.4646

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8207 4.8106 1.1280 497.6056 19.6912 169.7270 1.3157

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 122454.984 0.622 182.477 267739.344 0.117223E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.632 EfDer = 0.961 SH = 0.128656E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.369 2465.203 4.811 497.605 1.000 1.000 0.980

 W Kg/sec = 11.986 Wdry = 26.366 WH2O = 0.003 lbm/sec H2O = 0.052g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.923 2516.912 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62316.125 20689.689 2.556 590.487 231.033 468.502 2.028

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 253.28 -0.09 253.28 0.23 0.47 451.35

 MEAN 18.08 0.00 -0.02 253.28 -0.09 253.28 0.23 0.43

 HUB 15.21 0.00 -0.02 253.28 -0.09 253.28 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.20 46.36 13.84 442.09 509.58 4.63 492.45 471.96 1.05

 MEAN 56.93 42.30 14.63 388.92 464.19 4.63 492.45 471.96 1.05

 HUB 52.27 37.84 14.43 327.21 413.85 4.63 492.45 471.96 1.05

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 366.90 252.02 266.64 1093.80 0.34 2.33 2.04 9.02

 MEAN 18.01 367.03 249.35 269.32 1091.33 0.34 2.40 2.13 7.35

 HUB 15.22 389.61 278.66 272.30 1088.90 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 439.29 325.84 187.28 0.30 5148.03 0.92 0.88

 MEAN 387.45 302.66 138.10 0.28 4492.37 0.92 0.88 0.88 1.69

 HUB 327.49 276.64 48.84 0.25 4243.29 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 515.41 1.04 504.59 481.15 0.71

 MEAN 5.31 1.10 4.91 513.15 1.03 502.32 480.04 0.77

 HUB 5.28 1.10 4.84 512.28 1.03 500.08 479.63 0.82

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.38 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.79 27.15 23.50 3.65 0.95 0.51 1.63

 HUB 45.66 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 393.0236 250.0506 303.2198 1090.1024 0.3605 -0.1096 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3184 4.8671 501.1960 480.2782 0.7965 39.5107 30.6000 -8.9107

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 293.3853 62.1998 286.7162 1096.0637 0.2677 0.3568 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3126 5.0578 506.6945 480.2021 491.5697 0.0241 0.4545

 

NASA/TM—2013-218094 O–230
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 304.0901 0.0000 304.0901 1095.4967 0.2776 0.3484 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0243 506.1803 480.1688 0.0000 0.0600 0.0623 0.2754

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8372 5.2969 1.1011 513.6141 16.0092 191.4622 1.4842

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 99578.008 0.516 148.387 243172.703 0.133220E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.647 EfDer = 0.976 SH = 0.139335E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.369 2465.203 5.297 513.614 1.000 1.000 0.980

 W Kg/sec = 11.986 Wdry = 26.366 WH2O = 0.004 lbm/sec H2O = 0.061g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.821 2477.378 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58412.004 20689.604 2.559 545.479 213.175 424.468 1.991

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 257.00 -0.09 257.00 0.23 0.46 433.88

 MEAN 17.74 0.00 -0.02 257.00 -0.09 257.00 0.23 0.42

 HUB 15.05 0.00 -0.02 257.00 -0.09 257.00 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.24 46.36 12.88 431.76 502.54 5.10 508.30 480.16 0.68

 MEAN 56.05 43.40 12.65 381.61 460.15 5.10 508.30 480.16 0.68

 HUB 51.57 38.84 12.73 323.77 413.44 5.10 508.30 480.16 0.68

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 358.78 235.65 270.54 1109.73 0.32 2.26 1.98 8.75

 MEAN 17.51 360.88 236.14 272.89 1107.62 0.33 2.34 2.07 6.78

 HUB 14.85 385.41 269.53 275.49 1105.55 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.17 330.89 190.52 0.30 4669.99 0.92 0.89

 MEAN 376.62 306.92 140.47 0.28 4135.65 0.92 0.89 0.89 1.64

 HUB 319.47 279.98 49.94 0.25 4003.83 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.86 1.11 5.45 529.77 1.03 519.42 487.86 0.49

 MEAN 5.79 1.09 5.38 527.92 1.03 517.45 487.02 0.52

 HUB 5.77 1.09 5.31 527.46 1.03 515.52 486.83 0.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.06 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.87 27.24 23.50 3.74 0.94 0.49 1.62

 HUB 44.37 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 388.0459 237.6942 306.7264 1106.3510 0.3507 -0.1173 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8024 5.3351 516.2780 487.2395 0.5378 37.7735 31.5000 -6.2735

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 301.8628 65.8493 294.5930 1111.4586 0.2716 0.3051 2.3726

 

NASA/TM—2013-218094 O–231
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7988 5.5127 521.0574 487.1834 451.3937 0.0187 0.4293

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 306.9557 0.0000 306.9557 1111.1815 0.2762 0.3330 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4907 520.8081 487.1536 0.0000 0.0600 0.0498 0.2531

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8574 5.7856 1.0923 528.3813 14.7681 196.9079 1.5264

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91873.766 0.506 136.906 241654.953 0.144221E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.061 EfDer = 0.986 SH = 0.151090E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.369 2465.203 5.786 528.381 1.000 1.000 0.980

 W Kg/sec = 11.986 Wdry = 26.365 WH2O = 0.004 lbm/sec H2O = 0.070g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.621 2442.514 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54973.957 20689.508 2.593 513.330 197.959 395.845 2.000

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 257.02 -0.09 257.02 0.23 0.44 410.51

 MEAN 16.97 0.00 -0.02 257.02 -0.09 257.02 0.23 0.40

 HUB 14.32 0.00 -0.02 257.02 -0.09 257.02 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.19 46.36 11.83 414.34 487.66 5.58 523.07 487.15 0.47

 MEAN 54.86 43.80 11.06 365.09 446.56 5.58 523.07 487.15 0.47

 HUB 50.17 37.84 12.33 308.07 401.27 5.58 523.07 487.15 0.47

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.49 215.83 269.78 1123.98 0.31 2.16 1.89 8.34

 MEAN 16.57 347.53 216.46 271.89 1122.09 0.31 2.24 1.97 6.35

 HUB 13.89 370.50 249.17 274.20 1120.22 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.16 330.16 190.33 0.29 4076.64 0.92 0.90

 MEAN 356.55 305.86 140.09 0.27 3589.08 0.92 0.90 0.90 1.60

 HUB 298.81 278.65 49.64 0.25 3462.30 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.31 1.09 5.91 542.48 1.03 532.88 493.46 0.36

 MEAN 6.24 1.08 5.85 540.79 1.02 531.09 492.73 0.38

 HUB 6.23 1.08 5.78 540.35 1.02 529.32 492.55 0.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.66 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.52 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.26 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 369.1813 217.6769 298.1805 1121.1925 0.3293 -0.0929 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2541 5.8074 530.2546 492.9103 0.3888 36.1301 32.4000 -3.7301

 

NASA/TM—2013-218094 O–232
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 299.4664 67.1616 291.8381 1125.1438 0.2662 0.2680 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2522 5.9557 534.0009 492.8733 432.2457 0.0146 0.4079

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 297.0705 0.0000 297.0705 1125.2546 0.2640 0.3187 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9498 534.1156 492.8458 0.0000 0.0600 0.0414 0.2537

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8705 6.2411 1.0787 541.2076 12.8271 212.2879 1.6456

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79813.898 0.484 118.935 247230.609 0.156484E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.609 EfDer = 0.993 SH = 0.164706E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.369 2465.203 6.241 541.207 1.000 1.000 0.980

 W Kg/sec = 11.986 Wdry = 26.365 WH2O = 0.004 lbm/sec H2O = 0.080g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.442 2413.397 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52043.051 20689.396 2.744 509.668 185.729 384.739 2.072

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 245.07 -0.08 245.07 0.22 0.41 385.82

 MEAN 15.91 0.00 -0.02 245.07 -0.08 245.07 0.22 0.37

 HUB 13.07 0.00 -0.02 245.07 -0.08 245.07 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.13 47.36 10.77 394.12 464.17 6.04 536.38 492.84 0.35

 MEAN 54.41 44.80 9.61 342.34 421.08 6.04 536.38 492.84 0.35

 HUB 48.93 38.84 10.09 281.17 373.05 6.04 536.38 492.84 0.35

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 328.03 202.80 257.83 1136.80 0.29 2.05 1.78 7.43

 MEAN 15.50 327.17 198.73 259.90 1134.84 0.29 2.13 1.86 5.75

 HUB 12.59 344.34 223.33 262.09 1132.90 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 385.94 316.26 183.15 0.28 3639.71 0.92 0.91

 MEAN 333.40 292.71 134.67 0.26 3081.21 0.92 0.91 0.91 1.59

 HUB 270.85 266.37 47.52 0.24 2812.86 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.08 6.36 553.79 1.02 545.14 498.20 0.28

 MEAN 6.66 1.07 6.29 551.86 1.02 543.26 497.40 0.30

 HUB 6.62 1.06 6.21 550.93 1.02 541.40 497.02 0.31

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.19 35.39 31.50 3.89 0.93 0.47 1.40

 MEAN 37.40 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.43 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 358.4105 202.3760 295.8074 1133.3743 0.3162 -0.1732 2.0437

 

NASA/TM—2013-218094 O–233
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6612 6.2208 541.8729 497.5355 0.3093 34.3779 33.0000 -1.3779

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 302.3251 69.0362 294.3373 1136.4827 0.2660 0.1497 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6592 6.3437 544.8504 497.5067 410.5396 0.0252 0.3837

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 294.0803 0.0000 294.0803 1136.8855 0.2587 0.3070 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3560 545.2454 497.4948 0.0000 0.0600 0.0373 0.1819

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8794 6.6546 1.0662 552.1942 10.9873 231.9502 1.7981

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68379.039 0.459 101.896 259186.359 0.170960E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1554 Tt4 = 552.1942 T1 = 477.9153

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 462099.69 688.6019 87.2487 1.5604 0.8405 15.0976 1.1554 37.3740

NASA/TM—2013-218094 O–234
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.208 EfDer = 0.957 SH = 0.101719E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.397 2387.630 4.199 471.471 1.000 1.000 0.980

 W Kg/sec = 11.544 Wdry = 25.394 WH2O = 0.003 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.761 2504.352 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64376.887 19926.633 3.351 831.557 248.115 619.754 2.498

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 185.80 -0.06 185.80 0.18 0.44 450.85

 MEAN 17.06 0.00 -0.02 185.80 -0.06 185.80 0.18 0.38

 HUB 12.51 0.00 -0.02 185.80 -0.06 185.80 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.63 50.47 16.16 429.85 468.34 4.11 468.70 456.90 2.02

 MEAN 62.41 47.20 15.21 355.47 401.15 4.11 468.69 456.90 2.02

 HUB 54.52 38.62 15.90 260.66 320.15 4.11 468.70 456.90 2.02

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 386.15 294.91 249.27 1066.71 0.36 7.29 6.52 16.04

 MEAN 18.04 391.24 298.96 252.38 1063.77 0.37 7.43 6.80 12.53

 HUB 15.00 424.29 337.83 256.70 1060.14 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 429.85 283.45 134.94 0.27 6085.30 0.92 0.88

 MEAN 375.80 263.82 76.84 0.25 5393.10 0.92 0.88 0.88 1.74

 HUB 312.54 257.95 25.29 0.24 5068.24 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 491.86 1.04 479.87 469.26 1.40

 MEAN 4.73 1.13 4.32 489.54 1.04 477.23 467.95 1.54

 HUB 4.70 1.12 4.21 488.46 1.04 473.98 467.37 1.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.79 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.83 16.93 12.70 4.23 0.95 0.51 2.22

 HUB 52.77 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 402.8457 298.3769 270.6582 1063.3964 0.3788 -0.0371 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7408 4.2992 476.9044 468.1924 1.5741 47.7888 35.4000 -12.3888

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 269.1416 65.8402 260.9641 1071.4170 0.2512 0.5080 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7304 4.5298 484.1295 468.0731 554.9116 0.0338 0.5996

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 267.9661 0.0000 267.9661 1071.4619 0.2501 0.4793 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5108 484.1801 468.0276 0.0000 0.0600 0.0832 0.4645

NASA/TM—2013-218094 O–235
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8194 4.7088 1.1214 489.9540 18.4835 169.2512 1.3120

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 114940.055 0.622 164.960 260276.719 0.112096E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.660 EfDer = 0.961 SH = 0.122264E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.397 2387.630 4.709 489.954 1.000 1.000 0.980

 W Kg/sec = 11.544 Wdry = 25.393 WH2O = 0.003 lbm/sec H2O = 0.050g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.056 2456.674 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60290.094 19926.471 2.618 590.487 225.565 468.502 2.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 245.05 -0.08 245.05 0.23 0.46 440.55

 MEAN 18.08 0.00 -0.02 245.05 -0.08 245.05 0.23 0.42

 HUB 15.21 0.00 -0.02 245.05 -0.08 245.05 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.22 46.36 13.86 428.18 493.41 4.54 485.13 468.05 1.32

 MEAN 56.96 42.30 14.66 376.68 449.44 4.54 485.13 468.05 1.32

 HUB 52.30 37.84 14.46 316.92 400.67 4.54 485.13 468.05 1.32

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 355.47 243.87 258.62 1084.99 0.33 2.33 2.04 9.02

 MEAN 18.01 355.60 241.42 261.09 1082.66 0.33 2.40 2.13 7.35

 HUB 15.22 377.41 269.88 263.82 1080.37 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 425.47 316.01 181.60 0.29 4981.63 0.92 0.88

 MEAN 375.26 293.39 133.84 0.27 4349.47 0.92 0.88 0.88 1.69

 HUB 317.19 268.03 47.31 0.25 4109.64 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.24 1.11 4.87 506.65 1.03 496.49 477.13 0.91

 MEAN 5.17 1.10 4.80 504.53 1.03 494.36 476.03 0.97

 HUB 5.14 1.09 4.73 503.72 1.03 492.27 475.63 1.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.32 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.76 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.65 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 380.7344 242.0965 293.8503 1081.5035 0.3520 -0.1097 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1812 4.7609 493.3106 476.2695 1.0085 39.4843 30.6000 -8.8843

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 284.7041 60.3593 278.2322 1087.1190 0.2619 0.3556 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1760 4.9381 498.4483 476.1959 491.5697 0.0235 0.4532

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 295.0252 0.0000 295.0252 1086.5851 0.2715 0.3470 0.5911

NASA/TM—2013-218094 O–236
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9067 497.9672 476.1668 0.0000 0.0600 0.0622 0.2738

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8370 5.1612 1.0961 504.9649 15.0117 191.4249 1.4839

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93366.859 0.516 133.999 236621.703 0.126302E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.588 EfDer = 0.976 SH = 0.131504E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.397 2387.630 5.161 504.965 1.000 1.000 0.980

 W Kg/sec = 11.544 Wdry = 25.393 WH2O = 0.003 lbm/sec H2O = 0.057g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.370 2419.884 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56699.059 19926.398 2.611 545.479 208.925 424.468 2.032

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.46 -0.09 249.46 0.23 0.45 423.82

 MEAN 17.74 0.00 -0.02 249.46 -0.09 249.46 0.23 0.41

 HUB 15.05 0.00 -0.02 249.46 -0.09 249.46 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.19 46.36 12.83 418.18 487.01 4.98 499.96 476.16 0.86

 MEAN 55.99 43.40 12.59 369.60 445.98 4.98 499.96 476.16 0.86

 HUB 51.50 38.84 12.66 313.58 400.77 4.98 499.96 476.16 0.86

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 347.86 227.45 263.20 1099.99 0.32 2.26 1.98 8.75

 MEAN 17.51 350.01 228.24 265.37 1098.02 0.32 2.34 2.07 6.78

 HUB 14.85 373.82 260.86 267.76 1096.08 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 412.76 321.89 185.31 0.29 4507.47 0.92 0.89

 MEAN 364.77 298.43 136.53 0.27 3997.15 0.92 0.89 0.89 1.64

 HUB 309.41 272.12 48.55 0.25 3875.12 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.68 1.10 5.30 520.07 1.03 510.34 483.75 0.62

 MEAN 5.62 1.09 5.24 518.36 1.03 508.51 482.93 0.66

 HUB 5.60 1.09 5.18 517.95 1.03 506.71 482.75 0.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.83 35.15 31.50 3.65 0.93 0.50 1.40

 MEAN 40.70 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.25 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 376.4218 229.7338 298.1874 1096.8110 0.3432 -0.1181 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6296 5.1945 507.3987 483.1483 0.6846 37.6119 31.5000 -6.1119

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 293.8095 64.0926 286.7336 1101.6100 0.2667 0.3011 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6264 5.3585 511.8497 483.0941 451.3937 0.0181 0.4259

 

NASA/TM—2013-218094 O–237
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 298.7218 0.0000 298.7218 1101.3488 0.2712 0.3298 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3380 511.6157 483.0676 0.0000 0.0600 0.0491 0.2491

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8580 5.6142 1.0878 518.7888 13.8246 197.4453 1.5306

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85996.656 0.505 123.421 235442.016 0.135736E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.920 EfDer = 0.987 SH = 0.141731E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.397 2387.630 5.614 518.789 1.000 1.000 0.980

 W Kg/sec = 11.544 Wdry = 25.393 WH2O = 0.004 lbm/sec H2O = 0.065g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.503 2387.426 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53522.313 19926.320 2.637 513.330 194.683 395.845 2.033

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.24 -0.09 250.24 0.23 0.43 401.26

 MEAN 16.97 0.00 -0.02 250.24 -0.09 250.24 0.23 0.39

 HUB 14.32 0.00 -0.02 250.24 -0.09 250.24 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.06 46.36 11.70 401.30 473.00 5.42 513.76 483.06 0.60

 MEAN 54.72 43.80 10.92 353.60 433.26 5.42 513.76 483.06 0.60

 HUB 50.02 37.84 12.18 298.37 389.48 5.42 513.76 483.06 0.60

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 335.30 207.75 263.17 1113.42 0.30 2.16 1.89 8.34

 MEAN 16.57 337.44 208.76 265.12 1111.64 0.30 2.24 1.97 6.35

 HUB 13.89 359.89 241.03 267.25 1109.90 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 393.38 322.05 185.63 0.29 3924.07 0.92 0.90

 MEAN 345.33 298.23 136.58 0.27 3461.39 0.92 0.90 0.90 1.59

 HUB 289.41 271.59 48.38 0.24 3349.17 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.09 1.09 5.73 531.93 1.03 522.90 489.26 0.46

 MEAN 6.04 1.08 5.67 530.38 1.02 521.23 488.56 0.48

 HUB 6.02 1.07 5.60 530.01 1.02 519.60 488.40 0.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.29 35.20 31.50 3.70 0.93 0.47 1.40

 MEAN 38.22 27.25 23.50 3.75 0.94 0.46 1.62

 HUB 42.05 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.5873 209.9321 290.7118 1110.7872 0.3228 -0.0938 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0465 5.6306 520.4390 488.7387 0.4968 35.8342 32.4000 -3.4342

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.2558 65.5444 284.8112 1114.4822 0.2622 0.2614 2.2705

 

NASA/TM—2013-218094 O–238
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0449 5.7664 523.9089 488.7030 432.2457 0.0141 0.4026

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.8980 0.0000 289.8980 1114.5909 0.2601 0.3135 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7610 524.0190 488.6783 0.0000 0.0600 0.0406 0.2475

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8714 6.0347 1.0749 530.7736 11.9856 213.4862 1.6549

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74568.719 0.482 107.020 241155.703 0.146446E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.395 EfDer = 0.994 SH = 0.153574E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.397 2387.630 6.035 530.773 1.000 1.000 0.980

 W Kg/sec = 11.544 Wdry = 25.393 WH2O = 0.004 lbm/sec H2O = 0.074g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.579 2360.318 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50803.848 19926.227 2.782 509.668 183.200 384.739 2.100

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.23 -0.08 239.23 0.21 0.40 377.34

 MEAN 15.91 0.00 -0.02 239.23 -0.08 239.23 0.21 0.37

 HUB 13.07 0.00 -0.02 239.23 -0.08 239.23 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.93 47.36 10.57 381.72 450.56 5.85 526.17 488.67 0.45

 MEAN 54.20 44.80 9.40 331.56 408.93 5.85 526.17 488.67 0.45

 HUB 48.71 38.84 9.87 272.33 362.54 5.85 526.17 488.67 0.45

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 318.58 194.73 252.14 1125.49 0.28 2.05 1.78 7.43

 MEAN 15.50 318.01 191.29 254.04 1123.65 0.28 2.13 1.86 5.75

 HUB 12.59 334.91 215.85 256.08 1121.84 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 373.80 309.26 179.07 0.27 3495.00 0.92 0.91

 MEAN 322.91 286.11 131.61 0.25 2965.91 0.92 0.91 0.91 1.58

 HUB 262.33 260.26 46.48 0.23 2718.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.49 1.07 6.14 542.48 1.02 534.32 493.92 0.36

 MEAN 6.42 1.06 6.07 540.71 1.02 532.58 493.15 0.38

 HUB 6.38 1.06 6.01 539.88 1.02 530.86 492.80 0.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.68 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 36.98 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.13 10.29 6.50 3.79 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 348.5915 194.8017 289.0819 1122.2416 0.3106 -0.1749 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4207 6.0105 531.2554 493.2869 0.3954 33.9746 33.0000 -0.9746

 

NASA/TM—2013-218094 O–239
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.7007 67.5235 287.8879 1125.1294 0.2628 0.1402 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4191 6.1220 533.9938 493.2596 410.5396 0.0246 0.3770

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.6487 0.0000 287.6487 1125.5194 0.2556 0.2999 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1335 534.3712 493.2480 0.0000 0.0600 0.0369 0.1726

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 6.4147 1.0630 541.0203 10.2475 233.8993 1.8132

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63765.508 0.456 91.515 253087.563 0.158902E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1475 Tt4 = 541.0203 T1 = 471.4712

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 432637.78 620.9152 84.7614 1.5276 0.8409 15.2082 1.1475 37.3740

NASA/TM—2013-218094 O–240
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.268 EfDer = 0.956 SH = 0.965871E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.949 2357.155 4.337 469.499 1.000 1.000 0.980

 W Kg/sec = 11.795 Wdry = 25.947 WH2O = 0.003 lbm/sec H2O = 0.038g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.676 2477.574 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 63393.563 20360.174 3.395 831.557 244.938 619.754 2.530

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 182.96 -0.06 182.96 0.17 0.44 446.03

 MEAN 17.06 0.00 -0.02 182.96 -0.06 182.96 0.17 0.38

 HUB 12.51 0.00 -0.02 182.96 -0.06 182.96 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.68 50.47 16.21 424.36 462.18 4.25 466.81 456.00 2.16

 MEAN 62.47 47.20 15.27 350.93 395.82 4.25 466.81 456.00 2.16

 HUB 54.59 38.62 15.97 257.33 315.80 4.25 466.81 456.00 2.16

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 381.12 291.35 245.70 1064.29 0.36 7.29 6.52 16.04

 MEAN 18.04 386.05 295.26 248.70 1061.43 0.36 7.43 6.80 12.53

 HUB 15.00 418.49 333.46 252.86 1057.88 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 424.36 279.40 133.01 0.26 6011.82 0.92 0.87

 MEAN 371.00 259.98 75.74 0.24 5326.43 0.92 0.87 0.87 1.75

 HUB 308.55 254.08 24.91 0.24 5002.64 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 489.39 1.04 477.71 468.35 1.51

 MEAN 4.88 1.12 4.45 487.12 1.04 475.14 467.04 1.65

 HUB 4.84 1.12 4.35 486.05 1.04 471.97 466.45 1.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.86 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.89 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.83 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.4471 294.6886 266.6886 1061.0640 0.3746 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8840 4.4385 474.8169 467.2756 1.6861 47.8554 35.4000 -12.4554

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 265.4007 64.9251 257.3369 1068.8953 0.2483 0.5088 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8736 4.6715 481.8554 467.1614 554.9116 0.0336 0.6003

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 264.2325 0.0000 264.2325 1068.9396 0.2472 0.4795 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6521 481.9050 467.1178 0.0000 0.0600 0.0837 0.4648

NASA/TM—2013-218094 O–241
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8187 4.8514 1.1186 487.5190 18.0206 168.9940 1.3100

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 112061.555 0.622 164.328 266676.531 0.106085E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.688 EfDer = 0.961 SH = 0.115357E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.949 2357.155 4.851 487.519 1.000 1.000 0.980

 W Kg/sec = 11.795 Wdry = 25.946 WH2O = 0.003 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.227 2431.366 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59457.438 20360.025 2.646 590.487 223.136 468.502 2.100

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 241.66 -0.08 241.66 0.23 0.46 436.01

 MEAN 18.08 0.00 -0.02 241.66 -0.08 241.66 0.23 0.41

 HUB 15.21 0.00 -0.02 241.66 -0.08 241.66 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.25 46.36 13.89 422.71 486.99 4.68 482.82 467.14 1.41

 MEAN 56.99 42.30 14.69 371.87 443.56 4.68 482.82 467.14 1.41

 HUB 52.32 37.84 14.48 312.87 395.40 4.68 482.82 467.14 1.41

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 350.95 240.79 255.31 1082.14 0.32 2.33 2.04 9.02

 MEAN 18.01 351.04 238.38 257.69 1079.87 0.33 2.40 2.13 7.35

 HUB 15.22 372.53 266.47 260.33 1077.64 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 420.04 311.96 179.25 0.29 4918.62 0.92 0.88 

 MEAN 370.47 289.57 132.09 0.27 4294.64 0.92 0.88 0.88 1.69

 HUB 313.14 264.48 46.67 0.25 4057.78 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.11 5.01 503.79 1.03 493.89 476.22 0.98

 MEAN 5.32 1.10 4.95 501.73 1.03 491.82 475.12 1.05

 HUB 5.29 1.09 4.88 500.94 1.03 489.78 474.72 1.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.32 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.77 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.67 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.8126 239.0447 289.9875 1078.7428 0.3484 -0.1096 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3278 4.9041 490.7963 475.3588 1.0840 39.4997 30.6000 -8.8997

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 281.1149 59.5984 274.7247 1084.2240 0.2593 0.3556 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3227 5.0827 495.7979 475.2883 491.5697 0.0232 0.4531

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 291.2793 0.0000 291.2793 1083.7036 0.2688 0.3467 0.5911

NASA/TM—2013-218094 O–242
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0510 495.3302 475.2604 0.0000 0.0600 0.0623 0.2736

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8368 5.3076 1.0940 502.1514 14.6330 191.3039 1.4830

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91010.984 0.516 133.459 242533.484 0.119031E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.581 EfDer = 0.977 SH = 0.123769E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.949 2357.155 5.308 502.151 1.000 1.000 0.980

 W Kg/sec = 11.795 Wdry = 25.946 WH2O = 0.003 lbm/sec H2O = 0.055g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.713 2395.680 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55991.523 20359.957 2.635 545.479 207.001 424.468 2.051

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 246.35 -0.08 246.35 0.23 0.44 419.58

 MEAN 17.74 0.00 -0.02 246.35 -0.08 246.35 0.23 0.41

 HUB 15.05 0.00 -0.02 246.35 -0.08 246.35 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.18 46.36 12.82 412.84 480.83 5.12 497.27 475.25 0.92

 MEAN 55.98 43.40 12.58 364.88 440.33 5.12 497.27 475.25 0.92

 HUB 51.50 38.84 12.66 309.58 395.70 5.12 497.27 475.25 0.92

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 343.54 224.37 260.16 1096.79 0.31 2.26 1.98 8.75

 MEAN 17.51 345.65 225.17 262.25 1094.86 0.32 2.34 2.07 6.78

 HUB 14.85 369.19 257.50 264.56 1092.98 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 407.49 318.15 183.13 0.29 4446.37 0.92 0.89

 MEAN 360.11 294.93 134.94 0.27 3943.49 0.92 0.89 0.89 1.64

 HUB 305.47 268.87 47.96 0.25 3825.22 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.83 1.10 5.45 516.86 1.03 507.37 482.84 0.67

 MEAN 5.77 1.09 5.39 515.19 1.03 505.59 482.02 0.71

 HUB 5.75 1.08 5.32 514.80 1.03 503.84 481.84 0.75

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.78 35.14 31.50 3.64 0.93 0.50 1.40

 MEAN 40.65 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.23 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.7343 226.6495 294.6462 1093.6837 0.3399 -0.1181 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7792 5.3407 504.5091 482.2407 0.7386 37.5684 31.5000 -6.0684

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 290.4612 63.3621 283.4659 1098.3619 0.2644 0.3001 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7761 5.5055 508.8355 482.1890 451.3937 0.0178 0.4249

 

NASA/TM—2013-218094 O–243
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 295.2998 0.0000 295.2998 1098.1072 0.2689 0.3288 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4848 508.6076 482.1636 0.0000 0.0600 0.0490 0.2480

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8582 5.7637 1.0859 515.6175 13.4668 197.5550 1.5314

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83769.445 0.504 122.840 241448.109 0.127641E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.879 EfDer = 0.987 SH = 0.133071E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.949 2357.155 5.764 515.617 1.000 1.000 0.980

 W Kg/sec = 11.795 Wdry = 25.946 WH2O = 0.003 lbm/sec H2O = 0.063g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.984 2364.190 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 52919.512 20359.885 2.658 513.330 193.162 395.845 2.049

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 247.42 -0.09 247.42 0.22 0.42 397.35

 MEAN 16.97 0.00 -0.02 247.42 -0.09 247.42 0.22 0.39

 HUB 14.32 0.00 -0.02 247.42 -0.09 247.42 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.02 46.36 11.66 396.18 467.16 5.57 510.70 482.16 0.64

 MEAN 54.68 43.80 10.88 349.09 427.95 5.57 510.70 482.16 0.64

 HUB 49.98 37.84 12.14 294.56 384.75 5.57 510.70 482.16 0.64

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.25 204.71 260.42 1109.89 0.30 2.16 1.89 8.34

 MEAN 16.57 333.40 205.79 262.30 1108.16 0.30 2.24 1.97 6.35

 HUB 13.89 355.61 237.86 264.36 1106.46 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.36 318.67 183.66 0.29 3866.47 0.92 0.90

 MEAN 340.93 295.07 135.14 0.27 3412.19 0.92 0.90 0.90 1.59

 HUB 285.72 268.66 47.86 0.24 3305.03 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.25 1.08 5.88 528.40 1.02 519.58 488.35 0.50

 MEAN 6.19 1.07 5.82 526.90 1.02 517.97 487.65 0.52

 HUB 6.17 1.07 5.75 526.55 1.02 516.38 487.49 0.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.17 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.12 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 41.98 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 354.3167 206.9475 287.5988 1107.3198 0.3200 -0.0940 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1983 5.7791 517.1930 487.8297 0.5374 35.7377 32.4000 -3.3377

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 289.2412 64.8684 281.8734 1110.9156 0.2604 0.2593 2.2705

 

NASA/TM—2013-218094 O–244
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1968 5.9151 520.5591 487.7955 432.2457 0.0139 0.4009

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.9009 0.0000 286.9009 1111.0232 0.2582 0.3118 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9098 520.6674 487.7719 0.0000 0.0600 0.0404 0.2455

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8717 6.1865 1.0733 527.2832 11.6665 213.8603 1.6578

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72581.383 0.481 106.434 247424.766 0.137356E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.324 EfDer = 0.994 SH = 0.143854E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.949 2357.155 6.186 527.283 1.000 1.000 0.980

 W Kg/sec = 11.795 Wdry = 25.945 WH2O = 0.004 lbm/sec H2O = 0.071g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.167 2337.891 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50286.652 20359.797 2.800 509.668 181.992 384.739 2.114 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.80 -0.08 236.80 0.21 0.40 373.75

 MEAN 15.91 0.00 -0.02 236.80 -0.08 236.80 0.21 0.36

 HUB 13.07 0.00 -0.02 236.80 -0.08 236.80 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.86 47.36 10.50 376.84 445.14 6.00 522.78 487.77 0.49

 MEAN 54.12 44.80 9.32 327.33 404.07 6.00 522.78 487.77 0.49

 HUB 48.64 38.84 9.80 268.85 358.33 6.00 522.78 487.77 0.49

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.81 191.64 249.75 1121.66 0.28 2.05 1.78 7.43

 MEAN 15.50 314.33 188.43 251.59 1119.87 0.28 2.13 1.86 5.75

 HUB 12.59 331.15 213.00 253.56 1118.11 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 369.03 306.34 177.38 0.27 3439.60 0.92 0.91

 MEAN 318.79 283.36 130.36 0.25 2921.47 0.92 0.91 0.91 1.58

 HUB 258.98 257.69 45.98 0.23 2682.75 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.64 1.07 6.29 538.66 1.02 530.69 493.00 0.39

 MEAN 6.57 1.06 6.22 536.94 1.02 529.00 492.24 0.41

 HUB 6.54 1.06 6.16 536.15 1.02 527.34 491.89 0.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.50 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.83 27.39 23.50 3.89 0.93 0.44 1.64

 HUB 40.03 10.28 6.50 3.78 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 344.6235 191.8823 286.2630 1118.4897 0.3081 -0.1753 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5738 6.1603 527.7057 492.3725 0.4283 33.8340 33.0000 -0.8340

 

NASA/TM—2013-218094 O–245
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 292.9149 66.8874 285.1757 1121.2932 0.2612 0.1370 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5723 6.2716 530.3550 492.3464 410.5396 0.0243 0.3746

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 284.9452 0.0000 284.9452 1121.6772 0.2540 0.2973 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2832 530.7249 492.3351 0.0000 0.0600 0.0368 0.1693

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8802 6.5678 1.0616 537.2499 9.9675 234.5652 1.8183

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 62020.949 0.455 90.948 259780.344 0.148689E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1443 Tt4 = 537.2499 T1 = 469.4992

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 421444.28 618.0090 83.6761 1.5143 0.8408 15.2680 1.1443 37.3740

NASA/TM—2013-218094 O–246
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.373 EfDer = 0.955 SH = 0.116041E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.785 2282.956 4.829 471.209 1.000 1.000 0.980

 W Kg/sec = 12.630 Wdry = 27.782 WH2O = 0.003 lbm/sec H2O = 0.051g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.623 2395.230 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61123.965 21800.490 3.523 831.557 236.006 619.754 2.626

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 176.41 -0.06 176.41 0.17 0.42 431.20

 MEAN 17.06 0.00 -0.02 176.41 -0.06 176.41 0.17 0.36

 HUB 12.51 0.00 -0.02 176.41 -0.06 176.41 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.77 50.47 16.30 411.00 447.32 4.74 468.71 458.00 2.66

 MEAN 62.57 47.20 15.37 339.88 382.99 4.74 468.71 458.00 2.66

 HUB 54.71 38.62 16.09 249.23 305.40 4.74 468.71 458.00 2.66

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 369.08 282.42 237.60 1065.63 0.35 7.29 6.52 16.04

 MEAN 18.04 373.67 286.16 240.30 1062.95 0.35 7.43 6.80 12.53

 HUB 15.00 404.72 322.87 244.03 1059.64 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 411.00 270.16 128.58 0.25 5827.66 0.92 0.87

 MEAN 359.32 251.19 73.17 0.24 5162.15 0.92 0.87 0.87 1.75

 HUB 298.84 245.21 24.03 0.23 4843.81 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 489.88 1.04 478.93 469.76 1.89

 MEAN 5.39 1.12 4.95 487.75 1.04 476.52 468.51 2.06

 HUB 5.35 1.11 4.85 486.73 1.03 473.56 467.94 2.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.93 28.42 24.20 4.22 0.93 0.57 1.80

 MEAN 49.98 16.93 12.70 4.23 0.95 0.52 2.22

 HUB 52.92 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 384.6269 285.6001 257.6247 1062.6151 0.3620 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3957 4.9344 476.2231 468.7327 2.0955 47.9481 35.4000 -12.5481

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.9864 62.8667 249.1782 1069.9324 0.2402 0.5097 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3854 5.1761 482.8079 468.6114 554.9116 0.0327 0.6004

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.8171 0.0000 255.8171 1069.9752 0.2391 0.4789 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1553 482.8560 468.5700 0.0000 0.0600 0.0843 0.4642

NASA/TM—2013-218094 O–247
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8175 5.3618 1.1104 488.1175 16.9093 168.5596 1.3067

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 105164.859 0.623 165.125 284445.000 0.125416E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.689 EfDer = 0.961 SH = 0.134357E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.785 2282.956 5.362 488.117 1.000 1.000 0.980

 W Kg/sec = 12.630 Wdry = 27.781 WH2O = 0.004 lbm/sec H2O = 0.062g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.897 2353.388 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57583.227 21800.334 2.730 590.487 216.320 468.502 2.166 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 234.04 -0.08 234.04 0.22 0.44 422.03

 MEAN 18.08 0.00 -0.02 234.04 -0.08 234.04 0.22 0.40

 HUB 15.21 0.00 -0.02 234.04 -0.08 234.04 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.25 46.36 13.89 409.41 471.65 5.19 483.71 468.59 1.76

 MEAN 56.99 42.30 14.69 360.16 429.60 5.19 483.71 468.59 1.76

 HUB 52.33 37.84 14.49 303.02 382.95 5.19 483.71 468.59 1.76

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 340.13 232.75 248.03 1082.30 0.31 2.33 2.04 9.02

 MEAN 18.01 340.25 230.61 250.18 1080.19 0.31 2.40 2.13 7.35

 HUB 15.22 361.06 258.01 252.57 1078.10 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.82 303.02 174.07 0.28 4754.35 0.92 0.88

 MEAN 358.80 281.11 128.20 0.26 4154.66 0.92 0.88 0.88 1.68

 HUB 303.28 256.59 45.27 0.24 3928.98 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.91 1.10 5.53 503.35 1.03 494.05 477.26 1.24

 MEAN 5.84 1.09 5.46 501.43 1.03 492.12 476.22 1.32

 HUB 5.82 1.08 5.39 500.70 1.03 490.22 475.84 1.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.18 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.67 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.61 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.2480 231.2533 281.4223 1079.1235 0.3375 -0.1099 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8533 5.4150 491.1593 476.4520 1.3696 39.4110 30.6000 -8.8110

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 273.2738 57.9360 267.0618 1084.2319 0.2520 0.3532 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8484 5.5988 495.8218 476.3775 491.5697 0.0223 0.4506

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 283.0714 0.0000 283.0714 1083.7443 0.2612 0.3443 0.5911

NASA/TM—2013-218094 O–248
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5659 495.3835 476.3526 0.0000 0.0600 0.0618 0.2708

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8369 5.8326 1.0878 501.8250 13.7081 191.4710 1.4843

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85269.602 0.515 133.887 259037.891 0.137902E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.474 EfDer = 0.977 SH = 0.142439E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.785 2282.956 5.833 501.825 1.000 1.000 0.980

 W Kg/sec = 12.630 Wdry = 27.781 WH2O = 0.004 lbm/sec H2O = 0.070g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.878 2321.024 1.381 0.248 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54446.340 21800.266 2.705 545.479 201.634 424.468 2.105

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 239.55 -0.08 239.55 0.22 0.43 406.50

 MEAN 17.74 0.00 -0.02 239.55 -0.08 239.55 0.22 0.39

 HUB 15.05 0.00 -0.02 239.55 -0.08 239.55 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.08 46.36 12.72 399.85 466.18 5.64 497.21 476.34 1.17

 MEAN 55.87 43.40 12.47 353.40 427.00 5.64 497.21 476.34 1.17

 HUB 51.38 38.84 12.54 299.83 383.84 5.64 497.21 476.34 1.17

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.28 216.14 253.69 1095.96 0.30 2.26 1.98 8.75

 MEAN 17.51 335.49 217.34 255.58 1094.18 0.31 2.34 2.07 6.78

 HUB 14.85 358.45 249.17 257.67 1092.42 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 394.67 310.21 178.52 0.28 4283.41 0.92 0.89

 MEAN 348.78 287.40 131.44 0.26 3806.25 0.92 0.89 0.89 1.63

 HUB 295.85 261.87 46.68 0.24 3701.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 515.54 1.03 506.62 483.61 0.87

 MEAN 6.30 1.08 5.91 514.02 1.02 504.97 482.83 0.92

 HUB 6.29 1.08 5.85 513.68 1.02 503.35 482.68 0.97

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.43 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.38 27.22 23.50 3.72 0.94 0.48 1.62

 HUB 44.04 10.27 6.50 3.77 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 360.9131 218.7611 287.0573 1093.0532 0.3302 -0.1191 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3168 5.8632 503.9431 483.0465 0.9508 37.3104 31.5000 -5.8104

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 283.4045 61.8228 276.5792 1097.3969 0.2583 0.2940 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3139 6.0314 507.9573 482.9918 451.3937 0.0170 0.4199

 

NASA/TM—2013-218094 O–249
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.0698 0.0000 288.0698 1097.1570 0.2626 0.3240 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0101 507.7429 482.9691 0.0000 0.0600 0.0480 0.2420

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8592 6.3012 1.0803 514.4129 12.5887 198.4471 1.5383

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 78316.563 0.503 122.969 258300.563 0.146126E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.670 EfDer = 0.988 SH = 0.151266E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.785 2282.956 6.301 514.413 1.000 1.000 0.980

 W Kg/sec = 12.630 Wdry = 27.781 WH2O = 0.004 lbm/sec H2O = 0.078g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.551 2292.449 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51651.043 21800.189 2.716 513.330 188.970 395.845 2.095

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.49 -0.08 241.49 0.22 0.41 385.29

 MEAN 16.97 0.00 -0.02 241.49 -0.08 241.49 0.22 0.38

 HUB 14.32 0.00 -0.02 241.49 -0.08 241.49 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.82 46.36 11.46 383.71 453.44 6.10 509.73 482.96 0.83

 MEAN 54.47 43.80 10.67 338.10 415.55 6.10 509.73 482.96 0.83

 HUB 49.76 37.84 11.92 285.29 373.84 6.10 509.73 482.96 0.83

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 321.77 196.50 254.81 1108.15 0.29 2.16 1.89 8.34

 MEAN 16.57 324.09 198.08 256.51 1106.56 0.29 2.24 1.97 6.35

 HUB 13.89 345.91 229.99 258.38 1105.00 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.14 311.77 179.64 0.28 3711.45 0.92 0.90

 MEAN 330.19 288.54 132.11 0.26 3284.35 0.92 0.90 0.90 1.58

 HUB 276.72 262.57 46.73 0.24 3195.78 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.08 6.41 526.30 1.02 517.98 488.89 0.66

 MEAN 6.73 1.07 6.35 524.93 1.02 516.49 488.23 0.68

 HUB 6.72 1.07 6.29 524.65 1.02 515.03 488.11 0.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.64 35.18 31.50 3.68 0.93 0.47 1.40

 MEAN 37.68 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.67 10.25 6.50 3.75 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 344.5973 199.1930 281.1930 1105.7571 0.3116 -0.0952 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7450 6.3113 515.7484 488.4082 0.7007 35.3132 32.4000 -2.9132

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 283.1508 63.5025 275.9381 1109.0737 0.2553 0.2501 2.2705

 

NASA/TM—2013-218094 O–250
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7437 6.4487 518.8484 488.3722 432.2457 0.0132 0.3934

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.8368 0.0000 280.8368 1109.1785 0.2532 0.3044 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4433 518.9531 488.3503 0.0000 0.0600 0.0395 0.2367

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 6.7331 1.0685 525.2916 10.8794 215.6189 1.6715

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67692.078 0.478 106.287 265091.406 0.155281E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.023 EfDer = 0.995 SH = 0.161333E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.785 2282.956 6.733 525.291 1.000 1.000 0.980

 W Kg/sec = 12.630 Wdry = 27.781 WH2O = 0.004 lbm/sec H2O = 0.088g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.045 2268.587 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49244.773 21800.104 2.852 509.668 178.711 384.739 2.153

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.89 -0.08 231.89 0.21 0.39 362.67

 MEAN 15.91 0.00 -0.02 231.89 -0.08 231.89 0.21 0.35

 HUB 13.07 0.00 -0.02 231.89 -0.08 231.89 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.58 47.36 10.22 364.98 432.48 6.53 520.97 488.34 0.63

 MEAN 53.82 44.80 9.02 317.03 392.85 6.53 520.97 488.34 0.63

 HUB 48.32 38.84 9.48 260.39 348.74 6.53 520.97 488.34 0.63

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 306.10 183.34 245.12 1119.11 0.27 2.05 1.78 7.43

 MEAN 15.50 305.98 180.88 246.79 1117.47 0.27 2.13 1.86 5.75

 HUB 12.59 322.68 205.74 248.58 1115.85 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 357.41 300.64 174.07 0.27 3290.57 0.92 0.91

 MEAN 308.75 277.95 127.87 0.25 2804.54 0.92 0.91 0.91 1.56

 HUB 250.82 252.63 45.09 0.23 2591.30 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.19 1.07 6.83 535.83 1.02 528.30 493.35 0.52

 MEAN 7.12 1.06 6.76 534.27 1.02 526.75 492.63 0.54

 HUB 7.09 1.05 6.70 533.59 1.02 525.22 492.32 0.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.79 35.38 31.50 3.88 0.93 0.45 1.40

 MEAN 36.24 27.39 23.50 3.89 0.93 0.43 1.64

 HUB 39.61 10.28 6.50 3.78 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 335.7577 184.2009 280.7191 1116.1404 0.3008 -0.1776 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1265 6.6984 525.5034 492.7671 0.5617 33.2719 33.0000 -0.2719

 

NASA/TM—2013-218094 O–251
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 287.5472 65.6616 279.9499 1118.7012 0.2570 0.1237 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1252 6.8093 527.9181 492.7401 410.5396 0.0236 0.3653

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 279.7390 0.0000 279.7390 1119.0718 0.2500 0.2873 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8214 528.2739 492.7286 0.0000 0.0600 0.0366 0.1562

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 7.1203 1.0575 534.5621 9.2712 237.3458 1.8399

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57694.184 0.452 90.589 278708.750 0.165794E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1344 Tt4 = 534.5621 T1 = 471.2089

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 394137.31 618.8569 80.6226 1.4746 0.8415 15.3730 1.1344 37.3740

NASA/TM—2013-218094 O–252
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.907 EfDer = 0.967 SH = 0.201136E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.676 2155.605 5.592 480.736 1.000 1.000 0.980

 W Kg/sec = 14.398 Wdry = 31.669 WH2O = 0.006 lbm/sec H2O = 0.100g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.159 2239.096 1.381 0.249 53.355 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61376.906 24852.438 3.544 831.557 234.665 619.754 2.641 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 177.14 -0.06 177.14 0.17 0.40 403.09

 MEAN 17.06 0.00 -0.02 177.14 -0.06 177.14 0.17 0.34

 HUB 12.51 0.00 -0.02 177.14 -0.06 177.14 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.47 50.47 15.00 388.08 426.65 5.49 478.21 465.18 3.51

 MEAN 61.11 47.20 13.91 320.92 366.62 5.49 478.21 465.18 3.51

 HUB 53.04 38.62 14.42 235.33 294.60 5.49 478.21 465.18 3.51

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 352.83 258.69 239.93 1074.40 0.33 7.29 6.52 16.04

 MEAN 18.04 359.70 265.89 242.26 1072.15 0.34 7.43 6.80 12.53

 HUB 15.00 392.85 306.63 245.58 1069.28 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.08 272.59 129.38 0.25 5338.12 0.92 0.88

 MEAN 339.28 253.13 73.39 0.24 4796.59 0.92 0.88 0.88 1.66

 HUB 282.17 246.79 24.47 0.23 4600.27 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 496.88 1.03 486.87 475.05 2.65

 MEAN 6.15 1.10 5.70 495.24 1.03 484.84 474.13 2.85

 HUB 6.13 1.10 5.59 494.65 1.03 482.24 473.84 3.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.15 28.34 24.20 4.14 0.93 0.53 1.80

 MEAN 47.66 16.85 12.70 4.15 0.95 0.48 2.22

 HUB 51.31 -5.69 -9.30 3.61 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.967 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 371.3333 265.3707 259.7438 1071.7762 0.3465 -0.0423 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1617 5.6768 484.5063 474.3372 2.8886 45.6139 35.4000 -10.2139

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 260.3981 63.7013 252.4863 1077.9845 0.2416 0.4692 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1541 5.9124 490.1390 474.1911 554.9116 0.0259 0.5582

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 258.9447 0.0000 258.9447 1078.0414 0.2402 0.4497 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8949 490.1996 474.1573 0.0000 0.0600 0.0697 0.4326

NASA/TM—2013-218094 O–253
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8352 6.1331 1.0967 495.5885 14.8525 175.7274 1.3622

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92408.906 0.614 165.415 319366.938 0.212034E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.845 EfDer = 0.975 SH = 0.221919E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.676 2155.605 6.133 495.588 1.000 1.000 0.980

 W Kg/sec = 14.398 Wdry = 31.669 WH2O = 0.007 lbm/sec H2O = 0.116g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.211 2205.296 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58284.625 24852.234 2.718 590.487 217.255 468.502 2.156

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.89 -0.08 236.89 0.22 0.42 395.47

 MEAN 18.08 0.00 -0.02 236.89 -0.08 236.89 0.22 0.38

 HUB 15.21 0.00 -0.02 236.89 -0.08 236.89 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.50 46.36 12.14 386.57 453.45 5.93 491.08 474.17 2.45

 MEAN 55.15 42.30 12.85 340.07 414.52 5.93 491.08 474.17 2.45

 HUB 50.38 37.84 12.54 286.12 371.52 5.93 491.08 474.17 2.45

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 326.66 207.24 252.51 1088.56 0.30 2.33 2.04 9.02

 MEAN 18.01 328.99 208.72 254.31 1086.86 0.30 2.40 2.13 7.35

 HUB 15.22 351.57 240.64 256.30 1085.20 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.12 308.30 176.89 0.28 4233.43 0.92 0.89

 MEAN 338.79 285.64 130.07 0.26 3760.49 0.92 0.89 0.89 1.59

 HUB 286.36 260.35 45.72 0.24 3664.48 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.66 1.09 6.26 508.39 1.03 499.81 481.35 1.84

 MEAN 6.60 1.08 6.20 506.96 1.02 498.26 480.59 1.94

 HUB 6.59 1.07 6.13 506.67 1.02 496.73 480.46 2.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.38 35.01 31.50 3.51 0.93 0.48 1.40

 MEAN 39.38 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.19 10.12 6.50 3.62 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 354.4999 209.3046 286.1150 1085.7416 0.3265 -0.1231 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6122 6.1475 497.2390 480.8135 2.0048 36.1870 30.6000 -5.5870

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 278.9829 59.1464 272.6411 1089.9298 0.2560 0.2893 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6095 6.3189 501.0833 480.7270 491.5697 0.0165 0.3972

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 288.7729 0.0000 288.7729 1089.4364 0.2651 0.2987 0.5911

NASA/TM—2013-218094 O–254
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2863 500.6366 480.7139 0.0000 0.0600 0.0471 0.2114

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8565 6.5967 1.0756 507.3376 11.7496 204.1237 1.5824

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73115.203 0.496 130.878 292036.344 0.225751E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.397 EfDer = 0.990 SH = 0.230733E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.676 2155.605 6.597 507.337 1.000 1.000 0.980

 W Kg/sec = 14.398 Wdry = 31.668 WH2O = 0.007 lbm/sec H2O = 0.127g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.809 2179.611 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55526.164 24852.148 2.669 545.479 204.373 424.468 2.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 244.30 -0.08 244.30 0.22 0.41 381.73

 MEAN 17.74 0.00 -0.02 244.30 -0.08 244.30 0.22 0.38

 HUB 15.05 0.00 -0.02 244.30 -0.08 244.30 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.10 46.36 10.74 377.54 449.76 6.37 502.54 480.69 1.74

 MEAN 53.80 43.40 10.40 333.68 413.62 6.37 502.54 480.69 1.74

 HUB 49.22 38.84 10.38 283.11 374.01 6.37 502.54 480.69 1.74

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.01 189.64 260.25 1099.97 0.29 2.26 1.98 8.75

 MEAN 17.51 326.28 194.76 261.78 1098.60 0.30 2.34 2.07 6.78

 HUB 14.85 350.82 231.63 263.48 1097.25 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 372.65 318.15 183.01 0.29 3758.40 0.92 0.91

 MEAN 329.32 294.34 134.56 0.27 3411.04 0.92 0.91 0.91 1.53

 HUB 279.35 267.77 47.71 0.24 3441.02 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.09 1.08 6.69 518.70 1.02 510.37 486.70 1.37

 MEAN 7.05 1.07 6.63 517.65 1.02 509.09 486.17 1.43

 HUB 7.05 1.07 6.58 517.74 1.02 507.85 486.24 1.48

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.08 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.65 27.20 23.50 3.70 0.94 0.43 1.62

 HUB 41.32 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.4532 196.0361 294.1071 1097.3960 0.3221 -0.1336 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0602 6.5767 507.9915 486.3819 1.4748 33.6853 31.5000 -2.1853

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 291.5375 63.5969 284.5164 1100.8562 0.2648 0.2180 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0588 6.7273 511.2001 486.3184 451.3937 0.0132 0.3615

 

NASA/TM—2013-218094 O–255
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 296.2009 0.0000 296.2009 1100.6119 0.2691 0.2684 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7065 510.9799 486.3036 0.0000 0.0600 0.0382 0.1698

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8743 7.0480 1.0684 518.0292 10.6921 213.8182 1.6575

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66542.930 0.479 119.114 292291.563 0.234574E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.347 EfDer = 0.998 SH = 0.239898E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.676 2155.605 7.048 518.029 1.000 1.000 0.980

 W Kg/sec = 14.398 Wdry = 31.668 WH2O = 0.008 lbm/sec H2O = 0.138g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.023 2157.001 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53080.047 24852.059 2.656 513.330 193.294 395.845 2.048

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 248.17 -0.09 248.17 0.23 0.40 362.53

 MEAN 16.97 0.00 -0.02 248.17 -0.09 248.17 0.23 0.37

 HUB 14.32 0.00 -0.02 248.17 -0.09 248.17 0.23 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.60 46.36 9.24 362.30 439.22 6.81 513.08 486.28 1.30

 MEAN 52.15 43.80 8.35 319.24 404.42 6.81 513.08 486.28 1.30

 HUB 47.36 37.84 9.52 269.38 366.33 6.81 513.08 486.28 1.30

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 313.13 169.35 263.39 1110.09 0.28 2.16 1.89 8.34

 MEAN 16.57 317.52 175.33 264.72 1108.91 0.29 2.24 1.97 6.35

 HUB 13.89 340.90 212.96 266.20 1107.75 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.16 322.33 185.80 0.29 3199.02 0.92 0.91

 MEAN 311.77 297.82 136.45 0.27 2907.31 0.92 0.91 0.91 1.48

 HUB 261.29 270.55 48.32 0.24 2959.28 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.49 1.06 7.10 527.70 1.02 519.82 491.14 1.07

 MEAN 7.45 1.06 7.04 526.82 1.02 518.72 490.72 1.11

 HUB 7.46 1.06 6.99 526.97 1.02 517.64 490.82 1.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.74 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.52 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.66 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 339.6429 176.3136 290.2943 1108.0198 0.3065 -0.1079 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4637 6.9989 517.8953 490.8999 1.1345 31.2729 32.4000 1.1271

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 293.4195 65.8054 285.9452 1110.5311 0.2642 0.1654 2.2705

 

NASA/TM—2013-218094 O–256
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4628 7.1139 520.2462 490.8582 432.2457 0.0122 0.3305

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 290.9632 0.0000 290.9632 1110.6484 0.2620 0.2380 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1096 520.3614 490.8375 0.0000 0.0600 0.0370 0.1552

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.4523 1.0574 527.1627 9.1342 235.2420 1.8236

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 56854.406 0.451 101.771 301005.406 0.243902E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.478 EfDer = 1.000 SH = 0.249854E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.676 2155.605 7.452 527.163 1.000 1.000 0.980

 W Kg/sec = 14.398 Wdry = 31.668 WH2O = 0.008 lbm/sec H2O = 0.150g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.990 2138.233 1.381 0.249 53.356 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50982.109 24851.963 2.764 509.668 184.416 384.739 2.086

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 240.07 -0.08 240.07 0.22 0.38 341.83

 MEAN 15.91 0.00 -0.02 240.07 -0.08 240.07 0.22 0.34

 HUB 13.07 0.00 -0.02 240.07 -0.08 240.07 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.14 47.36 7.78 344.62 420.07 7.22 522.53 490.82 1.02

 MEAN 51.28 44.80 6.48 299.34 383.78 7.22 522.53 490.82 1.02

 HUB 45.69 38.84 6.85 245.86 343.69 7.22 522.53 490.82 1.02

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.12 156.01 255.22 1119.23 0.27 2.05 1.78 7.43

 MEAN 15.50 301.48 158.37 256.54 1118.00 0.27 2.13 1.86 5.75

 HUB 12.59 320.25 189.78 257.96 1116.80 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.47 313.15 181.46 0.28 2800.37 0.92 0.91

 MEAN 291.53 289.04 133.16 0.26 2455.63 0.92 0.91 0.91 1.46

 HUB 236.83 262.22 47.05 0.23 2390.44 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.86 1.05 7.48 535.63 1.02 528.44 494.90 0.87

 MEAN 7.81 1.05 7.43 534.58 1.01 527.28 494.42 0.90

 HUB 7.80 1.05 7.37 534.39 1.01 526.15 494.34 0.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.44 35.41 31.50 3.91 0.93 0.39 1.40

 MEAN 31.69 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.34 10.34 6.50 3.84 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 333.5288 161.2714 291.9470 1116.5597 0.2987 -0.1965 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8120 7.3491 525.9297 494.5608 0.9350 28.9162 33.0000 4.0838

 

NASA/TM—2013-218094 O–257
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 300.1678 68.5436 292.2370 1118.3615 0.2684 0.0179 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8092 7.4328 527.6278 494.5284 410.5396 0.0271 0.2994

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 291.9957 0.0000 291.9957 1118.7689 0.2610 0.2115 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4470 528.0165 494.5125 0.0000 0.0600 0.0423 0.0538

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8741 7.8032 1.0471 534.8654 7.7032 261.9484 2.0306

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47953.531 0.421 85.838 317381.313 0.254100E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1126 Tt4 = 534.8654 T1 = 480.7365

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 336874.97 603.0157 80.1588 1.3953 0.8549 13.9067 1.1126 37.3740

NASA/TM—2013-218094 O–258
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.160 EfDer = 0.995 SH = 0.336511E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.692 1971.592 6.513 491.412 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.678 WH2O = 0.013 lbm/sec H2O = 0.190g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.200 2025.591 1.381 0.249 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67688.727 31139.961 3.257 831.557 255.304 619.754 2.428

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 195.36 -0.07 195.36 0.18 0.38 364.66

 MEAN 17.06 0.00 -0.02 195.36 -0.07 195.36 0.18 0.33

 HUB 12.51 0.00 -0.02 195.36 -0.07 195.36 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.18 50.47 10.71 354.95 405.22 6.37 488.35 473.01 4.45

 MEAN 56.36 47.20 9.16 293.53 352.65 6.37 488.35 473.01 4.45

 HUB 47.78 38.62 9.16 215.24 290.73 6.37 488.35 473.01 4.45

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 340.74 211.24 267.36 1082.33 0.31 7.29 6.52 16.04

 MEAN 18.04 353.48 229.13 269.16 1080.86 0.33 7.43 6.80 12.53

 HUB 15.00 394.42 285.45 272.19 1078.62 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.95 303.53 143.70 0.28 4359.32 0.92 0.91

 MEAN 310.32 281.13 81.19 0.26 4133.71 0.92 0.91 0.91 1.42

 HUB 258.08 273.56 27.36 0.25 4282.52 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.06 1.08 6.59 503.46 1.02 494.14 480.21 3.73

 MEAN 7.03 1.08 6.53 502.84 1.02 492.80 479.89 3.90

 HUB 7.05 1.08 6.43 503.25 1.02 490.75 480.21 4.17

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.31 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.41 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.36 -5.74 -9.30 3.56 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.4070 228.6834 288.8384 1080.2893 0.3410 -0.0596 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0374 6.5001 492.2809 480.1075 3.9705 38.3699 35.4000 -2.9699

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 291.8511 71.3957 282.9836 1084.7325 0.2691 0.3352 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0350 6.6943 496.3413 479.9576 554.9116 0.0145 0.4355

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 289.7169 0.0000 289.7169 1084.8337 0.2671 0.3473 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6867 496.4411 479.9377 0.0000 0.0600 0.0396 0.3206

NASA/TM—2013-218094 O–259
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8756 7.0218 1.0782 503.1832 11.7716 200.8568 1.5570

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73280.594 0.582 164.369 394686.750 0.347880E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.307 EfDer = 1.000 SH = 0.357599E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.692 1971.592 7.022 503.183 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.678 WH2O = 0.014 lbm/sec H2O = 0.210g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.841 2001.760 1.381 0.249 53.360 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65134.176 31139.697 2.464 590.487 239.618 468.502 1.955

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 264.73 -0.09 264.73 0.24 0.41 358.97

 MEAN 18.08 0.00 -0.02 264.73 -0.09 264.73 0.24 0.38 

 HUB 15.21 0.00 -0.02 264.73 -0.09 264.73 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.18 46.36 6.82 353.57 441.77 6.74 497.55 479.93 3.46 

 MEAN 49.61 42.30 7.31 311.04 408.52 6.74 497.55 479.93 3.46

 HUB 44.68 37.84 6.84 261.69 372.31 6.74 497.55 479.93 3.46

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.96 151.25 285.35 1092.35 0.30 2.33 2.04 9.02

 MEAN 18.01 329.62 163.13 286.42 1091.52 0.30 2.40 2.13 7.35

 HUB 15.22 356.33 210.29 287.67 1090.71 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.33 348.51 200.09 0.32 3090.33 0.92 0.91

 MEAN 309.87 321.83 146.74 0.29 2939.59 0.92 0.91 0.91 1.38

 HUB 261.92 292.26 51.63 0.27 3202.62 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.43 1.06 6.99 511.72 1.02 503.35 484.69 2.88

 MEAN 7.41 1.05 6.96 511.31 1.02 502.58 484.47 2.95

 HUB 7.44 1.06 6.92 512.03 1.02 501.84 484.91 3.02

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.93 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.66 27.13 23.50 3.63 0.93 0.33 1.63

 HUB 36.17 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 361.9608 163.5865 322.8856 1089.9723 0.3321 -0.1639 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4188 6.8804 501.1661 484.7328 3.0895 26.8686 30.6000 3.7314

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 317.1510 67.2383 309.9416 1092.6281 0.2903 0.0960 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4166 7.0008 503.6101 484.6465 491.5697 0.0147 0.2547

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 328.4280 0.0000 328.4280 1091.9888 0.3008 0.1472 0.5911

NASA/TM—2013-218094 O–260
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9596 503.0255 484.6461 0.0000 0.0600 0.0414 0.0080

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8713 7.4042 1.0544 511.6888 8.5059 251.3762 1.9487

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 52958.250 0.429 118.786 363831.563 0.361150E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.381 EfDer = 0.994 SH = 0.365813E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.692 1971.592 7.404 511.689 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.677 WH2O = 0.015 lbm/sec H2O = 0.222g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.268 1985.053 1.381 0.249 53.360 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62958.566 31139.602 2.380 545.479 229.160 424.468 1.852

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 277.01 -0.10 277.01 0.25 0.40 347.66

 MEAN 17.74 0.00 -0.02 277.01 -0.10 277.01 0.25 0.38

 HUB 15.05 0.00 -0.02 277.01 -0.10 277.01 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.27 46.36 4.91 345.31 442.76 7.09 505.53 484.58 2.74

 MEAN 47.78 43.40 4.38 305.20 412.23 7.09 505.53 484.58 2.74

 HUB 43.08 38.84 4.24 258.94 379.25 7.09 505.53 484.58 2.74

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 325.93 129.86 298.94 1099.82 0.30 2.26 1.98 8.75

 MEAN 17.51 333.47 146.45 299.59 1099.36 0.30 2.34 2.07 6.78

 HUB 14.85 361.14 200.41 300.43 1098.93 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 340.84 365.89 210.98 0.33 2574.45 0.92 0.91

 MEAN 301.21 337.20 154.75 0.31 2565.60 0.92 0.91 0.91 1.32

 HUB 255.50 305.43 55.09 0.28 2977.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.75 1.05 7.30 518.80 1.01 510.27 488.38 2.37

 MEAN 7.75 1.05 7.28 518.78 1.01 509.85 488.38 2.40

 HUB 7.80 1.05 7.25 519.92 1.02 509.44 489.01 2.43

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.48 35.21 31.50 3.71 0.93 0.28 1.40

 MEAN 26.05 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.71 10.39 6.50 3.89 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 368.1964 147.4151 337.3980 1097.6642 0.3354 -0.1766 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7626 7.1883 508.2791 488.6295 2.5178 23.6014 31.5000 7.8986

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 337.1089 73.5380 328.9902 1099.5662 0.3066 0.0002 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7574 7.2742 510.0398 488.5644 451.3937 0.0205 0.2126

 

NASA/TM—2013-218094 O–261
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 342.9506 0.0000 342.9506 1099.2185 0.3120 0.0914 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2408 509.7208 488.5435 0.0000 0.0600 0.0571 -0.0674

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8405 7.7393 1.0453 519.1664 7.4779 272.1880 2.1100

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46562.656 0.401 104.441 366472.781 0.369143E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.783 EfDer = 0.974 SH = 0.373819E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.692 1971.592 7.739 519.166 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.677 WH2O = 0.015 lbm/sec H2O = 0.233g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.424 1970.706 1.381 0.249 53.360 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61214.641 31139.502 2.324 513.330 220.835 395.845 1.792

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 286.20 -0.10 286.20 0.26 0.40 331.22

 MEAN 16.97 0.00 -0.02 286.20 -0.10 286.20 0.26 0.37

 HUB 14.32 0.00 -0.02 286.20 -0.10 286.20 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.19 46.36 2.83 331.38 437.93 7.39 512.59 488.47 2.24

 MEAN 45.58 43.80 1.78 291.99 408.93 7.39 512.59 488.47 2.24

 HUB 40.74 37.84 2.90 246.38 377.71 7.39 512.59 488.47 2.24

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 325.93 106.28 308.12 1106.16 0.29 2.16 1.89 8.34

 MEAN 16.57 332.82 125.00 308.45 1105.96 0.30 2.24 1.97 6.35

 HUB 13.89 358.56 181.88 309.01 1105.78 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.84 377.77 218.56 0.34 2008.39 0.92 0.89

 MEAN 285.16 347.55 160.16 0.31 2073.46 0.92 0.89 0.89 1.26

 HUB 238.98 314.24 57.10 0.28 2527.70 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.01 1.03 7.55 524.72 1.01 516.19 491.32 2.02

 MEAN 8.02 1.04 7.54 524.90 1.01 516.00 491.42 2.03

 HUB 8.08 1.04 7.52 526.15 1.01 515.83 492.08 2.04

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.03 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 22.06 27.44 23.50 3.94 0.91 0.24 1.62

 HUB 30.48 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 361.5781 125.7059 339.0232 1104.6212 0.3273 -0.1443 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0317 7.4646 514.7557 491.6393 2.1029 20.3442 32.4000 12.0558

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 345.5186 77.4897 336.7172 1105.6014 0.3125 -0.0621 2.2705

 

NASA/TM—2013-218094 O–262
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0224 7.5040 515.6674 491.5956 432.2457 0.0284 0.1760

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 343.2524 0.0000 343.2524 1105.7339 0.3104 0.0376 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4859 515.7927 491.5448 0.0000 0.0600 0.0811 -0.0982

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7707 7.9960 1.0332 525.2542 6.0881 313.1230 2.4273

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37912.016 0.359 85.037 379726.313 0.377108E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.624 EfDer = 0.940 SH = 0.382055E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.692 1971.592 7.996 525.254 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.677 WH2O = 0.015 lbm/sec H2O = 0.244g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.429 1959.252 1.381 0.249 53.361 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59861.477 31139.402 2.371 509.668 214.998 384.739 1.789

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 281.88 -0.10 281.88 0.25 0.38 313.22

 MEAN 15.91 0.00 -0.02 281.88 -0.10 281.88 0.25 0.35

 HUB 13.07 0.00 -0.02 281.88 -0.10 281.88 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.20 47.36 0.84 315.20 422.93 7.65 518.87 491.47 1.89

 MEAN 44.18 44.80 -0.62 273.79 393.03 7.65 518.87 491.47 1.89

 HUB 38.59 38.84 -0.25 224.87 360.65 7.65 518.87 491.47 1.89

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 317.41 90.80 304.14 1112.01 0.29 2.05 1.78 7.43

 MEAN 15.50 322.76 107.14 304.46 1111.81 0.29 2.13 1.86 5.75

 HUB 12.59 344.31 159.73 305.02 1111.61 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 308.66 374.12 217.87 0.34 1630.68 0.92 0.86 

 MEAN 266.64 343.71 159.50 0.31 1662.01 0.92 0.86 0.86 1.23

 HUB 216.62 310.28 56.89 0.28 2012.23 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.21 1.03 7.77 529.76 1.01 521.67 493.71 1.74

 MEAN 8.22 1.03 7.76 529.85 1.01 521.48 493.76 1.75

 HUB 8.26 1.03 7.74 530.81 1.01 521.29 494.25 1.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.62 35.62 31.50 4.12 0.93 0.19 1.40

 MEAN 19.39 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.64 10.56 6.50 4.06 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.940 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 364.4684 109.1078 347.7538 1109.6593 0.3285 -0.2488 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2209 7.6367 519.4736 493.9483 1.8553 17.4193 33.0000 15.5807

 

NASA/TM—2013-218094 O–263
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 361.2358 82.4885 351.6915 1109.8646 0.3255 -0.2731 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1954 7.6230 519.6617 493.8955 410.5396 0.0735 0.1440

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 351.4503 0.0000 351.4503 1110.4624 0.3165 0.0040 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6390 520.2216 493.8539 0.0000 0.0600 0.1045 -0.2395

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6787 8.1806 1.0231 530.1399 4.8860 365.1613 2.8307

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30428.369 0.319 68.251 402383.688 0.385557E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0788 Tt4 = 530.1399 T1 = 491.4120

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 241141.89 540.8846 87.1996 1.2561 0.8234 9.1598 1.0788 37.3740

NASA/TM—2013-218094 O–264
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.578 EfDer = 0.999 SH = 0.619759E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.723 1793.828 7.939 506.410 1.000 1.000 0.980

 W Kg/sec = 22.147 Wdry = 48.693 WH2O = 0.030 lbm/sec H2O = 0.414g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 89.141 1815.466 1.380 0.249 53.368 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70310.383 38221.488 3.186 831.557 261.041 619.754 2.374

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.93 -0.07 202.93 0.19 0.35 326.83

 MEAN 17.06 0.00 -0.02 202.93 -0.07 202.93 0.19 0.31

 HUB 12.51 0.00 -0.02 202.93 -0.07 202.93 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.86 50.47 7.39 322.94 381.47 7.75 503.11 483.64 5.57

 MEAN 52.78 47.20 5.58 267.06 335.47 7.75 503.11 483.64 5.57

 HUB 43.99 38.62 5.37 195.83 282.06 7.75 503.11 483.64 5.57

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.03 171.89 280.56 1095.83 0.30 7.29 6.52 16.04

 MEAN 18.04 343.81 197.10 281.70 1094.99 0.31 7.43 6.80 12.53

 HUB 15.00 387.30 263.16 284.17 1093.30 0.35 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.94 318.64 151.06 0.29 3547.51 0.92 0.91

 MEAN 282.34 294.31 85.24 0.27 3556.10 0.92 0.91 0.91 1.27

 HUB 234.81 285.58 28.35 0.26 3948.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.41 1.06 7.91 515.32 1.02 506.63 488.78 5.03

 MEAN 8.41 1.06 7.86 515.34 1.02 505.86 488.84 5.15

 HUB 8.47 1.07 7.77 516.33 1.02 504.29 489.51 5.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.49 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 34.98 16.84 12.70 4.14 0.92 0.26 2.22

 HUB 42.80 -5.70 -9.30 3.60 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 360.7850 196.7177 302.4367 1094.3005 0.3297 -0.0736 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4250 7.8220 505.2199 489.0573 5.2573 33.0417 35.4000 2.3583

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.6434 75.2590 298.2961 1097.3810 0.2803 0.2279 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4229 7.9814 508.0703 488.8950 554.9116 0.0136 0.3486

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 305.3287 0.0000 305.3287 1097.4980 0.2782 0.2522 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9741 508.1842 488.8715 0.0000 0.0600 0.0385 0.2155

NASA/TM—2013-218094 O–265
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8729 8.4084 1.0591 515.6646 9.2552 222.8898 1.7278

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57677.258 0.553 158.809 474141.594 0.632340E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.133 EfDer = 0.987 SH = 0.642858E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.723 1793.828 8.408 515.664 1.000 1.000 0.980

 W Kg/sec = 22.147 Wdry = 48.692 WH2O = 0.031 lbm/sec H2O = 0.440g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.931 1799.099 1.380 0.249 53.369 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68607.383 38221.141 2.374 590.487 248.717 468.502 1.884

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.85 -0.10 278.85 0.25 0.39 322.63

 MEAN 18.08 0.00 -0.02 278.85 -0.10 278.85 0.25 0.36

 HUB 15.21 0.00 -0.02 278.85 -0.10 278.85 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.09 46.36 2.73 321.69 425.80 8.05 509.43 488.83 4.72

 MEAN 45.43 42.30 3.13 283.00 397.37 8.05 509.43 488.83 4.72

 HUB 40.50 37.84 2.66 238.10 366.73 8.05 509.43 488.83 4.72

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.96 105.74 304.09 1102.44 0.29 2.33 2.04 9.02

 MEAN 18.01 329.15 125.35 304.35 1102.30 0.30 2.40 2.13 7.35

 HUB 15.22 355.51 182.96 304.81 1102.17 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.66 371.80 213.91 0.34 2161.24 0.92 0.90

 MEAN 281.93 342.26 156.58 0.31 2259.35 0.92 0.90 0.90 1.25

 HUB 238.30 309.79 55.34 0.28 2786.70 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.70 1.03 8.21 521.09 1.01 512.78 491.76 4.26

 MEAN 8.72 1.04 8.20 521.34 1.01 512.65 491.91 4.28

 HUB 8.79 1.05 8.19 522.66 1.01 512.52 492.66 4.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.17 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.39 27.22 23.50 3.72 0.91 0.24 1.63

 HUB 30.97 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.7918 125.7057 343.5138 1100.4846 0.3324 -0.1938 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7300 8.0954 510.9640 492.1976 4.4995 20.0996 30.6000 10.5004

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 339.3565 71.9460 331.6423 1102.0972 0.3079 -0.0443 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7217 8.1740 512.4594 492.1026 491.5697 0.0254 0.1609

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 352.0259 0.0000 352.0259 1101.3381 0.3196 0.0235 0.5911

NASA/TM—2013-218094 O–266
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1103 511.7567 492.1022 0.0000 0.0600 0.0714 -0.1627

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7982 8.6969 1.0343 521.6993 6.0349 303.3949 2.3519

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37613.832 0.368 103.566 439664.781 0.646622E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.254 EfDer = 0.946 SH = 0.651441E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.723 1793.828 8.697 521.699 1.000 1.000 0.980

 W Kg/sec = 22.147 Wdry = 48.692 WH2O = 0.032 lbm/sec H2O = 0.454g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.592 1788.664 1.380 0.249 53.369 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67360.078 38221.012 2.255 545.479 241.870 424.468 1.755

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 296.37 -0.10 296.37 0.27 0.39 313.26

 MEAN 17.74 0.00 -0.02 296.37 -0.10 296.37 0.27 0.37

 HUB 15.05 0.00 -0.02 296.37 -0.10 296.37 0.27 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.68 46.36 0.32 314.18 431.98 8.28 514.65 491.96 4.06

 MEAN 43.15 43.40 -0.25 277.68 406.20 8.28 514.65 491.96 4.06

 HUB 38.49 38.84 -0.35 235.59 378.67 8.28 514.65 491.96 4.06

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.86 80.41 324.03 1106.71 0.30 2.26 1.98 8.75

 MEAN 17.51 340.61 105.84 323.75 1107.01 0.31 2.34 2.07 6.78

 HUB 14.85 366.74 172.19 323.81 1107.32 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 310.11 397.19 229.70 0.36 1594.89 0.92 0.87

 MEAN 274.05 364.84 168.21 0.33 1854.72 0.92 0.87 0.87 1.19

 HUB 232.46 329.37 60.27 0.30 2558.60 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.91 1.02 8.37 525.71 1.01 516.76 494.07 3.81

 MEAN 8.94 1.03 8.38 526.36 1.01 517.05 494.41 3.78

 HUB 9.04 1.04 8.39 528.13 1.01 517.34 495.35 3.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.94 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.10 27.45 23.50 3.95 0.90 0.18 1.62

 HUB 28.00 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.946 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.5140 106.5356 365.2959 1104.9337 0.3444 -0.2082 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9576 8.2611 515.1135 494.7067 3.9951 16.2589 31.5000 15.2411

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 367.2376 80.1104 358.3933 1105.7924 0.3321 -0.1493 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9414 8.2926 515.9097 494.6373 451.3937 0.0377 0.1165

 

NASA/TM—2013-218094 O–267
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 374.5201 0.0000 374.5201 1105.3263 0.3388 -0.0411 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2325 515.4763 494.5993 0.0000 0.0600 0.1022 -0.2522

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6737 8.9037 1.0238 526.7295 5.0305 344.5878 2.6712

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31355.488 0.326 86.334 445227.188 0.655060E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.343 EfDer = 0.887 SH = 0.659793E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.723 1793.828 8.904 526.729 1.000 1.000 0.980

 W Kg/sec = 22.147 Wdry = 48.691 WH2O = 0.032 lbm/sec H2O = 0.464g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.062 1780.102 1.380 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 66658.594 38220.887 2.162 513.330 237.391 395.845 1.667

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 311.65 -0.11 311.65 0.28 0.39 299.18

 MEAN 16.97 0.00 -0.02 311.65 -0.11 311.65 0.28 0.37

 HUB 14.32 0.00 -0.02 311.65 -0.11 311.65 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.06 46.36 -2.30 301.50 433.70 8.43 518.94 494.43 3.59

 MEAN 40.46 43.80 -3.34 265.66 409.59 8.43 518.94 494.43 3.59

 HUB 35.74 37.84 -2.10 224.17 383.96 8.43 518.94 494.43 3.59

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 344.15 53.16 340.02 1109.90 0.31 2.16 1.89 8.34

 MEAN 16.57 349.14 82.08 339.35 1110.56 0.31 2.24 1.97 6.35

 HUB 13.89 372.40 153.77 339.17 1111.20 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.55 417.57 242.39 0.38 1005.72 0.92 0.81

 MEAN 259.45 382.91 177.37 0.34 1362.24 0.92 0.81 0.81 1.14

 HUB 217.44 345.09 63.67 0.31 2137.41 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.03 1.01 8.46 529.26 1.00 519.75 495.74 3.50

 MEAN 9.08 1.02 8.48 530.15 1.01 520.37 496.19 3.44

 HUB 9.17 1.03 8.50 532.10 1.01 520.97 497.18 3.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.89 35.48 31.50 3.98 0.93 0.08 1.40

 MEAN 13.60 27.59 23.50 4.09 0.89 0.13 1.62

 HUB 24.39 10.63 6.50 4.13 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.887 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.7773 82.5437 373.7714 1108.8168 0.3452 -0.1708 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0869 8.3772 518.7473 496.4453 3.5986 12.4533 32.4000 19.9467

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 383.3309 85.9699 373.5663 1108.7850 0.3457 -0.2028 2.2705

 

NASA/TM—2013-218094 O–268
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0633 8.3534 518.7129 496.4076 432.2457 0.0485 0.0804

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 381.7596 0.0000 381.7596 1108.8885 0.3443 -0.0916 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3122 518.8093 496.3175 0.0000 0.0600 0.1311 -0.2698

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4678 9.0125 1.0122 530.5012 3.7720 425.3912 3.2976

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23512.447 0.269 64.739 463846.594 0.663362E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.210 EfDer = 0.824 SH = 0.668313E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.723 1793.828 9.012 530.501 1.000 1.000 0.980

 W Kg/sec = 22.147 Wdry = 48.691 WH2O = 0.033 lbm/sec H2O = 0.473g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.370 1773.763 1.380 0.249 53.370 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66318.391 38220.758 2.165 509.668 235.367 384.739 1.635 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 312.29 -0.11 312.29 0.28 0.38 283.57

 MEAN 15.91 0.00 -0.02 312.29 -0.11 312.29 0.28 0.36

 HUB 13.07 0.00 -0.02 312.29 -0.11 312.29 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.57 47.36 -4.79 286.78 424.07 8.54 522.68 496.14 3.22

 MEAN 38.59 44.80 -6.21 249.10 399.54 8.54 522.68 496.14 3.22

 HUB 33.24 38.84 -5.60 204.60 373.40 8.54 522.68 496.14 3.22

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 343.02 35.08 341.23 1112.97 0.31 2.05 1.78 7.43

 MEAN 15.50 346.31 62.94 340.54 1113.70 0.31 2.13 1.86 5.75

 HUB 12.59 365.30 132.52 340.41 1114.40 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.83 420.51 245.76 0.38 631.29 0.92 0.75

 MEAN 242.60 385.03 179.66 0.35 977.18 0.92 0.75 0.75 1.10

 HUB 197.09 346.48 64.56 0.31 1669.88 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.09 1.01 8.51 532.09 1.00 522.65 496.96 3.22

 MEAN 9.13 1.01 8.54 532.96 1.00 523.33 497.37 3.16

 HUB 9.21 1.02 8.56 534.70 1.01 523.99 498.23 3.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.87 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.47 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.27 10.74 6.50 4.24 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.824 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 395.5756 64.0972 390.3481 1110.8883 0.3561 -0.2830 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1287 8.3725 520.6930 497.6367 3.3991 9.3251 33.0000 23.6749

 

NASA/TM—2013-218094 O–269
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 408.7989 93.3496 397.9980 1109.9849 0.3683 -0.4403 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0742 8.2731 519.8392 497.5880 410.5396 0.1106 0.0535

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 397.5820 0.0000 397.5820 1110.7625 0.3579 -0.1010 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2961 520.5646 497.5157 0.0000 0.0600 0.1449 -0.4020

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2419 9.0535 1.0045 533.2455 2.7445 538.5676 4.1749

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17108.584 0.217 47.107 493811.656 0.671954E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0530 Tt4 = 533.2455 T1 = 506.4096

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 167267.61 460.5552 89.1407 1.1404 0.6954 5.5778 1.0530 37.3740

NASA/TM—2013-218094 O–270
 100μm, ISA +18R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.145 EfDer = 0.957 SH = 0.454452E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.819 2405.688 4.265 457.737 1.000 1.000 0.980

 W Kg/sec = 12.191 Wdry = 26.818 WH2O = 0.001 lbm/sec H2O = 0.018g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.842 2560.871 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65038.973 21043.451 3.271 831.557 254.197 619.754 2.438

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 187.71 -0.06 187.71 0.18 0.45 461.02

 MEAN 17.06 0.00 -0.02 187.71 -0.06 187.71 0.18 0.39

 HUB 12.51 0.00 -0.02 187.71 -0.06 187.71 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.57 50.47 16.10 433.10 472.09 4.17 454.90 448.21 1.74

 MEAN 62.34 47.20 15.14 358.15 404.42 4.17 454.90 448.21 1.74

 HUB 54.45 38.62 15.83 262.63 322.87 4.17 454.90 448.21 1.74

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 389.08 297.03 251.31 1051.48 0.37 7.29 6.52 16.04

 MEAN 18.04 394.32 301.11 254.60 1048.45 0.38 7.43 6.80 12.53

 HUB 15.00 427.87 340.45 259.17 1044.69 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 433.10 285.78 136.07 0.27 6128.98 0.92 0.88

 MEAN 378.64 266.14 77.53 0.25 5431.98 0.92 0.88 0.88 1.74

 HUB 314.90 260.43 25.54 0.25 5107.52 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 478.44 1.05 466.26 462.20 1.11

 MEAN 4.83 1.13 4.39 476.08 1.04 463.58 460.71 1.23

 HUB 4.80 1.12 4.28 474.99 1.04 460.26 460.03 1.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.77 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.78 16.94 12.70 4.24 0.95 0.51 2.22

 HUB 52.72 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 406.0583 300.5277 273.0686 1048.0610 0.3874 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8413 4.3708 463.2391 460.9779 1.2439 47.7408 35.4000 -12.3408

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 271.0790 66.3142 262.8426 1056.3409 0.2566 0.5077 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8299 4.6164 470.5904 460.9021 554.9116 0.0344 0.5999

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 269.9224 0.0000 269.9224 1056.3879 0.2555 0.4799 1.3089

NASA/TM—2013-218094 O–271
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5966 470.6406 460.8587 0.0000 0.0600 0.0829 0.4652

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8202 4.8073 1.1272 476.5003 18.7637 169.5071 1.3140

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 116659.930 0.622 176.808 281326.375 0.461030E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.673 EfDer = 0.961 SH = 0.467062E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.819 2405.688 4.807 476.500 1.000 1.000 0.980

 W Kg/sec = 12.191 Wdry = 26.818 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.603 2509.954 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60715.422 21043.439 2.566 590.487 230.083 468.502 2.036

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 246.77 -0.08 246.77 0.23 0.47 450.10

 MEAN 18.08 0.00 -0.02 246.77 -0.08 246.77 0.23 0.43

 HUB 15.21 0.00 -0.02 246.77 -0.08 246.77 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.23 46.36 13.87 431.42 497.08 4.63 471.60 460.85 0.92

 MEAN 56.97 42.30 14.67 379.53 452.77 4.63 471.60 460.85 0.92

 HUB 52.31 37.84 14.47 319.31 403.62 4.63 471.60 460.85 0.92

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 357.96 246.17 259.87 1070.36 0.33 2.33 2.04 9.02

 MEAN 18.01 358.03 243.50 262.47 1067.96 0.34 2.40 2.13 7.35

 HUB 15.22 379.98 271.99 265.35 1065.59 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 428.69 317.57 182.52 0.30 5028.51 0.92 0.88

 MEAN 378.09 294.97 134.59 0.28 4386.99 0.92 0.88 0.88 1.69

 HUB 319.59 269.59 47.60 0.25 4141.72 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 493.48 1.04 483.18 471.11 0.60

 MEAN 5.30 1.10 4.91 491.31 1.03 481.01 469.86 0.65

 HUB 5.27 1.10 4.83 490.49 1.03 478.87 469.39 0.70

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.45 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.85 27.15 23.50 3.65 0.95 0.51 1.63

 HUB 45.71 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 383.3246 244.1849 295.4852 1066.7675 0.3593 -0.1093 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3121 4.8641 479.9431 470.1226 0.6727 39.5699 30.6000 -8.9699

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 285.9402 60.6214 279.4402 1072.5756 0.2666 0.3578 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3063 5.0538 485.1847 470.0801 491.5697 0.0241 0.4553

 

NASA/TM—2013-218094 O–272
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 296.3677 0.0000 296.3677 1072.0277 0.2765 0.3490 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0204 484.6964 470.0494 0.0000 0.0600 0.0626 0.2762

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8368 5.2905 1.1005 491.7599 15.2600 191.2210 1.4823

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 94887.352 0.516 143.810 255454.859 0.468908E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.679 EfDer = 0.976 SH = 0.468987E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.819 2405.688 5.291 491.760 1.000 1.000 0.980

 W Kg/sec = 12.191 Wdry = 26.818 WH2O = 0.001 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.558 2470.705 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56933.711 21043.439 2.568 545.479 212.390 424.468 1.999

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 250.50 -0.09 250.50 0.23 0.46 432.72

 MEAN 17.74 0.00 -0.02 250.50 -0.09 250.50 0.23 0.42

 HUB 15.05 0.00 -0.02 250.50 -0.09 250.50 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.27 46.36 12.91 421.34 490.26 5.10 486.71 470.04 0.53

 MEAN 56.08 43.40 12.68 372.39 448.88 5.10 486.71 470.04 0.53

 HUB 51.60 38.84 12.76 315.95 403.27 5.10 486.71 470.04 0.53

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 350.04 230.13 263.76 1085.88 0.32 2.26 1.98 8.75

 MEAN 17.51 352.07 230.59 266.04 1083.83 0.32 2.34 2.07 6.78

 HUB 14.85 375.93 263.06 268.56 1081.82 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.88 322.61 185.75 0.30 4560.58 0.92 0.89

 MEAN 367.53 299.21 136.93 0.28 4038.43 0.92 0.89 0.89 1.64

 HUB 311.75 272.94 48.69 0.25 3907.79 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.85 1.11 5.45 507.16 1.03 497.30 478.56 0.37

 MEAN 5.78 1.09 5.38 505.40 1.03 495.43 477.63 0.40

 HUB 5.76 1.09 5.31 504.95 1.03 493.59 477.40 0.42

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.10 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.92 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.41 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 378.5260 232.1067 299.0124 1082.5992 0.3496 -0.1172 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7929 5.3290 494.3142 477.8604 0.4091 37.8202 31.5000 -6.3202

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 294.3030 64.2002 287.2152 1087.5767 0.2706 0.3059 2.3726

 

NASA/TM—2013-218094 O–273
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7892 5.5056 498.8710 477.8309 451.3937 0.0187 0.4299

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 299.2657 0.0000 299.2657 1087.3102 0.2752 0.3335 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4837 498.6342 477.8026 0.0000 0.0600 0.0500 0.2537

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8571 5.7761 1.0918 505.8357 14.0763 196.7151 1.5249

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 87535.805 0.506 132.668 253844.234 0.470779E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.084 EfDer = 0.986 SH = 0.470853E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.819 2405.688 5.776 505.836 1.000 1.000 0.980

 W Kg/sec = 12.191 Wdry = 26.818 WH2O = 0.001 lbm/sec H2O = 0.023g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.403 2436.086 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53601.109 21043.438 2.602 513.330 197.303 395.845 2.006

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.60 -0.09 250.60 0.23 0.44 409.43

 MEAN 16.97 0.00 -0.02 250.60 -0.09 250.60 0.23 0.40

 HUB 14.32 0.00 -0.02 250.60 -0.09 250.60 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.22 46.36 11.86 404.34 475.77 5.57 500.79 477.79 0.33

 MEAN 54.88 43.80 11.08 356.28 435.66 5.57 500.79 477.79 0.33

 HUB 50.19 37.84 12.35 300.63 391.45 5.57 500.79 477.79 0.33

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 337.10 210.76 263.10 1099.78 0.31 2.16 1.89 8.34

 MEAN 16.57 339.05 211.31 265.15 1097.93 0.31 2.24 1.97 6.35

 HUB 13.89 361.43 243.18 267.39 1096.11 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 396.36 321.98 185.60 0.29 3980.76 0.92 0.90

 MEAN 347.94 298.28 136.63 0.27 3503.70 0.92 0.90 0.90 1.60

 HUB 291.60 271.73 48.42 0.25 3379.05 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.29 1.09 5.90 519.27 1.03 510.14 484.71 0.25

 MEAN 6.23 1.08 5.84 517.66 1.02 508.42 483.91 0.26

 HUB 6.21 1.08 5.77 517.24 1.02 506.74 483.71 0.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.70 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.55 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.29 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 360.1472 212.4991 290.7750 1097.0625 0.3283 -0.0928 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2415 5.7981 507.6320 484.1063 0.2669 36.1594 32.4000 -3.7594

 

NASA/TM—2013-218094 O–274
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.0544 65.4993 284.6148 1100.9125 0.2653 0.2685 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2396 5.9455 511.2028 484.0884 432.2457 0.0146 0.4083

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.7179 0.0000 289.7179 1101.0227 0.2631 0.3191 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9396 511.3121 484.0627 0.0000 0.0600 0.0414 0.2542

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8703 6.2286 1.0783 518.0606 12.2254 212.1394 1.6445

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 76034.469 0.484 115.237 259693.906 0.472621E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.624 EfDer = 0.993 SH = 0.472763E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.819 2405.688 6.229 518.060 1.000 1.000 0.980

 W Kg/sec = 12.191 Wdry = 26.818 WH2O = 0.001 lbm/sec H2O = 0.024g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.257 2407.172 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50758.523 21043.434 2.752 509.668 185.171 384.739 2.078

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.02 -0.08 239.02 0.22 0.41 384.83

 MEAN 15.91 0.00 -0.02 239.02 -0.08 239.02 0.22 0.37

 HUB 13.07 0.00 -0.02 239.02 -0.08 239.02 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.15 47.36 10.79 384.60 452.89 6.03 513.47 484.06 0.22

 MEAN 54.42 44.80 9.62 334.07 410.84 6.03 513.47 484.06 0.22

 HUB 48.95 38.84 10.11 274.39 363.95 6.03 513.47 484.06 0.22

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 320.09 197.98 251.52 1112.27 0.29 2.05 1.78 7.43

 MEAN 15.50 319.23 194.01 253.52 1110.35 0.29 2.13 1.86 5.75

 HUB 12.59 335.95 217.95 255.65 1108.47 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.62 308.50 178.64 0.28 3553.36 0.92 0.91

 MEAN 325.35 285.52 131.34 0.26 3007.95 0.92 0.91 0.91 1.59

 HUB 264.31 259.82 46.36 0.23 2745.04 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.72 1.08 6.35 530.06 1.02 521.82 489.89 0.17

 MEAN 6.64 1.07 6.27 528.21 1.02 520.02 489.01 0.18

 HUB 6.60 1.06 6.20 527.33 1.02 518.25 488.59 0.19

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.21 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 37.43 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.45 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 349.6911 197.5645 288.5345 1108.9347 0.3153 -0.1731 2.0437

 

NASA/TM—2013-218094 O–275
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6457 6.2086 518.7011 489.1532 0.1913 34.4001 33.0000 -1.4001

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 294.9098 67.3429 287.1180 1111.9645 0.2652 0.1502 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6437 6.3307 521.5400 489.1392 410.5396 0.0252 0.3840

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 286.8710 0.0000 286.8710 1112.3583 0.2579 0.3073 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3429 521.9160 489.1275 0.0000 0.0600 0.0373 0.1823

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 6.6391 1.0659 528.5318 10.4717 231.8381 1.7972

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 65135.250 0.459 98.718 272254.750 0.474599E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1547 Tt4 = 528.5318 T1 = 457.7372

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 440252.81 667.2422 86.8419 1.5568 0.8403 15.1447 1.1547 37.3740

NASA/TM—2013-218094 O–276
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.249 EfDer = 0.956 SH = 0.440675E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.842 2330.547 4.199 451.563 1.000 1.000 0.980

 W Kg/sec = 11.747 Wdry = 25.841 WH2O = 0.001 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.406 2497.787 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62728.457 20276.795 3.366 831.557 247.067 619.754 2.508

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 181.04 -0.06 181.04 0.18 0.44 449.67

 MEAN 17.06 0.00 -0.02 181.04 -0.06 181.04 0.18 0.38

 HUB 12.51 0.00 -0.02 181.04 -0.06 181.04 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.66 50.47 16.19 419.57 457.02 4.11 448.93 443.83 2.23

 MEAN 62.45 47.20 15.25 346.97 391.42 4.11 448.93 443.83 2.23

 HUB 54.57 38.62 15.95 254.43 312.32 4.11 448.93 443.83 2.23

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 376.81 288.04 242.95 1043.93 0.36 7.29 6.52 16.04

 MEAN 18.04 381.72 291.92 245.96 1041.07 0.37 7.43 6.80 12.53

 HUB 15.00 413.86 329.70 250.15 1037.53 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 419.57 276.27 131.53 0.26 5943.50 0.92 0.88

 MEAN 366.81 257.11 74.90 0.25 5266.08 0.92 0.88 0.88 1.75

 HUB 305.07 251.36 24.64 0.24 4946.35 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 471.01 1.04 459.59 457.65 1.44

 MEAN 4.73 1.13 4.32 468.79 1.04 457.07 456.17 1.59

 HUB 4.70 1.12 4.21 467.75 1.04 453.97 455.48 1.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.85 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.88 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.81 -5.62 -9.30 3.68 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 393.0095 291.3496 263.7648 1040.7074 0.3776 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7379 4.2991 456.7588 456.4299 1.6073 47.8448 35.4000 -12.4448

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 262.3339 64.1749 254.3633 1048.5220 0.2502 0.5088 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7276 4.5287 463.6468 456.3578 554.9116 0.0338 0.6005

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.1896 0.0000 261.1896 1048.5680 0.2491 0.4797 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5097 463.6948 456.3205 0.0000 0.0600 0.0836 0.4651

NASA/TM—2013-218094 O–277
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8190 4.7059 1.1207 469.1816 17.6189 169.0683 1.3106

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 109540.523 0.622 159.970 273652.031 0.446974E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.696 EfDer = 0.961 SH = 0.449531E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.842 2330.547 4.706 469.181 1.000 1.000 0.980

 W Kg/sec = 11.747 Wdry = 25.841 WH2O = 0.001 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.774 2450.448 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58767.527 20276.787 2.628 590.487 224.728 468.502 2.085

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 238.86 -0.08 238.86 0.23 0.46 439.43

 MEAN 18.08 0.00 -0.02 238.86 -0.08 238.86 0.23 0.42

 HUB 15.21 0.00 -0.02 238.86 -0.08 238.86 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.26 46.36 13.90 417.94 481.45 4.54 464.59 456.32 1.19

 MEAN 57.00 42.30 14.70 367.67 438.52 4.54 464.59 456.32 1.19

 HUB 52.33 37.84 14.49 309.34 390.89 4.54 464.59 456.32 1.19

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 346.90 238.24 252.16 1061.75 0.33 2.33 2.04 9.02

 MEAN 18.01 346.97 235.79 254.55 1059.48 0.33 2.40 2.13 7.35

 HUB 15.22 368.20 263.47 257.20 1057.25 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 415.30 308.11 177.06 0.29 4866.51 0.92 0.88

 MEAN 366.28 286.05 130.50 0.27 4247.99 0.92 0.88 0.88 1.69

 HUB 309.60 261.31 46.13 0.25 4012.08 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.23 1.11 4.87 485.10 1.03 475.42 466.48 0.79

 MEAN 5.17 1.10 4.80 483.08 1.03 473.40 465.25 0.85

 HUB 5.14 1.09 4.73 482.31 1.03 471.40 464.79 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.37 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.81 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.69 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 371.4506 236.4480 286.4749 1058.3558 0.3510 -0.1095 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1757 4.7583 472.3990 465.5094 0.8784 39.5353 30.6000 -8.9353

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 277.5911 58.8513 271.2809 1063.8287 0.2609 0.3565 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1706 4.9346 477.2983 465.4689 491.5697 0.0235 0.4539

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 287.6496 0.0000 287.6496 1063.3123 0.2705 0.3475 0.5911

NASA/TM—2013-218094 O–278
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9034 476.8411 465.4426 0.0000 0.0600 0.0625 0.2745

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8366 5.1558 1.0956 483.4953 14.3142 191.2168 1.4823

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89003.063 0.516 129.978 248723.203 0.451239E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.616 EfDer = 0.976 SH = 0.451239E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.842 2330.547 5.156 483.495 1.000 1.000 0.980

 W Kg/sec = 11.747 Wdry = 25.841 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.137 2413.904 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55285.809 20276.785 2.620 545.479 208.228 424.468 2.038 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 243.25 -0.08 243.25 0.23 0.45 422.77

 MEAN 17.74 0.00 -0.02 243.25 -0.08 243.25 0.23 0.41

 HUB 15.05 0.00 -0.02 243.25 -0.08 243.25 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.21 46.36 12.85 408.18 475.24 4.97 478.74 465.43 0.70

 MEAN 56.02 43.40 12.62 360.76 435.18 4.97 478.74 465.43 0.70

 HUB 51.53 38.84 12.69 306.08 391.03 4.97 478.74 465.43 0.70

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 339.49 222.18 256.70 1076.37 0.32 2.26 1.98 8.75

 MEAN 17.51 341.55 222.88 258.80 1074.45 0.32 2.34 2.07 6.78

 HUB 14.85 364.74 254.66 261.12 1072.56 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.89 313.93 180.72 0.29 4402.98 0.92 0.89

 MEAN 356.05 291.05 133.16 0.27 3903.39 0.92 0.89 0.89 1.64

 HUB 302.02 265.38 47.36 0.25 3782.95 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.67 1.10 5.30 497.90 1.03 488.63 473.88 0.49

 MEAN 5.61 1.09 5.24 496.26 1.03 486.88 472.96 0.52

 HUB 5.60 1.09 5.17 495.87 1.03 485.17 472.75 0.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.88 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.74 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.28 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 367.2766 224.3450 290.7944 1073.2769 0.3422 -0.1179 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6215 5.1893 485.8295 473.1978 0.5412 37.6498 31.5000 -6.1498

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 286.5534 62.5097 279.6523 1077.9540 0.2658 0.3019 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6183 5.3524 490.0738 473.1696 451.3937 0.0181 0.4265

 

NASA/TM—2013-218094 O–279
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.3419 0.0000 291.3419 1077.7023 0.2703 0.3302 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3320 489.8513 473.1451 0.0000 0.0600 0.0493 0.2497

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8578 5.6061 1.0873 496.6768 13.1819 197.2764 1.5293

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 81970.391 0.505 119.707 247461.750 0.452915E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.941 EfDer = 0.987 SH = 0.453066E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.842 2330.547 5.606 496.677 1.000 1.000 0.980

 W Kg/sec = 11.747 Wdry = 25.841 WH2O = 0.001 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.308 2381.656 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52203.762 20276.785 2.645 513.330 194.096 395.845 2.039

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.07 -0.08 244.07 0.23 0.43 400.29

 MEAN 16.97 0.00 -0.02 244.07 -0.08 244.07 0.23 0.39

 HUB 14.32 0.00 -0.02 244.07 -0.08 244.07 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.08 46.36 11.72 391.71 461.60 5.41 491.89 473.14 0.44

 MEAN 54.74 43.80 10.94 345.15 422.80 5.41 491.89 473.14 0.44

 HUB 50.04 37.84 12.20 291.24 380.05 5.41 491.89 473.14 0.44

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 327.24 202.91 256.74 1089.46 0.30 2.16 1.89 8.34

 MEAN 16.57 329.30 203.83 258.63 1087.73 0.30 2.24 1.97 6.35

 HUB 13.89 351.17 235.29 260.70 1086.03 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 383.98 314.17 181.07 0.29 3832.48 0.92 0.90

 MEAN 337.08 290.94 133.25 0.27 3379.70 0.92 0.90 0.90 1.59

 HUB 282.49 264.94 47.20 0.24 3269.36 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.08 1.09 5.72 509.21 1.03 500.60 479.98 0.33

 MEAN 6.03 1.07 5.66 507.73 1.02 499.01 479.20 0.35

 HUB 6.01 1.07 5.60 507.37 1.02 497.45 479.02 0.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.32 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.24 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.07 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 349.9085 204.9778 283.5843 1086.9004 0.3219 -0.0937 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0358 5.6228 498.2594 479.3973 0.3568 35.8598 32.4000 -3.4598

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 285.1121 63.9423 277.8494 1090.5018 0.2615 0.2619 2.2705

 

NASA/TM—2013-218094 O–280
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0343 5.7578 501.5680 479.3800 432.2457 0.0140 0.4030

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 282.8121 0.0000 282.8121 1090.6096 0.2593 0.3138 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7524 501.6730 479.3575 0.0000 0.0600 0.0407 0.2479

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8713 6.0241 1.0746 508.1041 11.4278 213.3545 1.6539

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71068.977 0.482 103.787 253453.797 0.454714E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.408 EfDer = 0.994 SH = 0.454850E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.842 2330.547 6.024 508.104 1.000 1.000 0.980

 W Kg/sec = 11.747 Wdry = 25.841 WH2O = 0.001 lbm/sec H2O = 0.023g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.413 2354.722 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49565.109 20276.783 2.790 509.668 182.698 384.739 2.106

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 233.40 -0.08 233.40 0.21 0.40 376.44

 MEAN 15.91 0.00 -0.02 233.40 -0.08 233.40 0.21 0.37

 HUB 13.07 0.00 -0.02 233.40 -0.08 233.40 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.94 47.36 10.58 372.59 439.73 5.84 503.72 479.35 0.30

 MEAN 54.21 44.80 9.41 323.64 399.08 5.84 503.72 479.35 0.30

 HUB 48.72 38.84 9.88 265.82 353.80 5.84 503.72 479.35 0.30

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 310.93 190.12 246.03 1101.23 0.28 2.05 1.78 7.43

 MEAN 15.50 310.36 186.75 247.88 1099.44 0.28 2.13 1.86 5.75

 HUB 12.59 326.88 210.76 249.86 1097.67 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 364.86 301.77 174.74 0.27 3412.30 0.92 0.91

 MEAN 315.19 279.18 128.44 0.25 2895.47 0.92 0.91 0.91 1.58

 HUB 256.05 253.93 45.29 0.23 2654.54 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.47 1.07 6.13 519.26 1.02 511.49 485.10 0.24

 MEAN 6.40 1.06 6.06 517.57 1.02 509.83 484.26 0.25

 HUB 6.37 1.06 5.99 516.79 1.02 508.19 483.86 0.26

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.70 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 36.99 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.15 10.27 6.50 3.77 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 340.1794 190.1754 282.0556 1098.0685 0.3098 -0.1747 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4076 6.0003 508.5701 484.3972 0.2576 33.9897 33.0000 -0.9897

 

NASA/TM—2013-218094 O–281
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 288.5300 65.8861 280.9067 1100.8831 0.2621 0.1407 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4061 6.1111 511.1809 484.3841 410.5396 0.0245 0.3771

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 280.6768 0.0000 280.6768 1101.2643 0.2549 0.3000 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1225 511.5402 484.3731 0.0000 0.0600 0.0369 0.1729

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 6.4017 1.0627 517.8740 9.7704 233.8002 1.8124

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 60767.637 0.456 88.743 265989.781 0.456543E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1468 Tt4 = 517.8740 T1 = 451.5633

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 412350.59 602.1852 84.4062 1.5245 0.8406 15.2491 1.1468 37.3740

NASA/TM—2013-218094 O–282
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.296 EfDer = 0.956 SH = 0.420292E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.433 2302.100 4.337 449.674 1.000 1.000 0.980

 W Kg/sec = 12.015 Wdry = 26.432 WH2O = 0.001 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.416 2472.477 1.381 0.248 53.350 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 61839.848 20740.453 3.406 831.557 244.169 619.754 2.538

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 178.48 -0.06 178.48 0.17 0.44 445.11

 MEAN 17.06 0.00 -0.02 178.48 -0.06 178.48 0.17 0.38

 HUB 12.51 0.00 -0.02 178.48 -0.06 178.48 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.70 50.47 16.23 414.45 451.30 4.25 447.11 442.64 2.40

 MEAN 62.50 47.20 15.30 342.73 386.47 4.25 447.11 442.64 2.40

 HUB 54.63 38.62 16.01 251.32 308.30 4.25 447.11 442.64 2.40

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 372.16 284.67 239.73 1041.57 0.36 7.29 6.52 16.04

 MEAN 18.04 376.93 288.46 242.64 1038.77 0.36 7.43 6.80 12.53

 HUB 15.00 408.51 325.63 246.68 1035.31 0.39 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 414.45 272.60 129.78 0.26 5873.93 0.92 0.87

 MEAN 362.34 253.64 73.88 0.24 5203.65 0.92 0.87 0.87 1.75

 HUB 301.34 247.87 24.29 0.24 4885.22 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 468.66 1.04 457.52 456.43 1.56

 MEAN 4.87 1.12 4.45 466.49 1.04 455.06 454.95 1.72

 HUB 4.84 1.12 4.35 465.46 1.04 452.04 454.26 1.95

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.90 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.93 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.85 -5.62 -9.30 3.68 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 388.0444 287.8958 260.1815 1038.4213 0.3737 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8817 4.4385 454.7581 455.2092 1.7409 47.8948 35.4000 -12.4948

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 258.9599 63.3495 251.0918 1046.0596 0.2476 0.5094 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8714 4.6706 461.4755 455.1404 554.9116 0.0336 0.6008

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 257.8208 0.0000 257.8208 1046.1051 0.2465 0.4798 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6512 461.5227 455.1055 0.0000 0.0600 0.0839 0.4651

NASA/TM—2013-218094 O–283
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8184 4.8493 1.1181 466.8688 17.1955 168.8682 1.3091

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 106909.922 0.622 159.698 280706.594 0.426076E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.712 EfDer = 0.961 SH = 0.427112E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.433 2302.100 4.849 466.869 1.000 1.000 0.980

 W Kg/sec = 12.015 Wdry = 26.432 WH2O = 0.001 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.020 2426.526 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58016.063 20740.447 2.654 590.487 222.522 468.502 2.105

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 235.80 -0.08 235.80 0.23 0.45 435.14

 MEAN 18.08 0.00 -0.02 235.80 -0.08 235.80 0.23 0.41

 HUB 15.21 0.00 -0.02 235.80 -0.08 235.80 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.27 46.36 13.91 412.84 475.51 4.68 462.40 455.10 1.29

 MEAN 57.01 42.30 14.71 363.19 433.09 4.68 462.40 455.10 1.29

 HUB 52.35 37.84 14.51 305.56 386.03 4.68 462.40 455.10 1.29

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 342.71 235.29 249.17 1058.98 0.32 2.33 2.04 9.02

 MEAN 18.01 342.77 232.91 251.48 1056.77 0.32 2.40 2.13 7.35

 HUB 15.22 363.71 260.27 254.05 1054.59 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.23 304.45 174.94 0.29 4806.39 0.92 0.88

 MEAN 361.81 282.60 128.90 0.27 4196.19 0.92 0.88 0.88 1.69

 HUB 305.82 258.11 45.56 0.24 3963.30 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.11 5.01 482.40 1.03 472.95 465.28 0.86

 MEAN 5.31 1.10 4.94 480.43 1.03 470.98 464.05 0.92

 HUB 5.29 1.09 4.87 479.68 1.03 469.04 463.58 0.99

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.36 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.80 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.69 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 366.9299 233.5650 282.9929 1055.6689 0.3476 -0.1095 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3236 4.9020 470.0068 464.3036 0.9563 39.5342 30.6000 -8.9342

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 274.3592 58.1661 268.1225 1061.0161 0.2586 0.3562 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3185 5.0799 474.7810 464.2649 491.5697 0.0233 0.4536

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.2756 0.0000 284.2756 1060.5116 0.2681 0.3471 0.5911

NASA/TM—2013-218094 O–284
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0483 474.3355 464.2403 0.0000 0.0600 0.0625 0.2741

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8365 5.3034 1.0937 480.8345 13.9662 191.1660 1.4819

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 86840.273 0.516 129.719 255230.828 0.428771E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.598 EfDer = 0.976 SH = 0.428771E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.433 2302.100 5.303 480.834 1.000 1.000 0.980

 W Kg/sec = 12.015 Wdry = 26.432 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.543 2391.027 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54648.207 20740.447 2.642 545.479 206.490 424.468 2.056

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.44 -0.08 240.44 0.23 0.44 418.76

 MEAN 17.74 0.00 -0.02 240.44 -0.08 240.44 0.23 0.40

 HUB 15.05 0.00 -0.02 240.44 -0.08 240.44 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.20 46.36 12.84 403.20 469.52 5.12 476.19 464.23 0.76

 MEAN 56.00 43.40 12.60 356.36 429.96 5.12 476.19 464.23 0.76

 HUB 51.51 38.84 12.67 302.35 386.36 5.12 476.19 464.23 0.76

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.47 219.19 253.96 1073.27 0.31 2.26 1.98 8.75

 MEAN 17.51 337.53 219.99 255.99 1071.39 0.32 2.34 2.07 6.78

 HUB 14.85 360.51 251.56 258.24 1069.55 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 397.98 310.58 178.79 0.29 4343.80 0.92 0.89

 MEAN 351.70 287.89 131.71 0.27 3852.71 0.92 0.89 0.89 1.64

 HUB 298.33 262.44 46.77 0.25 3736.87 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.82 1.10 5.45 494.87 1.03 485.82 472.70 0.54

 MEAN 5.76 1.09 5.38 493.28 1.03 484.12 471.78 0.57

 HUB 5.75 1.08 5.32 492.91 1.03 482.46 471.57 0.61

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.80 35.15 31.50 3.65 0.93 0.50 1.40

 MEAN 40.67 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.25 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 362.9747 221.4319 287.6083 1070.2465 0.3392 -0.1180 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7728 5.3365 483.0924 472.0121 0.5928 37.5930 31.5000 -6.0930

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 283.5450 61.8534 276.7163 1074.8103 0.2638 0.3005 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7697 5.5007 487.2220 471.9850 451.3937 0.0178 0.4253

 

NASA/TM—2013-218094 O–285
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.2664 0.0000 288.2664 1074.5642 0.2683 0.3290 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4801 487.0049 471.9620 0.0000 0.0600 0.0491 0.2483

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8580 5.7574 1.0856 493.6870 12.8529 197.4480 1.5306

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79925.164 0.505 119.389 254060.141 0.430361E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.891 EfDer = 0.987 SH = 0.430456E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.433 2302.100 5.757 493.687 1.000 1.000 0.980

 W Kg/sec = 12.015 Wdry = 26.432 WH2O = 0.001 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.843 2359.698 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51661.676 20740.443 2.663 513.330 192.734 395.845 2.054

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.54 -0.08 241.54 0.22 0.42 396.60

 MEAN 16.97 0.00 -0.02 241.54 -0.08 241.54 0.22 0.39

 HUB 14.32 0.00 -0.02 241.54 -0.08 241.54 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.03 46.36 11.67 386.93 456.20 5.56 489.00 471.95 0.48

 MEAN 54.69 43.80 10.89 340.93 417.89 5.56 489.00 471.95 0.48

 HUB 49.99 37.84 12.15 287.68 375.70 5.56 489.00 471.95 0.48

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.49 199.98 254.27 1086.05 0.30 2.16 1.89 8.34

 MEAN 16.57 325.58 201.03 256.10 1084.37 0.30 2.24 1.97 6.35

 HUB 13.89 347.24 232.30 258.10 1082.71 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 379.29 311.14 179.31 0.29 3777.21 0.92 0.90

 MEAN 332.96 288.08 131.93 0.27 3333.28 0.92 0.90 0.90 1.59

 HUB 279.04 262.30 46.75 0.24 3227.82 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.24 1.08 5.87 505.89 1.02 497.48 478.81 0.36

 MEAN 6.18 1.07 5.81 504.46 1.02 495.93 478.03 0.38

 HUB 6.17 1.07 5.75 504.12 1.02 494.42 477.85 0.40

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.18 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.13 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 41.99 10.27 6.50 3.77 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 345.9953 202.1616 280.7907 1083.5509 0.3193 -0.0940 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1898 5.7728 495.1948 478.2274 0.3927 35.7529 32.4000 -3.3529

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 282.4107 63.3365 275.2168 1087.0592 0.2598 0.2595 2.2705

 

NASA/TM—2013-218094 O–286
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1884 5.9083 498.4077 478.2108 432.2457 0.0138 0.4010

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.1256 0.0000 280.1256 1087.1659 0.2577 0.3119 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9029 498.5110 478.1894 0.0000 0.0600 0.0404 0.2457

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8716 6.1781 1.0731 504.8205 11.1339 213.7887 1.6573

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 69241.930 0.481 103.431 260328.281 0.431994E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.330 EfDer = 0.994 SH = 0.431994E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.433 2302.100 6.178 504.820 1.000 1.000 0.980

 W Kg/sec = 12.015 Wdry = 26.432 WH2O = 0.001 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.047 2333.532 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49101.234 20740.443 2.806 509.668 181.627 384.739 2.118

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.22 -0.08 231.22 0.21 0.40 373.06

 MEAN 15.91 0.00 -0.02 231.22 -0.08 231.22 0.21 0.36

 HUB 13.07 0.00 -0.02 231.22 -0.08 231.22 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.87 47.36 10.51 368.04 434.71 5.99 500.52 478.18 0.33

 MEAN 54.13 44.80 9.33 319.69 394.60 5.99 500.52 478.18 0.33

 HUB 48.64 38.84 9.80 262.57 349.92 5.99 500.52 478.18 0.33

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 307.45 187.20 243.90 1097.54 0.28 2.05 1.78 7.43

 MEAN 15.50 306.98 184.05 245.69 1095.80 0.28 2.13 1.86 5.75

 HUB 12.59 323.38 208.01 247.60 1094.08 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 360.41 299.15 173.21 0.27 3359.76 0.92 0.91

 MEAN 311.34 276.70 127.29 0.25 2853.66 0.92 0.91 0.91 1.58

 HUB 252.93 251.64 44.91 0.23 2619.94 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.63 1.07 6.28 515.67 1.02 508.07 483.94 0.26

 MEAN 6.56 1.06 6.21 514.04 1.02 506.46 483.09 0.27

 HUB 6.53 1.06 6.15 513.28 1.02 504.88 482.71 0.29

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.51 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.84 27.39 23.50 3.89 0.93 0.44 1.64

 HUB 40.03 10.28 6.50 3.78 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 336.5544 187.4287 279.5341 1094.4513 0.3075 -0.1754 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5635 6.1521 505.2256 483.2378 0.2845 33.8420 33.0000 -0.8420

 

NASA/TM—2013-218094 O–287
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 286.0421 65.3179 278.4845 1097.1863 0.2607 0.1371 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5620 6.2630 507.7541 483.2253 410.5396 0.0243 0.3747

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 278.2618 0.0000 278.2618 1097.5623 0.2535 0.2974 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2745 508.1070 483.2148 0.0000 0.0600 0.0368 0.1694

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8802 6.5575 1.0614 514.3323 9.5123 234.5258 1.8180

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 59162.121 0.455 88.374 273317.125 0.433460E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1438 Tt4 = 514.3323 T1 = 449.6739

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 402079.41 600.6118 83.4160 1.5119 0.8407 15.2958 1.1438 37.3740

NASA/TM—2013-218094 O–288
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.360 EfDer = 0.955 SH = 0.372261E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.406 2235.470 4.829 451.607 1.000 1.000 0.980

 W Kg/sec = 12.912 Wdry = 28.404 WH2O = 0.001 lbm/sec H2O = 0.017g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.689 2395.771 1.381 0.248 53.349 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59886.754 22288.033 3.521 831.557 236.188 619.754 2.624

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 172.84 -0.06 172.84 0.17 0.42 431.30

 MEAN 17.06 0.00 -0.02 172.84 -0.06 172.84 0.17 0.36

 HUB 12.51 0.00 -0.02 172.84 -0.06 172.84 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.76 50.47 16.29 402.45 438.05 4.74 449.20 444.60 2.14

 MEAN 62.56 47.20 15.36 332.81 375.07 4.74 449.20 444.60 2.14

 HUB 54.70 38.62 16.08 244.05 299.10 4.74 449.20 444.60 2.14

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 361.43 276.48 232.79 1043.24 0.35 7.29 6.52 16.04

 MEAN 18.04 365.97 280.19 235.43 1040.62 0.35 7.43 6.80 12.53

 HUB 15.00 396.41 316.19 239.09 1037.38 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 402.45 264.69 125.97 0.25 5705.07 0.92 0.87

 MEAN 351.85 246.09 71.66 0.24 5054.50 0.92 0.87 0.87 1.75

 HUB 292.62 240.25 23.56 0.23 4743.53 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 469.51 1.04 459.00 457.72 1.43

 MEAN 5.39 1.12 4.95 467.47 1.04 456.70 456.31 1.57

 HUB 5.35 1.11 4.85 466.49 1.03 453.85 455.64 1.76

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.90 28.42 24.20 4.22 0.93 0.57 1.80

 MEAN 49.96 16.93 12.70 4.23 0.95 0.52 2.22

 HUB 52.90 -5.63 -9.30 3.67 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 376.7104 279.6442 252.4081 1040.2888 0.3621 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3962 4.9344 456.4097 456.5518 1.5918 47.9304 35.4000 -12.5304

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 251.7791 61.5929 244.1292 1047.4579 0.2404 0.5094 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3858 5.1762 462.7244 456.4941 554.9116 0.0327 0.6001

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 250.6326 0.0000 250.6326 1047.5026 0.2393 0.4787 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1554 462.7707 456.4614 0.0000 0.0600 0.0842 0.4640

NASA/TM—2013-218094 O–289
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8177 5.3622 1.1105 467.8224 16.2157 168.6198 1.3071

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 100825.836 0.623 161.848 300363.344 0.379890E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.675 EfDer = 0.961 SH = 0.386112E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.406 2235.470 5.362 467.822 1.000 1.000 0.980

 W Kg/sec = 12.912 Wdry = 28.404 WH2O = 0.001 lbm/sec H2O = 0.019g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.953 2353.891 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56415.434 22288.020 2.728 590.487 216.473 468.502 2.164

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 229.30 -0.08 229.30 0.22 0.44 422.12

 MEAN 18.08 0.00 -0.02 229.30 -0.08 229.30 0.22 0.40

 HUB 15.21 0.00 -0.02 229.30 -0.08 229.30 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.24 46.36 13.88 400.89 461.90 5.19 463.59 456.46 1.22

 MEAN 56.98 42.30 14.68 352.67 420.73 5.19 463.59 456.46 1.22

 HUB 52.31 37.84 14.47 296.72 375.06 5.19 463.59 456.46 1.22

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 333.09 227.83 242.99 1059.58 0.31 2.33 2.04 9.02

 MEAN 18.01 333.22 225.75 245.10 1057.51 0.32 2.40 2.13 7.35

 HUB 15.22 353.64 252.65 247.44 1055.47 0.34 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 398.36 296.86 170.53 0.28 4653.85 0.92 0.88

 MEAN 351.34 275.40 125.59 0.26 4067.18 0.92 0.88 0.88 1.68

 HUB 296.97 251.38 44.32 0.24 3847.27 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.91 1.10 5.53 482.42 1.03 473.50 466.19 0.84

 MEAN 5.84 1.09 5.46 480.58 1.03 471.65 465.01 0.90

 HUB 5.82 1.08 5.39 479.89 1.03 469.84 464.58 0.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.15 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.65 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.60 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 356.7448 226.3838 275.7122 1056.4685 0.3377 -0.1100 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8540 5.4152 470.7329 465.2596 0.9252 39.3890 30.6000 -8.7890

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 267.7285 56.7603 261.6425 1061.4720 0.2522 0.3528 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8491 5.5991 475.2032 465.2266 491.5697 0.0223 0.4502

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 277.3273 0.0000 277.3273 1060.9957 0.2614 0.3440 0.5911

NASA/TM—2013-218094 O–290
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5662 474.7824 465.2036 0.0000 0.0600 0.0617 0.2704

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8371 5.8333 1.0879 480.9672 13.1451 191.5541 1.4849

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 81740.898 0.515 131.212 273458.969 0.387862E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.461 EfDer = 0.977 SH = 0.388003E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.406 2235.470 5.833 480.967 1.000 1.000 0.980

 W Kg/sec = 12.912 Wdry = 28.404 WH2O = 0.001 lbm/sec H2O = 0.020g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.929 2321.503 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53340.543 22288.020 2.703 545.479 201.769 424.468 2.104

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 234.69 -0.08 234.69 0.22 0.43 406.58

 MEAN 17.74 0.00 -0.02 234.69 -0.08 234.69 0.22 0.39 

 HUB 15.05 0.00 -0.02 234.69 -0.08 234.69 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.07 46.36 12.71 391.53 456.55 5.64 476.54 465.19 0.75 

 MEAN 55.86 43.40 12.46 346.05 418.19 5.64 476.54 465.19 0.75

 HUB 51.37 38.84 12.53 293.60 375.93 5.64 476.54 465.19 0.75

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 326.39 211.57 248.53 1072.96 0.30 2.26 1.98 8.75

 MEAN 17.51 328.57 212.76 250.39 1071.22 0.31 2.34 2.07 6.78

 HUB 14.85 351.08 244.00 252.44 1069.50 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 386.46 303.90 174.89 0.28 4192.85 0.92 0.89

 MEAN 341.52 281.55 128.76 0.26 3726.11 0.92 0.89 0.89 1.63

 HUB 289.70 256.54 45.70 0.24 3624.55 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 494.12 1.03 485.56 473.31 0.54

 MEAN 6.31 1.08 5.91 492.66 1.02 483.98 472.44 0.57

 HUB 6.29 1.08 5.85 492.34 1.02 482.43 472.25 0.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.41 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.36 27.21 23.50 3.71 0.94 0.48 1.62

 HUB 44.03 10.26 6.50 3.76 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.4830 214.1551 281.2256 1070.1204 0.3303 -0.1192 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3177 5.8637 482.9920 472.6660 0.5923 37.2895 31.5000 -5.7895

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 277.6470 60.5668 270.9604 1074.3748 0.2584 0.2937 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3149 6.0320 486.8407 472.6429 451.3937 0.0169 0.4195

 

NASA/TM—2013-218094 O–291
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 282.2175 0.0000 282.2175 1074.1414 0.2627 0.3237 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0106 486.6349 472.6219 0.0000 0.0600 0.0479 0.2417

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8593 6.3022 1.0804 493.0392 12.0724 198.5290 1.5390

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 75076.195 0.503 120.514 272626.875 0.389664E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.658 EfDer = 0.988 SH = 0.389797E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.406 2235.470 6.302 493.039 1.000 1.000 0.980

 W Kg/sec = 12.912 Wdry = 28.404 WH2O = 0.001 lbm/sec H2O = 0.021g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.597 2292.906 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50600.785 22288.018 2.715 513.330 189.090 395.845 2.093

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 236.58 -0.08 236.58 0.22 0.41 385.37

 MEAN 16.97 0.00 -0.02 236.58 -0.08 236.58 0.22 0.38

 HUB 14.32 0.00 -0.02 236.58 -0.08 236.58 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.81 46.36 11.45 375.73 444.07 6.10 488.54 472.61 0.49

 MEAN 54.46 43.80 10.66 331.07 406.97 6.10 488.54 472.61 0.49

 HUB 49.75 37.84 11.91 279.36 366.13 6.10 488.54 472.61 0.49

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 315.12 192.32 249.63 1084.92 0.29 2.16 1.89 8.34

 MEAN 16.57 317.41 193.91 251.29 1083.36 0.29 2.24 1.97 6.35

 HUB 13.89 338.77 225.15 253.12 1081.83 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 368.31 305.43 176.00 0.28 3632.52 0.92 0.90

 MEAN 323.33 282.66 129.42 0.26 3215.21 0.92 0.90 0.90 1.58

 HUB 270.97 257.23 45.81 0.24 3128.57 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.08 6.41 504.43 1.02 496.45 479.19 0.38

 MEAN 6.73 1.07 6.35 503.13 1.02 495.02 478.46 0.39

 HUB 6.72 1.07 6.29 502.85 1.02 493.63 478.31 0.41

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.61 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 37.66 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.65 10.26 6.50 3.76 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 337.5083 194.9996 275.4760 1082.5712 0.3118 -0.0954 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7461 6.3120 494.3124 478.6512 0.4029 35.2933 32.4000 -2.8933

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 277.3947 62.2115 270.3286 1085.8197 0.2555 0.2496 2.2705

 

NASA/TM—2013-218094 O–292
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7448 6.4493 497.2845 478.6371 432.2457 0.0132 0.3931

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 275.1274 0.0000 275.1274 1085.9242 0.2534 0.3041 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4440 497.3852 478.6175 0.0000 0.0600 0.0395 0.2363

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8731 6.7343 1.0686 503.4712 10.4325 215.7253 1.6723

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64883.266 0.478 104.152 279750.031 0.391429E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.010 EfDer = 0.996 SH = 0.391556E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 28.406 2235.470 6.734 503.471 1.000 1.000 0.980

 W Kg/sec = 12.912 Wdry = 28.404 WH2O = 0.001 lbm/sec H2O = 0.022g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.088 2269.027 1.381 0.248 53.350 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 48242.770 22288.016 2.850 509.668 178.821 384.739 2.152

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 227.17 -0.08 227.17 0.21 0.39 362.74

 MEAN 15.91 0.00 -0.02 227.17 -0.08 227.17 0.21 0.35

 HUB 13.07 0.00 -0.02 227.17 -0.08 227.17 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.56 47.36 10.20 357.39 423.55 6.54 499.32 478.61 0.34

 MEAN 53.81 44.80 9.01 310.43 384.74 6.54 499.32 478.61 0.34

 HUB 48.31 38.84 9.47 254.97 341.55 6.54 499.32 478.61 0.34

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.78 179.45 240.14 1095.66 0.27 2.05 1.78 7.43

 MEAN 15.50 299.69 177.09 241.77 1094.05 0.27 2.13 1.86 5.75

 HUB 12.59 316.01 201.40 243.52 1092.47 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.98 294.52 170.53 0.27 3220.78 0.92 0.91

 MEAN 302.33 272.28 125.24 0.25 2745.68 0.92 0.91 0.91 1.56

 HUB 245.61 247.50 44.21 0.23 2536.68 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.19 1.07 6.83 513.57 1.02 506.35 484.13 0.27

 MEAN 7.12 1.06 6.77 512.08 1.02 504.86 483.34 0.29

 HUB 7.09 1.05 6.70 511.43 1.02 503.40 482.99 0.30

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.77 35.38 31.50 3.88 0.93 0.45 1.40

 MEAN 36.22 27.39 23.50 3.89 0.93 0.43 1.64

 HUB 39.59 10.29 6.50 3.79 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.996 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.8631 180.3348 275.0096 1092.7493 0.3010 -0.1778 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1278 6.6992 503.6671 483.4799 0.2982 33.2545 33.0000 -0.2545

 

NASA/TM—2013-218094 O–293
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 281.6995 64.3263 274.2567 1095.2574 0.2572 0.1232 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1265 6.8101 505.9822 483.4693 410.5396 0.0236 0.3650

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 274.0497 0.0000 274.0497 1095.6226 0.2501 0.2870 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8222 506.3240 483.4593 0.0000 0.0600 0.0366 0.1558

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 7.1216 1.0575 512.3619 8.8911 237.4559 1.8407

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55301.922 0.452 88.772 294084.813 0.393228E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1345 Tt4 = 512.3619 T1 = 451.6072

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 377828.13 606.4975 80.6887 1.4749 0.8416 15.3596 1.1345 37.3740

NASA/TM—2013-218094 O–294
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.845 EfDer = 0.968 SH = 0.719598E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.560 2121.564 5.592 461.415 1.000 1.000 0.980

 W Kg/sec = 14.800 Wdry = 32.558 WH2O = 0.002 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.722 2249.405 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60560.836 25547.541 3.519 831.557 236.295 619.754 2.623

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 174.79 -0.06 174.79 0.17 0.40 404.95

 MEAN 17.06 0.00 -0.02 174.79 -0.06 174.79 0.17 0.35

 HUB 12.51 0.00 -0.02 174.79 -0.06 174.79 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.41 50.47 14.94 381.95 420.10 5.49 458.96 452.59 2.99

 MEAN 61.05 47.20 13.85 315.85 361.04 5.49 458.96 452.59 2.99

 HUB 52.97 38.62 14.35 231.61 290.21 5.49 458.96 452.59 2.99

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 347.42 254.34 236.67 1052.64 0.33 7.29 6.52 16.04

 MEAN 18.04 354.29 261.54 238.98 1050.43 0.34 7.43 6.80 12.53

 HUB 15.00 387.09 301.89 242.29 1047.58 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 381.95 268.88 127.61 0.26 5248.25 0.92 0.89

 MEAN 333.92 249.70 72.38 0.24 4718.23 0.92 0.89 0.89 1.65

 HUB 277.71 243.50 24.17 0.23 4529.03 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 477.04 1.03 467.34 463.63 2.16

 MEAN 6.16 1.10 5.70 475.46 1.03 465.37 462.58 2.33

 HUB 6.13 1.10 5.59 474.90 1.03 462.85 462.22 2.56

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.06 28.33 24.20 4.13 0.93 0.53 1.80

 MEAN 47.58 16.85 12.70 4.15 0.94 0.48 2.22

 HUB 51.25 -5.70 -9.30 3.60 0.94 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.968 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.7881 261.0355 256.2447 1050.0530 0.3484 -0.0424 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1673 5.6769 465.0425 462.8053 2.3573 45.5306 35.4000 -10.1306

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 256.8267 62.8277 249.0234 1056.1907 0.2432 0.4679 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1596 5.9145 470.4975 462.7312 554.9116 0.0258 0.5569

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.3920 0.0000 255.3920 1056.2491 0.2418 0.4489 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8970 470.5565 462.7028 0.0000 0.0600 0.0692 0.4318

NASA/TM—2013-218094 O–295
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8359 6.1386 1.0977 475.8008 14.3862 176.0145 1.3645

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 89469.641 0.613 164.624 338701.469 0.731716E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.791 EfDer = 0.975 SH = 0.741311E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.560 2121.564 6.139 475.801 1.000 1.000 0.980

 W Kg/sec = 14.800 Wdry = 32.558 WH2O = 0.002 lbm/sec H2O = 0.040g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.677 2215.143 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57480.813 25547.520 2.701 590.487 218.599 468.502 2.143

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 233.63 -0.08 233.63 0.22 0.42 397.24

 MEAN 18.08 0.00 -0.02 233.63 -0.08 233.63 0.22 0.39

 HUB 15.21 0.00 -0.02 233.63 -0.08 233.63 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.45 46.36 12.09 380.47 446.54 5.94 471.41 462.70 1.88

 MEAN 55.09 42.30 12.79 334.70 408.24 5.94 471.41 462.70 1.88

 HUB 50.33 37.84 12.49 281.60 365.96 5.94 471.41 462.70 1.88

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.63 203.64 248.95 1066.65 0.30 2.33 2.04 9.02

 MEAN 18.01 324.00 205.20 250.73 1064.98 0.30 2.40 2.13 7.35

 HUB 15.22 346.29 236.75 252.71 1063.34 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 378.06 303.96 174.41 0.28 4160.08 0.92 0.89

 MEAN 333.44 281.62 128.23 0.26 3697.17 0.92 0.89 0.89 1.59

 HUB 281.84 256.70 45.09 0.24 3605.31 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.67 1.09 6.27 488.19 1.03 479.87 470.75 1.38

 MEAN 6.61 1.08 6.20 486.81 1.02 478.37 469.89 1.46

 HUB 6.60 1.07 6.14 486.53 1.02 476.89 469.73 1.54

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.28 35.02 31.50 3.52 0.93 0.48 1.40

 MEAN 39.30 27.09 23.50 3.59 0.94 0.46 1.63

 HUB 43.13 10.12 6.50 3.62 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 349.1909 205.7798 282.1152 1063.8635 0.3282 -0.1236 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6223 6.1521 477.3724 470.1259 1.5081 36.1077 30.6000 -5.5077

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 275.0406 58.3106 268.7884 1068.0017 0.2575 0.2878 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6195 6.3250 481.0939 470.0847 491.5697 0.0165 0.3960

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 284.7016 0.0000 284.7016 1067.5132 0.2667 0.2977 0.5911

NASA/TM—2013-218094 O–296
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2921 480.6592 470.0696 0.0000 0.0600 0.0468 0.2100

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8570 6.6067 1.0762 487.1758 11.3752 204.4899 1.5852

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 70750.891 0.495 130.182 309621.563 0.744115E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.354 EfDer = 0.990 SH = 0.745219E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.560 2121.564 6.607 487.176 1.000 1.000 0.980

 W Kg/sec = 14.800 Wdry = 32.558 WH2O = 0.002 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.211 2189.129 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54736.031 25547.516 2.654 545.479 205.528 424.468 2.065

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 240.83 -0.08 240.83 0.23 0.41 383.40

 MEAN 17.74 0.00 -0.02 240.83 -0.08 240.83 0.23 0.38

 HUB 15.05 0.00 -0.02 240.83 -0.08 240.83 0.23 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.06 46.36 10.70 371.58 442.87 6.38 482.51 470.05 1.26

 MEAN 53.75 43.40 10.35 328.41 407.32 6.38 482.51 470.05 1.26

 HUB 49.17 38.84 10.33 278.64 368.35 6.38 482.51 470.05 1.26

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 317.05 186.39 256.47 1077.93 0.29 2.26 1.98 8.75

 MEAN 17.51 321.29 191.48 257.99 1076.58 0.30 2.34 2.07 6.78

 HUB 14.85 345.51 227.91 259.68 1075.25 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 366.77 313.55 180.37 0.29 3694.09 0.92 0.91

 MEAN 324.12 290.09 132.64 0.27 3353.68 0.92 0.91 0.91 1.53

 HUB 274.93 263.91 47.03 0.25 3385.67 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.11 1.08 6.70 498.17 1.02 490.09 476.76 0.97

 MEAN 7.06 1.07 6.64 497.16 1.02 488.86 476.16 1.01

 HUB 7.07 1.07 6.58 497.25 1.02 487.66 476.23 1.05

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.01 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.58 27.21 23.50 3.71 0.94 0.43 1.62

 HUB 41.27 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 348.1035 192.7398 289.8748 1075.3899 0.3237 -0.1339 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0748 6.5856 487.7871 476.3862 1.0463 33.6202 31.5000 -2.1202

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 287.3085 62.6744 280.3892 1078.8077 0.2663 0.2167 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0734 6.7375 490.8926 476.3571 451.3937 0.0132 0.3606

 

NASA/TM—2013-218094 O–297
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 291.9104 0.0000 291.9104 1078.5668 0.2706 0.2675 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7165 490.6783 476.3416 0.0000 0.0600 0.0381 0.1686

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8745 7.0625 1.0690 497.5286 10.3532 214.1345 1.6600

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 64398.988 0.479 118.494 309798.125 0.747683E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.314 EfDer = 0.998 SH = 0.749388E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.560 2121.564 7.062 497.529 1.000 1.000 0.980

 W Kg/sec = 14.800 Wdry = 32.558 WH2O = 0.002 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.374 2166.233 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52304.254 25547.510 2.642 513.330 194.298 395.845 2.037

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 244.54 -0.08 244.54 0.23 0.40 364.08

 MEAN 16.97 0.00 -0.02 244.54 -0.08 244.54 0.23 0.37

 HUB 14.32 0.00 -0.02 244.54 -0.08 244.54 0.23 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.56 46.36 9.20 356.58 432.45 6.82 492.72 476.33 0.89

 MEAN 52.11 43.80 8.31 314.20 398.21 6.82 492.72 476.33 0.89

 HUB 47.32 37.84 9.48 265.12 360.74 6.82 492.72 476.33 0.89

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 308.31 166.51 259.48 1087.94 0.28 2.16 1.89 8.34

 MEAN 16.57 312.64 172.42 260.80 1086.78 0.29 2.24 1.97 6.35

 HUB 13.89 335.70 209.55 262.27 1085.64 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 349.55 317.54 183.04 0.29 3145.27 0.92 0.91

 MEAN 306.85 293.41 134.43 0.27 2859.07 0.92 0.91 0.91 1.48

 HUB 257.16 266.55 47.61 0.25 2911.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.51 1.06 7.11 506.89 1.02 499.25 481.73 0.72

 MEAN 7.47 1.06 7.06 506.04 1.02 498.18 481.25 0.74

 HUB 7.48 1.06 7.00 506.20 1.02 497.14 481.35 0.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.69 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.47 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.63 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 334.4626 173.3881 286.0102 1085.9001 0.3080 -0.1080 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4825 7.0121 497.3829 481.4436 0.7617 31.2255 32.4000 1.1745

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 289.0661 64.8291 281.7027 1088.3807 0.2656 0.1645 2.2705

 

NASA/TM—2013-218094 O–298
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4816 7.1282 499.6583 481.4249 432.2457 0.0122 0.3299

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.6480 0.0000 286.6480 1088.4983 0.2633 0.2374 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1238 499.7702 481.4065 0.0000 0.0600 0.0371 0.1543

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.4709 1.0578 506.3752 8.8469 235.5072 1.8256

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 55034.055 0.450 101.263 318949.719 0.751757E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.454 EfDer = 1.000 SH = 0.754262E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 32.560 2121.564 7.471 506.375 1.000 1.000 0.980

 W Kg/sec = 14.800 Wdry = 32.558 WH2O = 0.002 lbm/sec H2O = 0.047g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.301 2147.228 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 50219.770 25547.506 2.750 509.668 185.304 384.739 2.076

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.48 -0.08 236.48 0.22 0.38 343.27

 MEAN 15.91 0.00 -0.02 236.48 -0.08 236.48 0.22 0.35

 HUB 13.07 0.00 -0.02 236.48 -0.08 236.48 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.12 47.36 7.76 339.18 413.55 7.23 501.88 481.39 0.66

 MEAN 51.25 44.80 6.45 294.62 377.85 7.23 501.88 481.39 0.66

 HUB 45.67 38.84 6.83 241.98 338.40 7.23 501.88 481.39 0.66

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 294.46 153.40 251.35 1096.99 0.27 2.05 1.78 7.43

 MEAN 15.50 296.83 155.79 252.66 1095.78 0.27 2.13 1.86 5.75

 HUB 12.59 315.33 186.77 254.07 1094.59 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 332.14 308.43 178.75 0.28 2753.44 0.92 0.91

 MEAN 286.92 284.66 131.14 0.26 2415.65 0.92 0.91 0.91 1.46

 HUB 233.09 258.26 46.33 0.24 2352.47 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.88 1.05 7.50 514.57 1.02 507.60 485.91 0.55

 MEAN 7.83 1.05 7.44 513.57 1.01 506.48 485.37 0.57

 HUB 7.82 1.05 7.39 513.38 1.01 505.38 485.28 0.59

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.40 35.42 31.50 3.92 0.93 0.39 1.40

 MEAN 31.66 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.32 10.33 6.50 3.83 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 328.4190 158.6454 287.5598 1094.3496 0.3001 -0.1968 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8344 7.3659 505.1677 485.5151 0.5961 28.8853 33.0000 4.1147

 

NASA/TM—2013-218094 O–299
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.6425 67.5102 287.8313 1096.1296 0.2697 0.0170 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8315 7.4504 506.8118 485.4989 410.5396 0.0272 0.2991

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.5884 0.0000 287.5884 1096.5344 0.2623 0.2110 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4648 507.1893 485.4863 0.0000 0.0600 0.0424 0.0531

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8739 7.8255 1.0475 513.8373 7.4625 262.1688 2.0323

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46425.250 0.421 85.422 336222.219 0.756490E-04

 

Melt Ratio at Stator LE, Throat, TE

 0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1136 Tt4 = 513.8373 T1 = 461.4150

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 326078.81 599.9853 80.7223 1.3993 0.8552 13.8453 1.1136 37.3740

NASA/TM—2013-218094 O–300
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.022 EfDer = 0.995 SH = 0.132743E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.042 6.513 472.324 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.060 WH2O = 0.005 lbm/sec H2O = 0.078g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 88.445 2044.580 1.381 0.248 53.353 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67333.266 32220.186 3.212 831.557 258.916 619.754 2.394

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 194.33 -0.07 194.33 0.18 0.38 368.08

 MEAN 17.06 0.00 -0.02 194.33 -0.07 194.33 0.18 0.33

 HUB 12.51 0.00 -0.02 194.33 -0.07 194.33 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.05 50.47 10.58 351.25 401.48 6.36 469.29 461.19 3.98

 MEAN 56.22 47.20 9.02 290.47 349.54 6.36 469.29 461.19 3.98

 HUB 47.63 38.62 9.01 213.00 288.38 6.36 469.29 461.19 3.98

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 337.78 208.34 265.88 1061.11 0.32 7.29 6.52 16.04

 MEAN 18.04 350.55 226.33 267.69 1059.66 0.33 7.43 6.80 12.53

 HUB 15.00 391.41 282.65 270.77 1057.42 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.25 301.85 142.91 0.28 4299.39 0.92 0.91 

 MEAN 307.08 279.61 80.75 0.26 4083.27 0.92 0.91 0.91 1.41

 HUB 255.39 272.13 27.25 0.26 4240.51 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.06 1.08 6.59 484.09 1.02 474.92 469.22 3.23

 MEAN 7.04 1.08 6.53 483.50 1.02 473.62 468.86 3.39

 HUB 7.06 1.08 6.43 483.93 1.02 471.62 469.19 3.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.08 28.26 24.20 4.06 0.93 0.39 1.80

 MEAN 40.21 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.23 -5.75 -9.30 3.55 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 365.4696 225.8922 287.2990 1059.0804 0.3451 -0.0601 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0472 6.4969 473.1049 469.0880 3.4542 38.1766 35.4000 -2.7766

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 290.1995 70.9917 281.3822 1063.5090 0.2729 0.3319 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0448 6.6941 477.0721 469.0061 554.9116 0.0145 0.4327

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 288.0760 0.0000 288.0760 1063.6125 0.2708 0.3447 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6865 477.1708 468.9880 0.0000 0.0600 0.0392 0.3177

NASA/TM—2013-218094 O–301
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8763 7.0315 1.0796 483.8413 11.5174 201.6137 1.5629

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 71650.531 0.581 166.275 420897.000 0.134275E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.176 EfDer = 1.000 SH = 0.135510E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.042 7.032 483.841 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.060 WH2O = 0.006 lbm/sec H2O = 0.083g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.916 2020.102 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64753.262 32220.148 2.433 590.487 242.729 468.502 1.930

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 263.19 -0.09 263.19 0.25 0.41 362.26

 MEAN 18.08 0.00 -0.02 263.19 -0.09 263.19 0.25 0.38

 HUB 15.21 0.00 -0.02 263.19 -0.09 263.19 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.06 46.36 6.70 349.89 437.89 6.74 478.27 468.97 2.90

 MEAN 49.48 42.30 7.18 307.80 405.05 6.74 478.27 468.97 2.90

 HUB 44.55 37.84 6.71 258.97 369.29 6.74 478.27 468.97 2.90

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 320.25 148.79 283.59 1071.10 0.30 2.33 2.04 9.02

 MEAN 18.01 326.93 160.78 284.66 1070.29 0.31 2.40 2.13 7.35

 HUB 15.22 353.49 207.88 285.90 1069.49 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 347.67 346.38 198.88 0.32 3040.16 0.92 0.91

 MEAN 306.64 319.85 145.86 0.30 2897.32 0.92 0.91 0.91 1.37

 HUB 259.19 290.47 51.31 0.27 3165.95 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.44 1.06 7.00 492.16 1.02 483.92 474.29 2.37

 MEAN 7.42 1.06 6.96 491.77 1.02 483.18 474.06 2.43

 HUB 7.46 1.06 6.92 492.51 1.02 482.46 474.54 2.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.68 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.46 27.13 23.50 3.63 0.93 0.33 1.63

 HUB 36.02 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 359.1950 161.2337 320.9746 1068.7252 0.3361 -0.1650 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4351 6.8829 481.7765 474.3153 2.5538 26.6715 30.6000 3.9285

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 315.2289 66.8308 308.0632 1071.3666 0.2942 0.0919 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4327 7.0048 484.1597 474.2689 491.5697 0.0151 0.2521

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 326.4850 0.0000 326.4850 1070.7200 0.3049 0.1439 0.5911

NASA/TM—2013-218094 O–302
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9624 483.5793 474.2612 0.0000 0.0600 0.0419 0.0033

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8706 7.4199 1.0552 492.1465 8.3054 252.6398 1.9584

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 51673.180 0.427 119.915 387944.250 0.135877E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.263 EfDer = 0.994 SH = 0.136154E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.042 7.420 492.146 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.060 WH2O = 0.006 lbm/sec H2O = 0.086g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 79.248 2002.984 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 62561.656 32220.143 2.351 545.479 231.993 424.468 1.830

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 275.26 -0.09 275.26 0.26 0.41 350.80

 MEAN 17.74 0.00 -0.02 275.26 -0.09 275.26 0.26 0.38

 HUB 15.05 0.00 -0.02 275.26 -0.09 275.26 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.16 46.36 4.80 341.71 438.86 7.09 486.06 474.22 2.21

 MEAN 47.66 43.40 4.26 302.02 408.70 7.09 486.06 474.22 2.21

 HUB 42.96 38.84 4.12 256.24 376.13 7.09 486.06 474.22 2.21

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 323.27 127.64 297.00 1078.54 0.30 2.26 1.98 8.75

 MEAN 17.51 330.76 144.28 297.64 1078.10 0.31 2.34 2.07 6.78

 HUB 14.85 358.20 198.04 298.47 1077.68 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.29 363.54 209.65 0.34 2530.46 0.92 0.91

 MEAN 298.07 335.02 153.79 0.31 2527.54 0.92 0.91 0.91 1.31

 HUB 252.84 303.46 54.79 0.28 2942.39 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.77 1.05 7.31 499.07 1.01 490.67 478.45 1.88

 MEAN 7.77 1.05 7.28 499.06 1.01 490.27 478.45 1.91

 HUB 7.83 1.05 7.26 500.20 1.02 489.89 479.15 1.93

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.26 35.22 31.50 3.72 0.93 0.27 1.40

 MEAN 25.86 27.33 23.50 3.83 0.92 0.29 1.62

 HUB 33.57 10.40 6.50 3.90 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 365.3914 145.2273 335.2909 1076.3815 0.3395 -0.1777 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7839 7.1947 488.7147 478.7023 2.0097 23.4193 31.5000 8.0807

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 334.9910 73.0760 326.9233 1078.2664 0.3107 -0.0039 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7783 7.2812 490.4258 478.6656 451.3937 0.0211 0.2102

 

NASA/TM—2013-218094 O–303
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 340.8406 0.0000 340.8406 1077.9141 0.3162 0.0882 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2467 490.1082 478.6437 0.0000 0.0600 0.0580 -0.0721

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8383 7.7597 1.0458 499.4449 7.2986 273.5878 2.1208

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45411.871 0.399 105.384 390658.406 0.136499E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.672 EfDer = 0.973 SH = 0.136753E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.042 7.760 499.445 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.060 WH2O = 0.006 lbm/sec H2O = 0.089g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.337 1988.296 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60811.727 32220.135 2.297 513.330 223.475 395.845 1.771 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 284.32 -0.10 284.32 0.26 0.40 334.17

 MEAN 16.97 0.00 -0.02 284.32 -0.10 284.32 0.26 0.38

 HUB 14.32 0.00 -0.02 284.32 -0.10 284.32 0.26 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.08 46.36 2.72 327.92 434.09 7.40 492.95 478.60 1.75

 MEAN 45.47 43.80 1.67 288.94 405.44 7.40 492.95 478.60 1.75

 HUB 40.63 37.84 2.79 243.81 374.60 7.40 492.95 478.60 1.75

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 323.36 104.31 306.08 1084.85 0.30 2.16 1.89 8.34

 MEAN 16.57 330.18 123.05 306.39 1084.66 0.30 2.24 1.97 6.35

 HUB 13.89 355.69 179.72 306.94 1084.49 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 321.45 375.28 217.14 0.35 1971.24 0.92 0.89

 MEAN 282.19 345.26 159.14 0.32 2041.02 0.92 0.89 0.89 1.26

 HUB 236.49 312.15 56.77 0.29 2497.69 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.03 1.04 7.56 504.84 1.01 496.44 481.76 1.55

 MEAN 8.04 1.04 7.55 505.03 1.01 496.27 481.88 1.56

 HUB 8.11 1.04 7.53 506.28 1.01 496.11 482.61 1.57

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.82 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 21.88 27.45 23.50 3.95 0.91 0.24 1.62

 HUB 30.35 10.48 6.50 3.98 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.973 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.8409 123.7383 336.8317 1083.3091 0.3312 -0.1451 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0563 7.4743 495.0349 482.0961 1.6246 20.1713 32.4000 12.2287

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 343.3124 76.9949 334.5672 1084.2694 0.3166 -0.0659 2.2705

 

NASA/TM—2013-218094 O–304
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0464 7.5131 495.9111 482.0678 432.2457 0.0292 0.1738

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 341.0918 0.0000 341.0918 1084.4015 0.3145 0.0345 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4944 496.0332 482.0249 0.0000 0.0600 0.0822 -0.1024

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7668 8.0192 1.0334 505.3833 5.9386 314.8394 2.4406

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 36951.527 0.358 85.751 404699.688 0.137055E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.731 EfDer = 0.938 SH = 0.137374E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 41.065 1951.042 8.019 505.383 1.000 1.000 0.980

 W Kg/sec = 18.666 Wdry = 41.060 WH2O = 0.006 lbm/sec H2O = 0.091g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.305 1976.580 1.381 0.249 53.353 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59457.977 32220.125 2.343 509.668 217.526 384.739 1.769

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 279.98 -0.10 279.98 0.26 0.39 315.99

 MEAN 15.91 0.00 -0.02 279.98 -0.10 279.98 0.26 0.36

 HUB 13.07 0.00 -0.02 279.98 -0.10 279.98 0.26 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.10 47.36 0.74 311.92 419.22 7.66 499.08 481.98 1.42

 MEAN 44.07 44.80 -0.73 270.94 389.68 7.66 499.08 481.98 1.42

 HUB 38.49 38.84 -0.35 222.53 357.71 7.66 499.08 481.98 1.42

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.94 89.02 302.10 1090.67 0.29 2.05 1.78 7.43

 MEAN 15.50 320.24 105.38 302.40 1090.48 0.29 2.13 1.86 5.75

 HUB 12.59 341.61 157.82 302.96 1090.30 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 305.45 371.62 216.43 0.34 1598.82 0.92 0.86

 MEAN 263.86 341.41 158.48 0.31 1634.69 0.92 0.86 0.86 1.23

 HUB 214.36 308.19 56.53 0.28 1988.26 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.24 1.03 7.78 509.76 1.01 501.79 484.46 1.30

 MEAN 8.24 1.03 7.77 509.86 1.01 501.62 484.52 1.31

 HUB 8.29 1.03 7.75 510.82 1.01 501.45 485.06 1.32

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.42 35.62 31.50 4.12 0.93 0.19 1.40

 MEAN 19.21 27.66 23.50 4.16 0.90 0.21 1.64

 HUB 27.52 10.57 6.50 4.07 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.938 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 361.8011 107.3132 345.5198 1088.3134 0.3324 -0.2499 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2470 7.6471 499.6270 484.6923 1.3940 17.2540 33.0000 15.7460

 

NASA/TM—2013-218094 O–305
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 359.0137 81.9811 349.5282 1088.4928 0.3298 -0.2784 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.2200 7.6310 499.7882 484.6480 410.5396 0.0752 0.1420

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 349.2614 0.0000 349.2614 1089.0973 0.3207 0.0013 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6479 500.3432 484.6172 0.0000 0.0600 0.1056 -0.2438

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6732 8.2051 1.0232 510.1464 4.7632 367.3015 2.8473

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 29639.402 0.318 68.782 428749.125 0.137716E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0801 Tt4 = 510.1464 T1 = 472.3241

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 235326.52 546.1075 88.4451 1.2598 0.8217 9.0220 1.0801 37.3740

NASA/TM—2013-218094 O–306
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.394 EfDer = 0.998 SH = 0.270771E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.283 7.939 487.555 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.856 WH2O = 0.014 lbm/sec H2O = 0.188g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 91.316 1848.641 1.381 0.249 53.357 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 70719.797 39910.719 3.110 831.557 267.353 619.754 2.318

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 204.11 -0.07 204.11 0.19 0.36 332.80

 MEAN 17.06 0.00 -0.02 204.11 -0.07 204.11 0.19 0.31

 HUB 12.51 0.00 -0.02 204.11 -0.07 204.11 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.69 50.47 7.22 322.67 381.86 7.74 484.21 472.71 5.17

 MEAN 52.59 47.20 5.39 266.83 336.00 7.74 484.21 472.71 5.17

 HUB 43.80 38.62 5.18 195.66 282.79 7.74 484.21 472.71 5.17

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.79 170.73 282.15 1075.20 0.31 7.29 6.52 16.04

 MEAN 18.04 344.69 196.32 283.32 1074.36 0.32 7.43 6.80 12.53

 HUB 15.00 388.53 263.09 285.90 1072.63 0.36 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.67 320.46 151.93 0.30 3523.66 0.92 0.91

 MEAN 282.09 296.02 85.77 0.28 3542.07 0.92 0.91 0.91 1.27

 HUB 234.61 287.32 28.48 0.27 3947.20 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.43 1.06 7.90 496.41 1.02 487.67 478.45 4.60

 MEAN 8.43 1.06 7.86 496.46 1.02 486.91 478.50 4.72

 HUB 8.49 1.07 7.76 497.47 1.02 485.35 479.21 4.97

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.18 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 34.72 16.84 12.70 4.14 0.92 0.25 2.22

 HUB 42.62 -5.69 -9.30 3.61 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 361.8842 195.9408 304.2490 1073.6385 0.3371 -0.0744 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4420 7.8116 486.2599 478.7265 4.8213 32.7821 35.4000 2.6179

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 309.3582 75.6785 299.9588 1076.7592 0.2873 0.2231 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4395 7.9755 489.0923 478.6266 554.9116 0.0141 0.3451

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 307.0449 0.0000 307.0449 1076.8800 0.2851 0.2480 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9680 489.2069 478.6050 0.0000 0.0600 0.0390 0.2107

NASA/TM—2013-218094 O–307
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8717 8.4244 1.0611 496.7801 9.2248 224.0840 1.7371

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57423.879 0.552 165.076 509667.219 0.273017E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 2.958 EfDer = 0.985 SH = 0.275024E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.283 8.424 496.780 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.856 WH2O = 0.014 lbm/sec H2O = 0.195g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 86.869 1831.397 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68968.656 39910.648 2.322 590.487 254.331 468.502 1.842 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 280.32 -0.10 280.32 0.26 0.40 328.42

 MEAN 18.08 0.00 -0.02 280.32 -0.10 280.32 0.26 0.37

 HUB 15.21 0.00 -0.02 280.32 -0.10 280.32 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.92 46.36 2.56 321.41 426.55 8.04 490.47 478.57 4.22

 MEAN 45.26 42.30 2.96 282.76 398.23 8.04 490.47 478.57 4.22

 HUB 40.33 37.84 2.49 237.89 367.72 8.04 490.47 478.57 4.22

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.95 104.32 305.64 1081.88 0.30 2.33 2.04 9.02

 MEAN 18.01 330.15 124.28 305.87 1081.76 0.31 2.40 2.13 7.35

 HUB 15.22 356.57 182.50 306.33 1081.65 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.38 373.72 215.06 0.35 2132.22 0.92 0.90

 MEAN 281.69 344.00 157.41 0.32 2239.97 0.92 0.90 0.90 1.24

 HUB 238.10 311.33 55.60 0.29 2779.65 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.73 1.04 8.21 502.14 1.01 493.76 481.85 3.77

 MEAN 8.74 1.04 8.20 502.41 1.01 493.65 482.02 3.79

 HUB 8.82 1.05 8.19 503.76 1.01 493.55 482.86 3.80

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 18.85 35.13 31.50 3.63 0.93 0.21 1.40

 MEAN 22.11 27.23 23.50 3.73 0.91 0.23 1.63

 HUB 30.79 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.985 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 367.2084 124.6259 345.4134 1079.8754 0.3400 -0.1955 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7556 8.0908 491.9390 482.2929 4.0029 19.8396 30.6000 10.7604

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 341.2035 72.3376 333.4473 1081.5011 0.3155 -0.0500 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7463 8.1706 493.4186 482.2319 491.5697 0.0266 0.1575

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 354.0725 0.0000 354.0725 1080.7107 0.3276 0.0189 0.5911

NASA/TM—2013-218094 O–308
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1033 492.7000 482.2209 0.0000 0.0600 0.0730 -0.1697

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7931 8.7202 1.0351 502.7703 5.9903 305.8959 2.3713

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37292.016 0.366 107.203 472668.094 0.275632E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.421 EfDer = 0.943 SH = 0.276185E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.283 8.720 502.770 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.856 WH2O = 0.014 lbm/sec H2O = 0.200g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.427 1820.455 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67696.578 39910.633 2.207 545.479 247.182 424.468 1.717

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 297.85 -0.10 297.85 0.27 0.40 318.83

 MEAN 17.74 0.00 -0.02 297.85 -0.10 297.85 0.27 0.38

 HUB 15.05 0.00 -0.02 297.85 -0.10 297.85 0.27 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.51 46.36 0.15 313.91 432.80 8.28 495.64 482.13 3.54

 MEAN 42.98 43.40 -0.42 277.44 407.12 8.28 495.64 482.13 3.54

 HUB 38.33 38.84 -0.51 235.39 379.70 8.28 495.64 482.13 3.54

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 335.11 78.93 325.68 1086.16 0.31 2.26 1.98 8.75

 MEAN 17.51 341.80 104.71 325.36 1086.50 0.31 2.34 2.07 6.78

 HUB 14.85 367.90 171.65 325.40 1086.84 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 309.84 399.24 230.91 0.37 1565.61 0.92 0.86

 MEAN 273.81 366.68 169.10 0.34 1834.98 0.92 0.86 0.86 1.18

 HUB 232.26 330.99 60.61 0.30 2550.59 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.94 1.02 8.37 506.70 1.01 497.68 484.46 3.31

 MEAN 8.97 1.03 8.39 507.38 1.01 498.00 484.86 3.27

 HUB 9.07 1.04 8.39 509.18 1.01 498.31 485.92 3.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.62 35.34 31.50 3.84 0.93 0.14 1.40

 MEAN 17.84 27.46 23.50 3.96 0.90 0.18 1.62

 HUB 27.81 10.55 6.50 4.05 0.90 0.24 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.943 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 382.1578 105.3997 367.3357 1084.3422 0.3524 -0.2100 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9878 8.2574 496.0239 485.1354 3.4846 16.0098 31.5000 15.4902

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 369.3446 80.5700 360.4496 1085.1913 0.3403 -0.1554 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9699 8.2877 496.7970 485.0863 451.3937 0.0392 0.1132

 

NASA/TM—2013-218094 O–309
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 376.8004 0.0000 376.8004 1084.7020 0.3474 -0.0453 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2243 496.3502 485.0465 0.0000 0.0600 0.1039 -0.2591

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6649 8.9304 1.0241 507.7545 4.9844 347.8526 2.6965

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31031.092 0.323 89.205 478568.063 0.276768E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.512 EfDer = 0.883 SH = 0.277323E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.283 8.930 507.754 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.856 WH2O = 0.014 lbm/sec H2O = 0.203g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.847 1811.498 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66998.789 39910.617 2.116 513.330 242.558 395.845 1.632

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 313.24 -0.11 313.24 0.29 0.40 304.46

 MEAN 16.97 0.00 -0.02 313.24 -0.11 313.24 0.29 0.38

 HUB 14.32 0.00 -0.02 313.24 -0.11 313.24 0.29 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.89 46.36 -2.47 301.24 434.66 8.44 499.87 484.94 3.07

 MEAN 40.29 43.80 -3.51 265.43 410.65 8.44 499.87 484.94 3.07

 HUB 35.58 37.84 -2.26 223.97 385.14 8.44 499.87 484.94 3.07

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.75 51.53 341.89 1089.33 0.32 2.16 1.89 8.34

 MEAN 16.57 350.60 80.87 341.15 1090.04 0.32 2.24 1.97 6.35

 HUB 13.89 373.75 153.14 340.93 1090.73 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.29 419.89 243.77 0.39 974.92 0.92 0.81

 MEAN 259.23 384.96 178.35 0.35 1342.18 0.92 0.81 0.81 1.13

 HUB 217.25 346.91 64.11 0.32 2128.64 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.06 1.01 8.45 510.20 1.00 500.60 486.36 2.99

 MEAN 9.11 1.02 8.48 511.13 1.01 501.25 486.88 2.93

 HUB 9.21 1.03 8.50 513.10 1.01 501.88 488.00 2.86

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.57 35.49 31.50 3.99 0.93 0.08 1.40

 MEAN 13.34 27.60 23.50 4.10 0.89 0.12 1.62

 HUB 24.19 10.65 6.50 4.15 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.883 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 384.6487 81.3258 375.9531 1088.2328 0.3535 -0.1724 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1175 8.3725 499.5940 487.1223 3.0836 12.2061 32.4000 20.1939

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 385.7268 86.5072 375.9011 1088.1642 0.3545 -0.2086 2.2705

 

NASA/TM—2013-218094 O–310
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0916 8.3447 499.5270 487.0879 432.2457 0.0501 0.0773

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 384.2344 0.0000 384.2344 1088.2654 0.3531 -0.0951 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3016 499.6192 487.0105 0.0000 0.0600 0.1323 -0.2755

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4537 9.0386 1.0121 511.4777 3.7234 430.6671 3.3385

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23181.170 0.266 66.639 498542.094 0.277885E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.383 EfDer = 0.820 SH = 0.278435E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 50.870 1792.283 9.039 511.478 1.000 1.000 0.980

 W Kg/sec = 23.123 Wdry = 50.856 WH2O = 0.014 lbm/sec H2O = 0.205g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.155 1804.892 1.381 0.249 53.357 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66674.844 39910.598 2.119 509.668 240.532 384.739 1.600

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 313.97 -0.11 313.97 0.29 0.39 288.54

 MEAN 15.91 0.00 -0.02 313.97 -0.11 313.97 0.29 0.37

 HUB 13.07 0.00 -0.02 313.97 -0.11 313.97 0.29 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.40 47.36 -4.96 286.54 425.14 8.54 503.56 486.90 2.71

 MEAN 38.42 44.80 -6.38 248.89 400.72 8.54 503.56 486.90 2.71

 HUB 33.08 38.84 -5.76 204.42 374.71 8.54 503.56 486.90 2.71

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 344.85 33.37 343.23 1092.41 0.32 2.05 1.78 7.43

 MEAN 15.50 348.00 61.72 342.48 1093.19 0.32 2.13 1.86 5.75

 HUB 12.59 366.89 132.02 342.32 1093.94 0.34 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.59 423.00 247.23 0.39 600.58 0.92 0.75

 MEAN 242.39 387.21 180.67 0.35 958.27 0.92 0.75 0.75 1.10

 HUB 196.92 348.41 64.89 0.32 1663.58 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.11 1.01 8.51 512.99 1.00 503.43 487.76 2.71

 MEAN 9.15 1.01 8.54 513.89 1.00 504.16 488.25 2.65

 HUB 9.24 1.02 8.56 515.66 1.01 504.85 489.22 2.58

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.55 35.76 31.50 4.26 0.93 0.03 1.40

 MEAN 10.22 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.09 10.73 6.50 4.23 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.820 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 397.9055 62.8541 392.9099 1090.2596 0.3650 -0.2853 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1565 8.3616 501.4596 488.4745 2.8763 9.0886 33.0000 23.9114

 

NASA/TM—2013-218094 O–311
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 411.8685 94.0505 400.9865 1089.2782 0.3781 -0.4489 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0973 8.2531 500.5510 488.4172 410.5396 0.1137 0.0508

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 400.4393 0.0000 400.4393 1090.0924 0.3673 -0.1033 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2795 501.2964 488.3655 0.0000 0.0600 0.1453 -0.4071

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2232 9.0773 1.0043 514.1764 2.6988 546.9078 4.2396

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 16802.309 0.213 48.302 530669.063 0.279027E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0546 Tt4 = 514.1764 T1 = 487.5555

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 165730.47 476.4251 91.3165 1.1433 0.6892 5.3937 1.0546 37.3740

NASA/TM—2013-218094 O–312
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 15435 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 6.464 EfDer = 1.000 SH = 0.460297E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.713 1582.119 9.337 500.813 1.000 1.000 0.980

 W Kg/sec = 22.597 Wdry = 49.690 WH2O = 0.023 lbm/sec H2O = 0.367g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.903 1610.127 1.381 0.249 53.363 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60042.984 38999.914 3.693 831.557 225.186 619.754 2.752

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 173.29 -0.06 173.29 0.16 0.31 289.86

 MEAN 17.06 0.00 -0.02 173.29 -0.06 173.29 0.16 0.27

 HUB 12.51 0.00 -0.02 173.29 -0.06 173.29 0.16 0.23

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.69 50.47 8.22 284.83 333.46 9.18 498.40 482.30 5.87

 MEAN 53.66 47.20 6.46 235.54 292.47 9.18 498.40 482.30 5.87

 HUB 44.92 38.62 6.30 172.72 244.71 9.18 498.40 482.30 5.87

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 286.13 155.78 240.00 1090.11 0.26 7.29 6.52 16.04

 MEAN 18.04 298.46 176.31 240.81 1089.40 0.27 7.43 6.80 12.53

 HUB 15.00 335.12 231.35 242.46 1088.07 0.31 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 284.83 272.49 129.05 0.25 3215.07 0.92 0.91

 MEAN 249.02 251.55 72.70 0.23 3180.99 0.92 0.91 0.91 1.30

 HUB 207.10 243.67 24.25 0.22 3470.96 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.79 1.05 9.33 507.94 1.01 501.37 486.70 5.34

 MEAN 9.78 1.05 9.29 507.86 1.01 500.71 486.68 5.46

 HUB 9.82 1.05 9.20 508.51 1.02 499.49 487.14 5.67

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.99 28.27 24.20 4.07 0.93 0.31 1.80

 MEAN 36.21 16.80 12.70 4.10 0.93 0.28 2.22

 HUB 43.66 -5.71 -9.30 3.59 0.93 0.17 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 312.4956 175.9697 258.2405 1088.9121 0.2870 -0.0701 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.7911 9.2541 500.2640 486.8479 5.5332 34.2712 35.4000 1.1288

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 263.4014 64.4360 255.3983 1091.3776 0.2413 0.2502 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.7903 9.4066 502.5335 486.7440 554.9116 0.0114 0.3650

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 261.3619 0.0000 261.3619 1091.4661 0.2395 0.2710 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.3996 502.6195 486.7254 0.0000 0.0600 0.0370 0.2368

NASA/TM—2013-218094 O–313
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8770 9.7770 1.0471 508.1024 7.2900 217.3285 1.6847

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 45416.004 0.560 127.587 485552.625 0.463505E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.939 EfDer = 0.992 SH = 0.466217E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.713 1582.119 9.777 508.102 1.000 1.000 0.980

 W Kg/sec = 22.597 Wdry = 49.689 WH2O = 0.023 lbm/sec H2O = 0.379g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.977 1598.533 1.380 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58830.180 38999.824 2.726 590.487 216.618 468.502 2.163

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 239.11 -0.08 239.11 0.22 0.34 286.66

 MEAN 18.08 0.00 -0.02 239.11 -0.08 239.11 0.22 0.32

 HUB 15.21 0.00 -0.02 239.11 -0.08 239.11 0.22 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.89 46.36 3.53 283.73 371.11 9.46 503.51 486.69 5.03

 MEAN 46.24 42.30 3.94 249.60 345.71 9.46 503.51 486.69 5.03

 HUB 41.30 37.84 3.46 210.00 318.29 9.46 503.51 486.69 5.03

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 279.17 98.37 261.27 1095.46 0.25 2.33 2.04 9.02

 MEAN 18.01 285.41 114.31 261.52 1095.27 0.26 2.40 2.13 7.35

 HUB 15.22 308.39 162.83 261.90 1095.09 0.28 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 281.93 319.31 183.56 0.29 2010.37 0.92 0.91

 MEAN 248.66 294.01 134.34 0.27 2060.27 0.92 0.91 0.91 1.27

 HUB 210.18 266.15 47.35 0.24 2479.98 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.06 1.03 9.62 512.56 1.01 506.30 489.31 4.61

 MEAN 10.07 1.03 9.61 512.67 1.01 506.13 489.38 4.63

 HUB 10.13 1.04 9.59 513.60 1.01 505.97 489.95 4.65

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 20.63 35.09 31.50 3.59 0.93 0.23 1.40

 MEAN 23.61 27.19 23.50 3.69 0.92 0.25 1.63

 HUB 31.87 10.25 6.50 3.75 0.92 0.29 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.992 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 315.9354 114.6342 294.4048 1093.9656 0.2888 -0.1855 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.0825 9.5227 504.9305 489.5962 4.8016 21.2748 30.6000 9.3252

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 291.1090 61.7172 284.4915 1095.2773 0.2658 -0.0180 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.0777 9.6012 506.1400 489.5370 491.5697 0.0200 0.1760

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 301.4410 0.0000 301.4410 1094.7430 0.2754 0.0438 0.5911

NASA/TM—2013-218094 O–314
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.5472 505.6486 489.5318 0.0000 0.0600 0.0646 -0.1310

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8185 10.0564 1.0286 512.9418 4.8395 292.4895 2.2674

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30151.537 0.379 84.705 449828.469 0.467087E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 0.475 EfDer = 0.957 SH = 0.468075E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.713 1582.119 10.056 512.942 1.000 1.000 0.980

 W Kg/sec = 22.597 Wdry = 49.689 WH2O = 0.023 lbm/sec H2O = 0.387g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.263 1590.975 1.380 0.249 53.363 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57913.648 38999.797 2.578 545.479 211.602 424.468 2.006

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 254.81 -0.09 254.81 0.23 0.34 278.64

 MEAN 17.74 0.00 -0.02 254.81 -0.09 254.81 0.23 0.32

 HUB 15.05 0.00 -0.02 254.81 -0.09 254.81 0.23 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 47.41 46.36 1.05 277.10 376.51 9.69 507.73 489.45 4.41

 MEAN 43.88 43.40 0.48 244.91 353.48 9.69 507.73 489.45 4.41

 HUB 39.21 38.84 0.37 207.79 328.85 9.69 507.73 489.45 4.41

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 288.90 76.15 278.69 1099.00 0.26 2.26 1.98 8.75

 MEAN 17.51 295.05 97.15 278.59 1099.15 0.27 2.34 2.07 6.78

 HUB 14.85 318.11 153.37 278.69 1099.30 0.29 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 273.51 341.49 197.36 0.31 1510.36 0.92 0.88

 MEAN 241.71 313.86 144.55 0.29 1702.40 0.92 0.88 0.88 1.20

 HUB 205.03 283.44 51.66 0.26 2278.88 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.27 1.02 9.79 516.29 1.01 509.59 491.36 4.16

 MEAN 10.29 1.02 9.80 516.71 1.01 509.73 491.61 4.14

 HUB 10.37 1.03 9.80 517.99 1.01 509.87 492.35 4.12

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 15.28 35.30 31.50 3.80 0.93 0.16 1.40

 MEAN 19.23 27.42 23.50 3.92 0.90 0.20 1.62

 HUB 28.82 10.50 6.50 4.00 0.90 0.26 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 328.3093 97.7920 313.4066 1097.6541 0.2991 -0.1996 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.3064 9.6942 508.3478 491.8291 4.3134 17.3294 31.5000 14.1706

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 314.9861 68.7121 307.4003 1098.3998 0.2868 -0.1222 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.2958 9.7319 509.0356 491.7859 451.3937 0.0305 0.1303

 

NASA/TM—2013-218094 O–315
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 320.6933 0.0000 320.6933 1098.0842 0.2920 -0.0228 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.6803 508.7444 491.7556 0.0000 0.0600 0.0950 -0.2222

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7087 10.2624 1.0205 516.9987 4.0569 331.2360 2.5677

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 25277.090 0.338 71.011 455894.188 0.468898E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-2.641 EfDer = 0.902 SH = 0.469807E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.713 1582.119 10.262 516.999 1.000 1.000 0.980

 W Kg/sec = 22.597 Wdry = 49.689 WH2O = 0.023 lbm/sec H2O = 0.392g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.092 1584.720 1.380 0.249 53.364 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57352.496 38999.773 2.466 513.330 208.173 395.845 1.902

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 268.14 -0.09 268.14 0.24 0.34 266.34

 MEAN 16.97 0.00 -0.02 268.14 -0.09 268.14 0.24 0.32

 HUB 14.32 0.00 -0.02 268.14 -0.09 268.14 0.24 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.77 46.36 -1.59 265.92 377.70 9.85 511.23 491.66 3.95

 MEAN 41.16 43.80 -2.64 234.31 356.15 9.85 511.23 491.66 3.95

 HUB 36.42 37.84 -1.42 197.71 333.21 9.85 511.23 491.66 3.95

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 296.92 52.49 292.25 1101.72 0.27 2.16 1.89 8.34

 MEAN 16.57 301.74 76.44 291.89 1102.13 0.27 2.24 1.97 6.35

 HUB 13.89 322.42 137.06 291.83 1102.53 0.29 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 260.67 358.81 208.18 0.33 992.79 0.92 0.82

 MEAN 228.83 329.28 152.39 0.30 1268.50 0.92 0.82 0.82 1.15

 HUB 191.77 296.92 54.71 0.27 1905.15 0.92 0.82

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.39 1.01 9.89 519.20 1.00 512.12 492.89 3.84

 MEAN 10.43 1.02 9.91 519.81 1.01 512.50 493.23 3.79

 HUB 10.52 1.02 9.92 521.22 1.01 512.88 494.02 3.74

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 10.18 35.46 31.50 3.96 0.93 0.10 1.40

 MEAN 14.68 27.57 23.50 4.07 0.89 0.14 1.62

 HUB 25.16 10.62 6.50 4.12 0.89 0.21 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.902 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 329.7592 76.8714 320.6742 1100.8849 0.2995 -0.1641 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4412 9.8193 511.3493 493.4235 3.9217 13.4805 32.4000 18.9195

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 328.3530 73.6400 319.9888 1100.9681 0.2982 -0.1769 2.2705

 

NASA/TM—2013-218094 O–316
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4248 9.8090 511.4234 493.3990 432.2457 0.0403 0.0935

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 326.6282 0.0000 326.6282 1101.0658 0.2966 -0.0762 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7719 511.5140 493.3346 0.0000 0.0600 0.1255 -0.2455

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.5219 10.3786 1.0113 520.0765 3.0779 405.4850 3.1433

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 19177.479 0.282 53.875 475193.625 0.470600E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-5.508 EfDer = 0.839 SH = 0.471520E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 49.713 1582.119 10.379 520.077 1.000 1.000 0.980

 W Kg/sec = 22.597 Wdry = 49.689 WH2O = 0.023 lbm/sec H2O = 0.396g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.505 1580.024 1.380 0.249 53.364 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57044.168 38999.746 2.469 509.668 206.455 384.739 1.864

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 268.62 -0.09 268.62 0.24 0.33 252.59

 MEAN 15.91 0.00 -0.02 268.62 -0.09 268.62 0.24 0.31

 HUB 13.07 0.00 -0.02 268.62 -0.09 268.62 0.24 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 43.29 47.36 -4.07 252.94 369.03 9.97 514.29 493.23 3.58

 MEAN 39.29 44.80 -5.51 219.70 347.08 9.97 514.29 493.23 3.58

 HUB 33.91 38.84 -4.93 180.45 323.65 9.97 514.29 493.23 3.58

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 295.29 36.82 292.99 1104.32 0.27 2.05 1.78 7.43

 MEAN 15.50 298.66 59.75 292.63 1104.78 0.27 2.13 1.86 5.75

 HUB 12.59 315.69 118.52 292.60 1105.22 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 247.69 360.98 210.87 0.33 662.32 0.92 0.77

 MEAN 213.97 330.78 154.22 0.30 927.44 0.92 0.77 0.77 1.12

 HUB 173.83 297.78 55.30 0.27 1493.41 0.92 0.77

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 10.46 1.01 9.96 521.54 1.00 514.55 494.04 3.55

 MEAN 10.49 1.01 9.98 522.13 1.00 514.97 494.36 3.50

 HUB 10.56 1.02 9.99 523.39 1.01 515.39 495.04 3.45

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 7.16 35.74 31.50 4.24 0.93 0.06 1.40

 MEAN 11.54 27.79 23.50 4.29 0.87 0.10 1.64

 HUB 22.05 10.70 6.50 4.20 0.87 0.17 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.839 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 339.5204 60.8445 334.0240 1102.7671 0.3079 -0.2727 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 10.4952 9.8363 513.1027 494.5425 3.6966 10.3236 33.0000 22.6764

 

NASA/TM—2013-218094 O–317
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 348.3947 79.5562 339.1898 1102.2455 0.3161 -0.3989 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 10.4561 9.7657 512.6124 494.5106 410.5396 0.0940 0.0656

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 339.2617 0.0000 339.2617 1102.7892 0.3076 -0.0907 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 9.7765 513.1163 494.4556 0.0000 0.0600 0.1424 -0.3784

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.3138 10.4305 1.0050 522.3540 2.2775 506.8609 3.9292

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 14190.972 0.231 39.867 506359.313 0.472337E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0430 Tt4 = 522.3540 T1 = 500.8125 

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 134213.08 377.0453 76.9027 1.1171 0.7203 6.4643 1.0430 37.3740

NASA/TM—2013-218094 O–318
 100μm, ISA +36R

*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 39000 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.093 EfDer = 0.958 SH = 0.908425E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.373 2465.077 4.265 477.918 1.000 1.000 0.980

 W Kg/sec = 11.988 Wdry = 26.371 WH2O = 0.002 lbm/sec H2O = 0.035g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.260 2568.094 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66790.227 20692.744 3.256 831.557 255.430 619.754 2.426

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 192.77 -0.07 192.77 0.18 0.46 462.32

 MEAN 17.06 0.00 -0.02 192.77 -0.07 192.77 0.18 0.39

 HUB 12.51 0.00 -0.02 192.77 -0.07 192.77 0.18 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.52 50.47 16.05 443.79 483.91 4.17 474.93 460.63 1.39

 MEAN 62.29 47.20 15.09 367.00 414.60 4.17 474.93 460.63 1.39

 HUB 54.39 38.62 15.77 269.11 331.08 4.17 474.93 460.63 1.39

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 398.81 304.11 258.01 1074.42 0.37 7.29 6.52 16.04

 MEAN 18.04 404.26 308.37 261.40 1071.31 0.38 7.43 6.80 12.53

 HUB 15.00 438.82 348.91 266.13 1067.45 0.41 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 443.79 293.39 139.68 0.27 6275.13 0.92 0.88

 MEAN 387.99 273.26 79.62 0.26 5562.90 0.92 0.88 0.88 1.74

 HUB 322.68 267.42 26.24 0.25 5234.54 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.91 1.15 4.47 499.63 1.05 486.84 473.12 0.91

 MEAN 4.84 1.13 4.39 497.16 1.04 484.02 471.80 1.00

 HUB 4.80 1.13 4.28 496.03 1.04 480.54 471.21 1.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.69 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.71 16.94 12.70 4.24 0.95 0.51 2.22

 HUB 52.67 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.958 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 416.3328 307.7709 280.3749 1070.9081 0.3888 -0.0371 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8446 4.3708 483.6685 472.0388 1.0176 47.6669 35.4000 -12.2669

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 278.2785 68.0754 269.8234 1079.4069 0.2578 0.5066 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8331 4.6176 491.3800 471.9306 554.9116 0.0343 0.5988

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 277.0878 0.0000 277.0878 1079.4529 0.2567 0.4792 1.3089

NASA/TM—2013-218094 O–319
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5978 491.4332 471.8736 0.0000 0.0600 0.0824 0.4645

 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8208 4.8105 1.1280 497.6069 19.6899 169.7458 1.3159

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 122439.500 0.622 182.479 267774.969 0.929228E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.627 EfDer = 0.961 SH = 0.947894E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.373 2465.077 4.811 497.607 1.000 1.000 0.980

 W Kg/sec = 11.988 Wdry = 26.370 WH2O = 0.002 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.934 2516.781 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62323.992 20692.711 2.556 590.487 231.060 468.502 2.028

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 253.31 -0.09 253.31 0.23 0.47 451.33

 MEAN 18.08 0.00 -0.02 253.31 -0.09 253.31 0.23 0.43

 HUB 15.21 0.00 -0.02 253.31 -0.09 253.31 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.19 46.36 13.83 442.07 509.58 4.63 492.45 471.87 0.77

 MEAN 56.93 42.30 14.63 388.90 464.19 4.63 492.45 471.87 0.77

 HUB 52.26 37.84 14.42 327.20 413.86 4.63 492.45 471.87 0.77

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 366.89 251.97 266.68 1093.80 0.34 2.33 2.04 9.02

 MEAN 18.01 367.03 249.31 269.36 1091.34 0.34 2.40 2.13 7.35

 HUB 15.22 389.62 278.63 272.33 1088.91 0.36 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 439.27 325.88 187.30 0.30 5147.08 0.92 0.88

 MEAN 387.43 302.70 138.11 0.28 4491.69 0.92 0.88 0.88 1.69

 HUB 327.48 276.68 48.84 0.25 4242.96 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.38 1.12 4.98 515.41 1.04 504.59 481.05 0.52

 MEAN 5.31 1.10 4.91 513.15 1.03 502.31 479.93 0.56

 HUB 5.28 1.10 4.84 512.29 1.03 500.08 479.52 0.60

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.38 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.79 27.15 23.50 3.65 0.95 0.51 1.63

 HUB 45.66 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 393.0298 250.0125 303.2593 1090.1068 0.3605 -0.1096 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3183 4.8670 501.1943 480.1691 0.5772 39.5028 30.6000 -8.9028

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 293.4253 62.2083 286.7552 1096.0673 0.2677 0.3566 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3125 5.0577 506.6919 480.1088 491.5697 0.0241 0.4543

 

NASA/TM—2013-218094 O–320
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 304.1313 0.0000 304.1313 1095.5004 0.2776 0.3483 0.5911

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0242 506.1777 480.0712 0.0000 0.0600 0.0623 0.2752

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8373 5.2968 1.1011 513.6143 16.0079 191.4926 1.4844

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 99558.648 0.516 148.378 243201.391 0.953803E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.642 EfDer = 0.976 SH = 0.961172E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.373 2465.077 5.297 513.614 1.000 1.000 0.980

 W Kg/sec = 11.988 Wdry = 26.370 WH2O = 0.003 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 72.832 2477.252 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58419.504 20692.699 2.559 545.479 213.201 424.468 1.991

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 257.03 -0.09 257.03 0.23 0.46 433.86

 MEAN 17.74 0.00 -0.02 257.03 -0.09 257.03 0.23 0.42

 HUB 15.05 0.00 -0.02 257.03 -0.09 257.03 0.23 0.38

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.24 46.36 12.88 431.74 502.54 5.10 508.30 480.06 0.47

 MEAN 56.04 43.40 12.64 381.59 460.16 5.10 508.30 480.06 0.47

 HUB 51.56 38.84 12.72 323.75 413.45 5.10 508.30 480.06 0.47

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 358.78 235.60 270.58 1109.73 0.32 2.26 1.98 8.75

 MEAN 17.51 360.90 236.13 272.93 1107.63 0.33 2.34 2.07 6.78

 HUB 14.85 385.42 269.51 275.52 1105.56 0.35 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 426.15 330.94 190.55 0.30 4669.06 0.92 0.89

 MEAN 376.60 306.95 140.47 0.28 4135.45 0.92 0.89 0.89 1.64

 HUB 319.45 280.01 49.95 0.25 4003.50 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.86 1.11 5.45 529.76 1.03 519.42 487.75 0.33

 MEAN 5.79 1.09 5.38 527.92 1.03 517.45 486.91 0.35

 HUB 5.77 1.09 5.31 527.46 1.03 515.52 486.71 0.37

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 41.05 35.15 31.50 3.65 0.93 0.51 1.40

 MEAN 40.87 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.37 10.27 6.50 3.77 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.976 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 388.0721 237.6827 306.7684 1106.3553 0.3508 -0.1174 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8023 5.3349 516.2747 487.1213 0.3650 37.7683 31.5000 -6.2683

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 301.9044 65.8584 294.6335 1111.4634 0.2716 0.3050 2.3726

 

NASA/TM—2013-218094 O–321
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7986 5.5125 521.0544 487.0793 451.3937 0.0187 0.4292

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 306.9981 0.0000 306.9981 1111.1865 0.2763 0.3329 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4905 520.8052 487.0457 0.0000 0.0600 0.0498 0.2529

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8575 5.7855 1.0923 528.3816 14.7677 196.9344 1.5266

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 91858.898 0.506 136.903 241682.203 0.966885E-04 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =11.056 EfDer = 0.986 SH = 0.974041E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.373 2465.077 5.785 528.381 1.000 1.000 0.980

 W Kg/sec = 11.988 Wdry = 26.370 WH2O = 0.003 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 67.632 2442.389 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54981.086 20692.689 2.593 513.330 197.983 395.845 1.999

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 257.06 -0.09 257.06 0.23 0.44 410.49

 MEAN 16.97 0.00 -0.02 257.06 -0.09 257.06 0.23 0.40

 HUB 14.32 0.00 -0.02 257.06 -0.09 257.06 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.19 46.36 11.83 414.32 487.66 5.58 523.07 487.03 0.30

 MEAN 54.86 43.80 11.06 365.07 446.56 5.58 523.07 487.03 0.30

 HUB 50.16 37.84 12.32 308.05 401.28 5.58 523.07 487.03 0.30

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 345.49 215.78 269.81 1123.99 0.31 2.16 1.89 8.34

 MEAN 16.57 347.54 216.42 271.93 1122.09 0.31 2.24 1.97 6.35

 HUB 13.89 370.51 249.15 274.23 1120.23 0.33 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.14 330.21 190.36 0.29 4075.71 0.92 0.90

 MEAN 356.53 305.90 140.11 0.27 3588.44 0.92 0.90 0.90 1.60

 HUB 298.80 278.69 49.65 0.25 3461.99 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.31 1.09 5.91 542.48 1.03 532.88 493.34 0.23

 MEAN 6.24 1.08 5.85 540.79 1.02 531.08 492.61 0.24

 HUB 6.23 1.08 5.78 540.35 1.02 529.32 492.42 0.25

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.65 35.20 31.50 3.70 0.93 0.48 1.40

 MEAN 38.52 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.26 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.986 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 369.1907 217.6379 298.2206 1121.1995 0.3293 -0.0930 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.2539 5.8072 530.2519 492.7838 0.2466 36.1215 32.4000 -3.7215

 

NASA/TM—2013-218094 O–322
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 299.5086 67.1710 291.8792 1125.1500 0.2662 0.2678 2.2705

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.2520 5.9554 533.9973 492.7579 432.2457 0.0146 0.4078

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 297.1122 0.0000 297.1122 1125.2611 0.2640 0.3186 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9495 534.1124 492.7278 0.0000 0.0600 0.0413 0.2536

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8705 6.2409 1.0787 541.2076 12.8265 212.3262 1.6459

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 79796.227 0.484 118.925 247257.016 0.980550E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.604 EfDer = 0.993 SH = 0.988896E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 26.373 2465.077 6.241 541.207 1.000 1.000 0.980

 W Kg/sec = 11.988 Wdry = 26.370 WH2O = 0.003 lbm/sec H2O = 0.048g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 63.453 2413.275 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 52049.906 20692.678 2.744 509.668 185.753 384.739 2.071

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 245.10 -0.08 245.10 0.22 0.41 385.80

 MEAN 15.91 0.00 -0.02 245.10 -0.08 245.10 0.22 0.37

 HUB 13.07 0.00 -0.02 245.10 -0.08 245.10 0.22 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.13 47.36 10.77 394.10 464.17 6.04 536.38 492.72 0.21

 MEAN 54.40 44.80 9.60 342.32 421.09 6.04 536.38 492.72 0.21

 HUB 48.93 38.84 10.09 281.16 373.06 6.04 536.38 492.72 0.21

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 328.03 202.75 257.87 1136.81 0.29 2.05 1.78 7.43

 MEAN 15.50 327.18 198.70 259.93 1134.85 0.29 2.13 1.86 5.75

 HUB 12.59 344.36 223.31 262.13 1132.91 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 385.92 316.31 183.17 0.28 3638.86 0.92 0.91

 MEAN 333.38 292.75 134.69 0.26 3080.64 0.92 0.91 0.91 1.59

 HUB 270.83 266.40 47.52 0.24 2812.61 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.73 1.08 6.36 553.79 1.02 545.14 498.07 0.17

 MEAN 6.66 1.07 6.29 551.86 1.02 543.26 497.27 0.18

 HUB 6.62 1.06 6.21 550.93 1.02 541.40 496.89 0.18

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.18 35.39 31.50 3.89 0.93 0.47 1.40

 MEAN 37.39 27.39 23.50 3.89 0.94 0.45 1.64

 HUB 40.43 10.28 6.50 3.78 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.993 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 358.4227 202.3385 295.8479 1133.3831 0.3162 -0.1732 2.0437

 

NASA/TM—2013-218094 O–323
 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6609 6.2205 541.8698 497.3965 0.1825 34.3693 33.0000 -1.3693

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 302.3682 69.0460 294.3793 1136.4908 0.2661 0.1495 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6589 6.3433 544.8466 497.3767 410.5396 0.0252 0.3836

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 294.1221 0.0000 294.1221 1136.8942 0.2587 0.3069 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.3556 545.2419 497.3628 0.0000 0.0600 0.0372 0.1818

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8794 6.6543 1.0662 552.1941 10.9871 231.9936 1.7984

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 68363.391 0.459 101.886 259212.141 0.995576E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1554 Tt4 = 552.1941 T1 = 477.9176

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 462016.69 688.5695 87.2603 1.5604 0.8406 15.0933 1.1554 37.3740

NASA/TM—2013-218094 O–324
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 38334 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.204 EfDer = 0.957 SH = 0.880660E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.399 2387.497 4.199 471.473 1.000 1.000 0.980

 W Kg/sec = 11.545 Wdry = 25.397 WH2O = 0.002 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.771 2504.213 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 64384.207 19929.014 3.351 831.557 248.142 619.754 2.498

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 185.82 -0.06 185.82 0.18 0.44 450.82

 MEAN 17.06 0.00 -0.02 185.82 -0.06 185.82 0.18 0.38

 HUB 12.51 0.00 -0.02 185.82 -0.06 185.82 0.18 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.62 50.47 16.15 429.82 468.33 4.11 468.70 456.85 1.75

 MEAN 62.40 47.20 15.20 355.45 401.14 4.11 468.70 456.85 1.75

 HUB 54.52 38.62 15.90 260.64 320.15 4.11 468.70 456.85 1.75

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 386.14 294.87 249.30 1066.71 0.36 7.29 6.52 16.04

 MEAN 18.04 391.24 298.93 252.41 1063.77 0.37 7.43 6.80 12.53

 HUB 15.00 424.30 337.82 256.73 1060.14 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 429.82 283.49 134.95 0.27 6084.50 0.92 0.88

 MEAN 375.78 263.85 76.85 0.25 5392.57 0.92 0.88 0.88 1.74

 HUB 312.52 257.98 25.29 0.24 5068.04 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.80 1.14 4.39 491.86 1.04 479.87 469.19 1.16

 MEAN 4.73 1.13 4.32 489.54 1.04 477.23 467.88 1.28

 HUB 4.70 1.12 4.21 488.46 1.04 473.98 467.29 1.44

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.79 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.82 16.93 12.70 4.23 0.95 0.51 2.22

 HUB 52.77 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.957 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 402.8450 298.3478 270.6894 1063.3987 0.3788 -0.0371 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.7407 4.2991 476.9040 468.1147 1.2933 47.7827 35.4000 -12.3827

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 269.1740 65.8482 260.9955 1071.4185 0.2512 0.5079 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.7303 4.5297 484.1281 468.0103 554.9116 0.0338 0.5995

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 267.9978 0.0000 267.9978 1071.4637 0.2501 0.4792 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.5107 484.1788 467.9592 0.0000 0.0600 0.0832 0.4645

NASA/TM—2013-218094 O–325
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8195 4.7087 1.1213 489.9543 18.4816 169.2713 1.3122

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 114921.945 0.622 164.953 260306.266 0.900251E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.656 EfDer = 0.961 SH = 0.917661E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.399 2387.497 4.709 489.954 1.000 1.000 0.980

 W Kg/sec = 11.545 Wdry = 25.397 WH2O = 0.002 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 77.065 2456.536 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 60296.770 19928.984 2.618 590.487 225.588 468.502 2.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 245.07 -0.08 245.07 0.23 0.46 440.52

 MEAN 18.08 0.00 -0.02 245.07 -0.08 245.07 0.23 0.42

 HUB 15.21 0.00 -0.02 245.07 -0.08 245.07 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.22 46.36 13.86 428.16 493.41 4.54 485.12 467.96 0.99

 MEAN 56.96 42.30 14.66 376.66 449.44 4.54 485.12 467.96 0.99

 HUB 52.29 37.84 14.45 316.90 400.67 4.54 485.12 467.96 0.99

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 355.46 243.83 258.65 1084.99 0.33 2.33 2.04 9.02

 MEAN 18.01 355.59 241.38 261.12 1082.67 0.33 2.40 2.13 7.35

 HUB 15.22 377.41 269.86 263.85 1080.38 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 425.45 316.05 181.62 0.29 4980.72 0.92 0.88

 MEAN 375.23 293.42 133.85 0.27 4348.82 0.92 0.88 0.88 1.69

 HUB 317.17 268.06 47.31 0.25 4109.30 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.24 1.11 4.87 506.64 1.03 496.48 477.03 0.67

 MEAN 5.17 1.10 4.80 504.53 1.03 494.36 475.93 0.72

 HUB 5.14 1.09 4.73 503.72 1.03 492.27 475.52 0.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.31 35.08 31.50 3.58 0.93 0.54 1.40

 MEAN 42.75 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.64 10.17 6.50 3.67 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 380.7375 242.0602 293.8842 1081.5063 0.3520 -0.1097 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.1811 4.7608 493.3081 476.1636 0.7455 39.4769 30.6000 -8.8769

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 284.7384 60.3666 278.2657 1087.1212 0.2619 0.3555 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.1759 4.9379 498.4451 476.1049 491.5697 0.0234 0.4531

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 295.0607 0.0000 295.0607 1086.5874 0.2715 0.3469 0.5911

NASA/TM—2013-218094 O–326
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.9066 497.9640 476.0714 0.0000 0.0600 0.0621 0.2737

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8371 5.1611 1.0961 504.9641 15.0101 191.4535 1.4841

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 93348.258 0.516 133.987 236645.750 0.922688E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.584 EfDer = 0.977 SH = 0.928924E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.399 2387.497 5.161 504.964 1.000 1.000 0.980

 W Kg/sec = 11.545 Wdry = 25.397 WH2O = 0.002 lbm/sec H2O = 0.040g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 71.380 2419.752 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 56705.523 19928.977 2.611 545.479 208.948 424.468 2.031

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 249.49 -0.09 249.49 0.23 0.45 423.79

 MEAN 17.74 0.00 -0.02 249.49 -0.09 249.49 0.23 0.41

 HUB 15.05 0.00 -0.02 249.49 -0.09 249.49 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.18 46.36 12.82 418.16 487.00 4.98 499.96 476.06 0.60

 MEAN 55.98 43.40 12.58 369.58 445.98 4.98 499.96 476.06 0.60

 HUB 51.50 38.84 12.66 313.56 400.78 4.98 499.96 476.06 0.60

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 347.86 227.40 263.23 1100.00 0.32 2.26 1.98 8.75

 MEAN 17.51 350.01 228.20 265.40 1098.02 0.32 2.34 2.07 6.78

 HUB 14.85 373.83 260.84 267.79 1096.09 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 412.74 321.93 185.34 0.29 4506.57 0.92 0.89

 MEAN 364.75 298.46 136.55 0.27 3996.50 0.92 0.89 0.89 1.64

 HUB 309.40 272.15 48.56 0.25 3874.79 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.68 1.10 5.30 520.06 1.03 510.33 483.65 0.44

 MEAN 5.62 1.09 5.24 518.35 1.03 508.50 482.82 0.46

 HUB 5.60 1.09 5.18 517.95 1.03 506.71 482.63 0.49

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.82 35.15 31.50 3.65 0.93 0.50 1.40

 MEAN 40.69 27.23 23.50 3.73 0.94 0.49 1.62

 HUB 44.25 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 376.4272 229.6965 298.2230 1096.8142 0.3432 -0.1181 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.6294 5.1943 507.3951 483.0334 0.4764 37.6041 31.5000 -6.1041

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 293.8461 64.1005 286.7694 1101.6123 0.2667 0.3010 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.6262 5.3582 511.8453 482.9924 451.3937 0.0181 0.4258

 

NASA/TM—2013-218094 O–327
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 298.7590 0.0000 298.7590 1101.3512 0.2713 0.3297 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.3377 511.6113 482.9624 0.0000 0.0600 0.0491 0.2489

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8581 5.6140 1.0878 518.7871 13.8235 197.4759 1.5308

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85979.102 0.505 123.410 235465.234 0.933595E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.916 EfDer = 0.987 SH = 0.939932E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.399 2387.497 5.614 518.787 1.000 1.000 0.980

 W Kg/sec = 11.545 Wdry = 25.397 WH2O = 0.002 lbm/sec H2O = 0.043g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.513 2387.297 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53528.574 19928.967 2.636 513.330 194.705 395.845 2.033

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 250.26 -0.09 250.26 0.23 0.43 401.23

 MEAN 16.97 0.00 -0.02 250.26 -0.09 250.26 0.23 0.39

 HUB 14.32 0.00 -0.02 250.26 -0.09 250.26 0.23 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.06 46.36 11.70 401.28 473.00 5.42 513.75 482.95 0.40

 MEAN 54.72 43.80 10.92 353.58 433.26 5.42 513.75 482.95 0.40

 HUB 50.02 37.84 12.18 298.35 389.49 5.42 513.75 482.95 0.40

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 335.29 207.71 263.21 1113.42 0.30 2.16 1.89 8.34

 MEAN 16.57 337.45 208.72 265.15 1111.65 0.30 2.24 1.97 6.35

 HUB 13.89 359.89 241.01 267.28 1109.90 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 393.36 322.10 185.65 0.29 3923.20 0.92 0.90

 MEAN 345.31 298.27 136.59 0.27 3460.76 0.92 0.90 0.90 1.59

 HUB 289.40 271.62 48.39 0.24 3348.86 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.09 1.09 5.73 531.93 1.03 522.89 489.15 0.30

 MEAN 6.04 1.08 5.67 530.38 1.02 521.23 488.44 0.32

 HUB 6.02 1.07 5.60 530.01 1.02 519.59 488.28 0.33

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.28 35.20 31.50 3.70 0.93 0.47 1.40

 MEAN 38.21 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 42.04 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 358.5936 209.8939 290.7472 1110.7913 0.3228 -0.0939 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.0463 5.6304 520.4346 488.6158 0.3244 35.8260 32.4000 -3.4260

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 292.2931 65.5528 284.8475 1114.4854 0.2623 0.2613 2.2705

 

NASA/TM—2013-218094 O–328
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.0447 5.7661 523.9036 488.5905 432.2457 0.0140 0.4025

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 289.9351 0.0000 289.9351 1114.5945 0.2601 0.3134 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.7607 524.0140 488.5632 0.0000 0.0600 0.0406 0.2474

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8714 6.0345 1.0749 530.7714 11.9847 213.5225 1.6552

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 74552.188 0.482 107.008 241178.313 0.944618E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.390 EfDer = 0.994 SH = 0.951641E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.399 2387.497 6.034 530.771 1.000 1.000 0.980

 W Kg/sec = 11.545 Wdry = 25.397 WH2O = 0.002 lbm/sec H2O = 0.046g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.589 2360.192 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50809.926 19928.959 2.782 509.668 183.222 384.739 2.100

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 239.26 -0.08 239.26 0.21 0.40 377.32

 MEAN 15.91 0.00 -0.02 239.26 -0.08 239.26 0.21 0.37

 HUB 13.07 0.00 -0.02 239.26 -0.08 239.26 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.92 47.36 10.56 381.69 450.55 5.85 526.17 488.55 0.28

 MEAN 54.19 44.80 9.39 331.54 408.93 5.85 526.17 488.55 0.28

 HUB 48.71 38.84 9.87 272.31 362.55 5.85 526.17 488.55 0.28

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 318.58 194.69 252.17 1125.49 0.28 2.05 1.78 7.43

 MEAN 15.50 318.02 191.26 254.08 1123.66 0.28 2.13 1.86 5.75

 HUB 12.59 334.92 215.83 256.11 1121.85 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 373.78 309.30 179.09 0.27 3494.20 0.92 0.91

 MEAN 322.89 286.15 131.63 0.25 2965.38 0.92 0.91 0.91 1.58

 HUB 262.31 260.29 46.48 0.23 2718.37 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.48 1.07 6.14 542.47 1.02 534.32 493.80 0.22

 MEAN 6.42 1.06 6.07 540.70 1.02 532.57 493.02 0.23

 HUB 6.38 1.06 6.00 539.88 1.02 530.86 492.66 0.24

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.67 35.38 31.50 3.88 0.93 0.47 1.40

 MEAN 36.97 27.39 23.50 3.89 0.94 0.44 1.64

 HUB 40.12 10.29 6.50 3.79 0.94 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 348.6021 194.7666 289.1183 1122.2469 0.3106 -0.1749 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.4204 6.0102 531.2504 493.1519 0.2411 33.9665 33.0000 -0.9665

 

NASA/TM—2013-218094 O–329
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 295.7393 67.5323 287.9255 1125.1342 0.2628 0.1400 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.4188 6.1216 533.9882 493.1329 410.5396 0.0246 0.3769

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 287.6864 0.0000 287.6864 1125.5247 0.2556 0.2997 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.1331 534.3658 493.1197 0.0000 0.0600 0.0369 0.1724

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8800 6.4144 1.0630 541.0179 10.2471 233.9399 1.8135

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 63751.156 0.456 91.505 253109.641 0.957016E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1475 Tt4 = 541.0179 T1 = 471.4733

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 432552.66 620.8639 84.7710 1.5275 0.8409 15.2042 1.1475 37.3740

NASA/TM—2013-218094 O–330
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 37357 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.264 EfDer = 0.956 SH = 0.839529E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.952 2357.013 4.337 469.501 1.000 1.000 0.980

 W Kg/sec = 11.796 Wdry = 25.950 WH2O = 0.002 lbm/sec H2O = 0.033g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 83.686 2477.426 1.381 0.248 53.351 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 63400.883 20362.631 3.395 831.557 244.965 619.754 2.530

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 182.98 -0.06 182.98 0.17 0.44 446.00

 MEAN 17.06 0.00 -0.02 182.98 -0.06 182.98 0.17 0.38

 HUB 12.51 0.00 -0.02 182.98 -0.06 182.98 0.17 0.30

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.68 50.47 16.21 424.33 462.17 4.25 466.81 455.95 1.88

 MEAN 62.46 47.20 15.26 350.91 395.81 4.25 466.81 455.95 1.88

 HUB 54.59 38.62 15.97 257.32 315.80 4.25 466.81 455.95 1.88

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 381.11 291.31 245.73 1064.30 0.36 7.29 6.52 16.04

 MEAN 18.04 386.04 295.23 248.73 1061.43 0.36 7.43 6.80 12.53

 HUB 15.00 418.49 333.44 252.89 1057.88 0.40 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 424.33 279.43 133.03 0.26 6010.99 0.92 0.87

 MEAN 370.98 260.01 75.75 0.24 5325.88 0.92 0.87 0.87 1.75

 HUB 308.53 254.11 24.91 0.24 5002.42 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 4.95 1.14 4.53 489.39 1.04 477.71 468.28 1.25

 MEAN 4.88 1.12 4.45 487.12 1.04 475.14 466.97 1.38

 HUB 4.84 1.12 4.35 486.05 1.04 471.97 466.37 1.55

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.85 28.43 24.20 4.23 0.93 0.57 1.80

 MEAN 49.89 16.94 12.70 4.24 0.95 0.52 2.22

 HUB 52.82 -5.63 -9.30 3.67 0.95 0.38 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.956 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 397.4456 294.6583 266.7199 1061.0659 0.3746 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 4.8839 4.4385 474.8163 467.2017 1.3932 47.8491 35.4000 -12.4491

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 265.4334 64.9331 257.3686 1068.8961 0.2483 0.5087 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 4.8735 4.6714 481.8537 467.1014 554.9116 0.0336 0.6002

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 264.2646 0.0000 264.2646 1068.9410 0.2472 0.4794 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 4.6520 481.9034 467.0528 0.0000 0.0600 0.0836 0.4647

NASA/TM—2013-218094 O–331
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8188 4.8514 1.1186 487.5192 18.0186 169.0146 1.3102

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 112042.969 0.622 164.320 266707.375 0.857705E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.683 EfDer = 0.961 SH = 0.873991E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.952 2357.013 4.851 487.519 1.000 1.000 0.980

 W Kg/sec = 11.796 Wdry = 25.950 WH2O = 0.002 lbm/sec H2O = 0.037g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 76.236 2431.220 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59464.215 20362.602 2.646 590.487 223.160 468.502 2.099

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 241.69 -0.08 241.69 0.23 0.46 435.98

 MEAN 18.08 0.00 -0.02 241.69 -0.08 241.69 0.23 0.41

 HUB 15.21 0.00 -0.02 241.69 -0.08 241.69 0.23 0.37

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.24 46.36 13.88 422.69 486.98 4.68 482.82 467.05 1.07

 MEAN 56.98 42.30 14.68 371.85 443.56 4.68 482.82 467.05 1.07

 HUB 52.32 37.84 14.48 312.85 395.40 4.68 482.82 467.05 1.07

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 350.94 240.74 255.35 1082.14 0.32 2.33 2.04 9.02

 MEAN 18.01 351.04 238.34 257.72 1079.88 0.33 2.40 2.13 7.35

 HUB 15.22 372.54 266.45 260.36 1077.64 0.35 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 420.02 311.99 179.27 0.29 4917.65 0.92 0.88 

 MEAN 370.44 289.61 132.10 0.27 4293.97 0.92 0.88 0.88 1.69

 HUB 313.12 264.51 46.67 0.25 4057.41 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.39 1.11 5.01 503.79 1.03 493.88 476.12 0.73

 MEAN 5.32 1.10 4.95 501.72 1.03 491.81 475.03 0.78

 HUB 5.29 1.09 4.88 500.94 1.03 489.78 474.62 0.84

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.31 35.07 31.50 3.57 0.93 0.54 1.40

 MEAN 42.76 27.14 23.50 3.64 0.95 0.51 1.63

 HUB 45.66 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 375.8156 239.0076 290.0220 1078.7449 0.3484 -0.1096 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3277 4.9040 490.7935 475.2581 0.8093 39.4920 30.6000 -8.8920

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 281.1500 59.6058 274.7589 1084.2251 0.2593 0.3555 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3226 5.0825 495.7943 475.2017 491.5697 0.0232 0.4529

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 291.3155 0.0000 291.3155 1083.7048 0.2688 0.3466 0.5911

NASA/TM—2013-218094 O–332
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.0508 495.3264 475.1697 0.0000 0.0600 0.0622 0.2735

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8368 5.3075 1.0940 502.1500 14.6312 191.3338 1.4832

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 90991.656 0.516 133.446 242558.875 0.878670E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.576 EfDer = 0.977 SH = 0.884804E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.952 2357.013 5.308 502.150 1.000 1.000 0.980

 W Kg/sec = 11.796 Wdry = 25.950 WH2O = 0.002 lbm/sec H2O = 0.039g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 70.723 2395.540 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55998.133 20362.592 2.635 545.479 207.024 424.468 2.050

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 246.38 -0.08 246.38 0.23 0.44 419.55

 MEAN 17.74 0.00 -0.02 246.38 -0.08 246.38 0.23 0.41

 HUB 15.05 0.00 -0.02 246.38 -0.08 246.38 0.23 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.18 46.36 12.82 412.82 480.82 5.12 497.27 475.16 0.66

 MEAN 55.98 43.40 12.58 364.86 440.33 5.12 497.27 475.16 0.66

 HUB 51.49 38.84 12.65 309.56 395.71 5.12 497.27 475.16 0.66

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 343.54 224.32 260.19 1096.79 0.31 2.26 1.98 8.75

 MEAN 17.51 345.67 225.16 262.28 1094.87 0.32 2.34 2.07 6.78

 HUB 14.85 369.20 257.48 264.59 1092.98 0.34 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 407.47 318.19 183.15 0.29 4445.43 0.92 0.89

 MEAN 360.09 294.95 134.93 0.27 3943.35 0.92 0.89 0.89 1.64

 HUB 305.45 268.90 47.97 0.25 3824.87 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.83 1.10 5.45 516.85 1.03 507.36 482.74 0.48

 MEAN 5.77 1.09 5.39 515.19 1.03 505.59 481.92 0.50

 HUB 5.75 1.08 5.32 514.80 1.03 503.84 481.73 0.53

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.77 35.14 31.50 3.64 0.93 0.50 1.40

 MEAN 40.65 27.22 23.50 3.72 0.94 0.49 1.62

 HUB 44.22 10.28 6.50 3.78 0.94 0.49 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 371.7591 226.6414 294.6837 1093.6849 0.3399 -0.1182 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.7790 5.3404 504.5042 482.1318 0.5205 37.5639 31.5000 -6.0639

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 290.4982 63.3702 283.5021 1098.3636 0.2645 0.2999 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.7759 5.5053 508.8310 482.0923 451.3937 0.0178 0.4249

 

NASA/TM—2013-218094 O–333
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 295.3376 0.0000 295.3376 1098.1089 0.2690 0.3287 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.4846 508.6031 482.0636 0.0000 0.0600 0.0489 0.2478

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8582 5.7636 1.0859 515.6155 13.4660 197.5809 1.5316

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 83754.734 0.504 122.833 241473.031 0.889227E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.874 EfDer = 0.987 SH = 0.894743E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.952 2357.013 5.764 515.615 1.000 1.000 0.980

 W Kg/sec = 11.796 Wdry = 25.950 WH2O = 0.002 lbm/sec H2O = 0.042g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 65.994 2364.052 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 52925.926 20362.586 2.657 513.330 193.185 395.845 2.049

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 247.45 -0.09 247.45 0.22 0.42 397.33

 MEAN 16.97 0.00 -0.02 247.45 -0.09 247.45 0.22 0.39

 HUB 14.32 0.00 -0.02 247.45 -0.09 247.45 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.02 46.36 11.66 396.16 467.16 5.57 510.69 482.05 0.43

 MEAN 54.67 43.80 10.87 349.07 427.95 5.57 510.69 482.05 0.43

 HUB 49.97 37.84 12.13 294.55 384.76 5.57 510.69 482.05 0.43

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 331.24 204.66 260.45 1109.89 0.30 2.16 1.89 8.34

 MEAN 16.57 333.40 205.75 262.34 1108.16 0.30 2.24 1.97 6.35

 HUB 13.89 355.62 237.83 264.39 1106.47 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.34 318.71 183.68 0.29 3865.57 0.92 0.90

 MEAN 340.90 295.11 135.15 0.27 3411.52 0.92 0.90 0.90 1.59

 HUB 285.70 268.69 47.87 0.24 3304.71 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.25 1.08 5.88 528.40 1.02 519.58 488.24 0.33

 MEAN 6.19 1.07 5.82 526.90 1.02 517.96 487.54 0.35

 HUB 6.17 1.07 5.75 526.54 1.02 516.38 487.38 0.36

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.16 35.19 31.50 3.69 0.93 0.47 1.40

 MEAN 38.11 27.26 23.50 3.76 0.94 0.46 1.62

 HUB 41.97 10.26 6.50 3.76 0.94 0.46 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 354.3228 206.9072 287.6352 1107.3228 0.3200 -0.0940 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1980 5.7788 517.1883 487.7130 0.3560 35.7289 32.4000 -3.3289

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 289.2795 64.8769 281.9106 1110.9178 0.2604 0.2591 2.2705

 

NASA/TM—2013-218094 O–334
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1965 5.9148 520.5536 487.6884 432.2457 0.0138 0.4007

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 286.9389 0.0000 286.9389 1111.0256 0.2583 0.3116 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.9094 520.6620 487.6624 0.0000 0.0600 0.0404 0.2453

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8717 6.1862 1.0733 527.2805 11.6654 213.8976 1.6581

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 72564.570 0.481 106.422 247449.125 0.899011E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.319 EfDer = 0.994 SH = 0.905340E-04

 

 W act RPM act Pt Tt POTS POTH AeroBl

 25.952 2357.013 6.186 527.280 1.000 1.000 0.980

 W Kg/sec = 11.796 Wdry = 25.950 WH2O = 0.002 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.177 2337.756 1.381 0.248 53.351 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50292.934 20362.576 2.800 509.668 182.014 384.739 2.114 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 236.83 -0.08 236.83 0.21 0.40 373.73

 MEAN 15.91 0.00 -0.02 236.83 -0.08 236.83 0.21 0.36

 HUB 13.07 0.00 -0.02 236.83 -0.08 236.83 0.21 0.32

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.86 47.36 10.50 376.82 445.13 6.00 522.77 487.65 0.31

 MEAN 54.12 44.80 9.32 327.31 404.07 6.00 522.77 487.65 0.31

 HUB 48.63 38.84 9.79 268.83 358.33 6.00 522.77 487.65 0.31

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 314.81 191.60 249.79 1121.66 0.28 2.05 1.78 7.43

 MEAN 15.50 314.33 188.39 251.63 1119.88 0.28 2.13 1.86 5.75

 HUB 12.59 331.16 212.98 253.59 1118.12 0.30 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 369.00 306.38 177.41 0.27 3438.78 0.92 0.91

 MEAN 318.77 283.40 130.38 0.25 2920.87 0.92 0.91 0.91 1.58

 HUB 258.96 257.73 45.98 0.23 2682.47 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.64 1.07 6.29 538.65 1.02 530.69 492.88 0.24

 MEAN 6.57 1.06 6.22 536.94 1.02 529.00 492.11 0.26

 HUB 6.54 1.06 6.16 536.15 1.02 527.34 491.76 0.27

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.49 35.38 31.50 3.88 0.93 0.46 1.40

 MEAN 36.82 27.39 23.50 3.89 0.93 0.44 1.64

 HUB 40.03 10.28 6.50 3.78 0.93 0.43 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 344.6326 191.8428 286.3005 1118.4937 0.3081 -0.1754 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.5735 6.1599 527.7002 492.2439 0.2653 33.8251 33.0000 -0.8251

 

NASA/TM—2013-218094 O–335
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 292.9548 66.8965 285.2146 1121.2964 0.2613 0.1368 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.5719 6.2712 530.3486 492.2256 410.5396 0.0243 0.3744

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 284.9840 0.0000 284.9840 1121.6807 0.2541 0.2972 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2828 530.7189 492.2128 0.0000 0.0600 0.0368 0.1691

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8802 6.5674 1.0616 537.2468 9.9667 234.6093 1.8187

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 62005.621 0.455 90.936 259804.484 0.910077E-04

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1443 Tt4 = 537.2468 T1 = 469.5012

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 421359.56 617.9562 83.6858 1.5142 0.8409 15.2639 1.1443 37.3740

NASA/TM—2013-218094 O–336
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 34281 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =15.369 EfDer = 0.955 SH = 0.102769E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.788 2282.816 4.829 471.211 1.000 1.000 0.980

 W Kg/sec = 12.631 Wdry = 27.785 WH2O = 0.003 lbm/sec H2O = 0.045g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.630 2395.083 1.381 0.248 53.352 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61129.789 21802.723 3.523 831.557 236.027 619.754 2.626

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 176.43 -0.06 176.43 0.17 0.42 431.18

 MEAN 17.06 0.00 -0.02 176.43 -0.06 176.43 0.17 0.36

 HUB 12.51 0.00 -0.02 176.43 -0.06 176.43 0.17 0.29

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 66.77 50.47 16.30 410.98 447.30 4.74 468.71 457.95 2.35

 MEAN 62.57 47.20 15.37 339.86 382.98 4.74 468.71 457.95 2.35

 HUB 54.71 38.62 16.09 249.22 305.40 4.74 468.71 457.95 2.35

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 369.06 282.39 237.62 1065.63 0.35 7.29 6.52 16.04

 MEAN 18.04 373.66 286.13 240.32 1062.95 0.35 7.43 6.80 12.53

 HUB 15.00 404.72 322.85 244.06 1059.64 0.38 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 410.98 270.19 128.59 0.25 5826.89 0.92 0.87

 MEAN 359.30 251.21 73.17 0.24 5161.63 0.92 0.87 0.87 1.75

 HUB 298.82 245.24 24.03 0.23 4843.56 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.46 1.13 5.03 489.88 1.04 478.93 469.69 1.61

 MEAN 5.39 1.12 4.95 487.75 1.04 476.52 468.44 1.76

 HUB 5.35 1.11 4.85 486.73 1.03 473.56 467.86 1.96

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 49.92 28.42 24.20 4.22 0.93 0.57 1.80

 MEAN 49.97 16.93 12.70 4.23 0.95 0.52 2.22

 HUB 52.91 -5.62 -9.30 3.68 0.95 0.39 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.955 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 384.6222 285.5713 257.6496 1062.6173 0.3620 -0.0370 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.3957 4.9343 476.2226 468.6574 1.7807 47.9424 35.4000 -12.5424

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 257.0126 62.8731 249.2036 1069.9335 0.2402 0.5096 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.3853 5.1760 482.8064 468.5493 554.9116 0.0327 0.6003

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 255.8428 0.0000 255.8428 1069.9769 0.2391 0.4788 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.1552 482.8546 468.5031 0.0000 0.0600 0.0842 0.4641

NASA/TM—2013-218094 O–337
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8175 5.3617 1.1104 488.1174 16.9074 168.5781 1.3068

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 105147.555 0.623 165.114 284472.063 0.104731E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =14.685 EfDer = 0.961 SH = 0.106448E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.788 2282.816 5.362 488.117 1.000 1.000 0.980

 W Kg/sec = 12.631 Wdry = 27.785 WH2O = 0.003 lbm/sec H2O = 0.049g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.904 2353.244 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 57588.621 21802.691 2.729 590.487 216.340 468.502 2.166 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 234.07 -0.08 234.07 0.22 0.44 422.00

 MEAN 18.08 0.00 -0.02 234.07 -0.08 234.07 0.22 0.40

 HUB 15.21 0.00 -0.02 234.07 -0.08 234.07 0.22 0.36

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 60.25 46.36 13.89 409.38 471.64 5.19 483.71 468.50 1.39

 MEAN 56.99 42.30 14.69 360.14 429.59 5.19 483.71 468.50 1.39

 HUB 52.32 37.84 14.48 303.00 382.94 5.19 483.71 468.50 1.39

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 340.12 232.70 248.05 1082.30 0.31 2.33 2.04 9.02

 MEAN 18.01 340.24 230.57 250.20 1080.19 0.31 2.40 2.13 7.35

 HUB 15.22 361.06 257.99 252.59 1078.11 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 406.79 303.05 174.09 0.28 4753.48 0.92 0.88

 MEAN 358.78 281.14 128.21 0.26 4154.05 0.92 0.88 0.88 1.68

 HUB 303.26 256.62 45.27 0.24 3928.61 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 5.91 1.10 5.53 503.34 1.03 494.04 477.17 0.97

 MEAN 5.84 1.09 5.46 501.42 1.03 492.12 476.13 1.04

 HUB 5.82 1.08 5.39 500.70 1.03 490.22 475.74 1.11

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 43.17 35.06 31.50 3.56 0.93 0.53 1.40

 MEAN 42.66 27.13 23.50 3.63 0.95 0.51 1.63

 HUB 45.61 10.16 6.50 3.66 0.95 0.50 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.961 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 364.2478 231.2194 281.4499 1079.1259 0.3375 -0.1099 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 5.8532 5.4148 491.1568 476.3511 1.0721 39.4041 30.6000 -8.8041

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 273.3020 57.9420 267.0893 1084.2334 0.2521 0.3531 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 5.8482 5.5986 495.8185 476.2899 491.5697 0.0223 0.4505

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 283.1005 0.0000 283.1005 1083.7460 0.2612 0.3442 0.5911

NASA/TM—2013-218094 O–338
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.5657 495.3802 476.2612 0.0000 0.0600 0.0618 0.2706

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8369 5.8325 1.0878 501.8235 13.7065 191.4977 1.4845

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 85252.148 0.515 133.872 259059.875 0.107034E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =12.470 EfDer = 0.977 SH = 0.107699E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.788 2282.816 5.832 501.823 1.000 1.000 0.980

 W Kg/sec = 12.631 Wdry = 27.785 WH2O = 0.003 lbm/sec H2O = 0.053g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 68.886 2320.885 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 54451.648 21802.680 2.705 545.479 201.653 424.468 2.105

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 239.58 -0.08 239.58 0.22 0.43 406.48

 MEAN 17.74 0.00 -0.02 239.58 -0.08 239.58 0.22 0.39

 HUB 15.05 0.00 -0.02 239.58 -0.08 239.58 0.22 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 59.07 46.36 12.71 399.82 466.18 5.64 497.21 476.25 0.88

 MEAN 55.87 43.40 12.47 353.37 427.00 5.64 497.21 476.25 0.88

 HUB 51.38 38.84 12.54 299.82 383.84 5.64 497.21 476.25 0.88

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.27 216.10 253.71 1095.96 0.30 2.26 1.98 8.75

 MEAN 17.51 335.49 217.30 255.60 1094.18 0.31 2.34 2.07 6.78

 HUB 14.85 358.45 249.15 257.70 1092.43 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 394.64 310.24 178.54 0.28 4282.56 0.92 0.89

 MEAN 348.75 287.43 131.45 0.26 3805.65 0.92 0.89 0.89 1.63

 HUB 295.83 261.89 46.68 0.24 3701.14 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.37 1.09 5.98 515.54 1.03 506.61 483.51 0.65

 MEAN 6.30 1.08 5.91 514.01 1.02 504.96 482.73 0.69

 HUB 6.29 1.08 5.84 513.68 1.02 503.35 482.57 0.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 40.42 35.13 31.50 3.63 0.93 0.50 1.40

 MEAN 40.37 27.22 23.50 3.72 0.94 0.48 1.62

 HUB 44.03 10.27 6.50 3.77 0.94 0.48 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.977 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 360.9159 218.7269 287.0868 1093.0553 0.3302 -0.1192 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.3166 5.8630 503.9392 482.9372 0.7104 37.3032 31.5000 -5.8032

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 283.4351 61.8294 276.6090 1097.3983 0.2583 0.2939 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.3137 6.0312 507.9527 482.8940 451.3937 0.0170 0.4197

 

NASA/TM—2013-218094 O–339
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 288.1008 0.0000 288.1008 1097.1586 0.2626 0.3239 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.0099 507.7384 482.8681 0.0000 0.0600 0.0479 0.2419

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8592 6.3010 1.0803 514.4106 12.5874 198.4762 1.5386

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 78299.961 0.503 122.955 258322.016 0.108213E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =10.666 EfDer = 0.988 SH = 0.108897E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.788 2282.816 6.301 514.411 1.000 1.000 0.980

 W Kg/sec = 12.631 Wdry = 27.785 WH2O = 0.003 lbm/sec H2O = 0.056g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 64.559 2292.314 1.381 0.248 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 51656.309 21802.672 2.716 513.330 188.989 395.845 2.095

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 241.51 -0.08 241.51 0.22 0.41 385.27

 MEAN 16.97 0.00 -0.02 241.51 -0.08 241.51 0.22 0.38

 HUB 14.32 0.00 -0.02 241.51 -0.08 241.51 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.82 46.36 11.46 383.68 453.44 6.10 509.72 482.85 0.60

 MEAN 54.47 43.80 10.67 338.08 415.55 6.10 509.72 482.85 0.60

 HUB 49.76 37.84 11.92 285.27 373.84 6.10 509.72 482.85 0.60

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 321.77 196.45 254.84 1108.16 0.29 2.16 1.89 8.34

 MEAN 16.57 324.09 198.04 256.54 1106.56 0.29 2.24 1.97 6.35

 HUB 13.89 345.92 229.97 258.40 1105.00 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 376.11 311.80 179.66 0.28 3710.62 0.92 0.90

 MEAN 330.17 288.57 132.13 0.26 3283.75 0.92 0.90 0.90 1.58

 HUB 276.71 262.59 46.74 0.24 3195.50 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.79 1.08 6.41 526.29 1.02 517.97 488.78 0.47

 MEAN 6.73 1.07 6.35 524.93 1.02 516.48 488.12 0.49

 HUB 6.72 1.07 6.29 524.64 1.02 515.03 487.99 0.51

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 37.63 35.18 31.50 3.68 0.93 0.47 1.40

 MEAN 37.67 27.25 23.50 3.75 0.94 0.45 1.62

 HUB 41.67 10.25 6.50 3.75 0.94 0.45 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.988 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 344.6010 199.1569 281.2230 1105.7598 0.3116 -0.0952 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.7447 6.3110 515.7437 488.2916 0.4985 35.3054 32.4000 -2.9054

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 283.1825 63.5096 275.9690 1109.0757 0.2553 0.2499 2.2705

 

NASA/TM—2013-218094 O–340
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.7434 6.4483 518.8430 488.2644 432.2457 0.0132 0.3933

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 280.8683 0.0000 280.8683 1109.1807 0.2532 0.3043 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.4430 518.9479 488.2404 0.0000 0.0600 0.0395 0.2366

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8730 6.7329 1.0685 525.2886 10.8784 215.6528 1.6717

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 67676.977 0.478 106.274 265112.594 0.109460E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 9.019 EfDer = 0.995 SH = 0.110180E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 27.788 2282.816 6.733 525.288 1.000 1.000 0.980

 W Kg/sec = 12.631 Wdry = 27.785 WH2O = 0.003 lbm/sec H2O = 0.060g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 61.054 2268.455 1.381 0.249 53.352 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 49249.992 21802.658 2.852 509.668 178.730 384.739 2.153

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 231.92 -0.08 231.92 0.21 0.39 362.65

 MEAN 15.91 0.00 -0.02 231.92 -0.08 231.92 0.21 0.35

 HUB 13.07 0.00 -0.02 231.92 -0.08 231.92 0.21 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.57 47.36 10.21 364.96 432.48 6.53 520.97 488.23 0.43

 MEAN 53.82 44.80 9.02 317.01 392.85 6.53 520.97 488.23 0.43

 HUB 48.32 38.84 9.48 260.37 348.74 6.53 520.97 488.23 0.43

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 306.10 183.30 245.15 1119.12 0.27 2.05 1.78 7.43

 MEAN 15.50 305.99 180.85 246.82 1117.47 0.27 2.13 1.86 5.75

 HUB 12.59 322.68 205.72 248.61 1115.85 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 357.39 300.68 174.09 0.27 3289.81 0.92 0.91

 MEAN 308.73 277.98 127.88 0.25 2804.04 0.92 0.91 0.91 1.56

 HUB 250.81 252.66 45.09 0.23 2591.01 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.19 1.07 6.83 535.82 1.02 528.29 493.23 0.35

 MEAN 7.12 1.06 6.76 534.27 1.02 526.74 492.51 0.37

 HUB 7.09 1.05 6.70 533.59 1.02 525.22 492.20 0.38

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.79 35.38 31.50 3.88 0.93 0.45 1.40

 MEAN 36.23 27.39 23.50 3.89 0.93 0.43 1.64

 HUB 39.61 10.28 6.50 3.78 0.93 0.42 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 335.7658 184.1680 280.7504 1116.1439 0.3008 -0.1777 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.1261 6.6980 525.4980 492.6394 0.3788 33.2643 33.0000 -0.2643

 

NASA/TM—2013-218094 O–341
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 287.5805 65.6693 279.9823 1118.7041 0.2571 0.1235 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.1248 6.8089 527.9120 492.6195 410.5396 0.0236 0.3652

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 279.7716 0.0000 279.7716 1119.0751 0.2500 0.2872 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.8210 528.2681 492.6065 0.0000 0.0600 0.0366 0.1560

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8808 7.1200 1.0575 534.5587 9.2706 237.3854 1.8402

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57680.750 0.452 90.577 278729.875 0.110727E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1344 Tt4 = 534.5587 T1 = 471.2105

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 394057.38 618.7915 80.6305 1.4745 0.8415 15.3693 1.1344 37.3740

NASA/TM—2013-218094 O–342
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 30029 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc =13.902 EfDer = 0.967 SH = 0.183652E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.679 2155.433 5.592 480.738 1.000 1.000 0.980

 W Kg/sec = 14.400 Wdry = 31.673 WH2O = 0.006 lbm/sec H2O = 0.091g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.167 2238.917 1.381 0.249 53.354 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61382.746 24855.117 3.543 831.557 234.686 619.754 2.641 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 177.16 -0.06 177.16 0.17 0.40 403.06

 MEAN 17.06 0.00 -0.02 177.16 -0.06 177.16 0.17 0.34

 HUB 12.51 0.00 -0.02 177.16 -0.06 177.16 0.17 0.28

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 65.46 50.47 14.99 388.04 426.63 5.49 478.21 465.12 3.21

 MEAN 61.10 47.20 13.90 320.90 366.60 5.49 478.21 465.12 3.21

 HUB 53.03 38.62 14.41 235.31 294.59 5.49 478.21 465.12 3.21

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 352.82 258.65 239.96 1074.40 0.33 7.29 6.52 16.04

 MEAN 18.04 359.69 265.85 242.28 1072.15 0.34 7.43 6.80 12.53

 HUB 15.00 392.85 306.61 245.60 1069.28 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 388.04 272.62 129.39 0.25 5337.23 0.92 0.88

 MEAN 339.25 253.15 73.40 0.24 4795.96 0.92 0.88 0.88 1.66

 HUB 282.15 246.82 24.47 0.23 4599.95 0.92 0.88

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.22 1.11 5.78 496.88 1.03 486.87 474.97 2.36

 MEAN 6.15 1.10 5.70 495.24 1.03 484.84 474.04 2.54

 HUB 6.13 1.10 5.59 494.65 1.03 482.24 473.75 2.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 47.15 28.33 24.20 4.13 0.93 0.53 1.80

 MEAN 47.66 16.85 12.70 4.15 0.95 0.48 2.22

 HUB 51.30 -5.69 -9.30 3.61 0.95 0.35 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.967 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 371.3263 265.3362 259.7691 1071.7784 0.3465 -0.0423 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.1616 5.6768 484.5049 474.2500 2.5673 45.6074 35.4000 -10.2074

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 260.4252 63.7079 252.5125 1077.9855 0.2416 0.4691 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.1540 5.9122 490.1364 474.1165 554.9116 0.0259 0.5581

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 258.9711 0.0000 258.9711 1078.0426 0.2402 0.4496 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 5.8947 490.1972 474.0780 0.0000 0.0600 0.0697 0.4325

NASA/TM—2013-218094 O–343
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8352 6.1330 1.0967 495.5875 14.8503 175.7502 1.3624

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 92388.945 0.614 165.396 319397.375 0.186454E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc =12.841 EfDer = 0.975 SH = 0.189201E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.679 2155.433 6.133 495.587 1.000 1.000 0.980

 W Kg/sec = 14.400 Wdry = 31.673 WH2O = 0.006 lbm/sec H2O = 0.099g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 74.219 2205.121 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 58290.199 24855.064 2.718 590.487 217.275 468.502 2.156

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 236.92 -0.08 236.92 0.22 0.42 395.44

 MEAN 18.08 0.00 -0.02 236.92 -0.08 236.92 0.22 0.38

 HUB 15.21 0.00 -0.02 236.92 -0.08 236.92 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 58.50 46.36 12.14 386.54 453.44 5.93 491.08 474.07 2.09

 MEAN 55.14 42.30 12.84 340.05 414.51 5.93 491.08 474.07 2.09

 HUB 50.38 37.84 12.54 286.10 371.52 5.93 491.08 474.07 2.09

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 326.65 207.19 252.54 1088.56 0.30 2.33 2.04 9.02

 MEAN 18.01 328.99 208.68 254.33 1086.87 0.30 2.40 2.13 7.35

 HUB 15.22 351.57 240.61 256.33 1085.20 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 384.09 308.34 176.91 0.28 4232.42 0.92 0.89

 MEAN 338.76 285.67 130.08 0.26 3759.76 0.92 0.89 0.89 1.59

 HUB 286.34 260.38 45.73 0.24 3664.07 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 6.66 1.09 6.26 508.38 1.03 499.81 481.24 1.56

 MEAN 6.60 1.08 6.20 506.96 1.02 498.26 480.48 1.64

 HUB 6.59 1.07 6.13 506.67 1.02 496.73 480.35 1.73

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 39.37 35.01 31.50 3.51 0.93 0.48 1.40

 MEAN 39.37 27.09 23.50 3.59 0.94 0.47 1.63

 HUB 43.19 10.12 6.50 3.62 0.94 0.46 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.975 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 354.4995 209.2642 286.1441 1085.7434 0.3265 -0.1232 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 6.6120 6.1473 497.2352 480.7017 1.6963 36.1789 30.6000 -5.5789

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 279.0130 59.1527 272.6705 1089.9305 0.2560 0.2891 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 6.6093 6.3187 501.0785 480.6268 491.5697 0.0165 0.3970

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 288.8040 0.0000 288.8040 1089.4373 0.2651 0.2986 0.5911

NASA/TM—2013-218094 O–344
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.2860 500.6318 480.6100 0.0000 0.0600 0.0471 0.2112

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8565 6.5965 1.0756 507.3349 11.7477 204.1578 1.5826

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73095.820 0.495 130.857 292062.000 0.190003E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =10.392 EfDer = 0.990 SH = 0.190897E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.679 2155.433 6.596 507.335 1.000 1.000 0.980

 W Kg/sec = 14.400 Wdry = 31.673 WH2O = 0.006 lbm/sec H2O = 0.105g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 69.818 2179.442 1.381 0.249 53.354 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 55531.840 24855.047 2.669 545.479 204.393 424.468 2.077

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 244.33 -0.08 244.33 0.22 0.41 381.70

 MEAN 17.74 0.00 -0.02 244.33 -0.08 244.33 0.22 0.38

 HUB 15.05 0.00 -0.02 244.33 -0.08 244.33 0.22 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.09 46.36 10.73 377.51 449.75 6.37 502.54 480.58 1.44

 MEAN 53.79 43.40 10.39 333.66 413.62 6.37 502.54 480.58 1.44

 HUB 49.21 38.84 10.37 283.09 374.01 6.37 502.54 480.58 1.44

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 322.00 189.59 260.28 1099.97 0.29 2.26 1.98 8.75

 MEAN 17.51 326.28 194.72 261.81 1098.60 0.30 2.34 2.07 6.78

 HUB 14.85 350.83 231.61 263.51 1097.26 0.32 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 372.62 318.19 183.03 0.29 3757.39 0.92 0.91

 MEAN 329.29 294.37 134.58 0.27 3410.33 0.92 0.91 0.91 1.53

 HUB 279.32 267.80 47.72 0.24 3440.61 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.09 1.08 6.69 518.69 1.02 510.36 486.58 1.13

 MEAN 7.05 1.07 6.63 517.65 1.02 509.09 486.05 1.17

 HUB 7.05 1.07 6.58 517.74 1.02 507.85 486.12 1.22

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 36.07 35.12 31.50 3.62 0.93 0.44 1.40

 MEAN 36.64 27.20 23.50 3.70 0.94 0.43 1.62

 HUB 41.31 10.26 6.50 3.76 0.94 0.44 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.990 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 353.4573 195.9953 294.1393 1097.3971 0.3221 -0.1336 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0599 6.5764 507.9857 486.2598 1.2112 33.6769 31.5000 -2.1769

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 291.5712 63.6043 284.5492 1100.8563 0.2649 0.2178 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0585 6.7269 511.1935 486.2064 451.3937 0.0132 0.3613

 

NASA/TM—2013-218094 O–345
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 296.2350 0.0000 296.2350 1100.6123 0.2692 0.2683 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.7061 510.9733 486.1886 0.0000 0.0600 0.0382 0.1696

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8743 7.0477 1.0684 518.0251 10.6905 213.8569 1.6578

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 66524.320 0.479 119.092 292316.750 0.191640E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 8.342 EfDer = 0.998 SH = 0.192507E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.679 2155.433 7.048 518.025 1.000 1.000 0.980

 W Kg/sec = 14.400 Wdry = 31.673 WH2O = 0.006 lbm/sec H2O = 0.111g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 66.033 2156.837 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 53085.867 24855.033 2.655 513.330 193.315 395.845 2.048

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 248.20 -0.09 248.20 0.23 0.40 362.50

 MEAN 16.97 0.00 -0.02 248.20 -0.09 248.20 0.23 0.37

 HUB 14.32 0.00 -0.02 248.20 -0.09 248.20 0.23 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.59 46.36 9.23 362.27 439.21 6.81 513.08 486.16 1.04

 MEAN 52.14 43.80 8.34 319.21 404.42 6.81 513.08 486.16 1.04

 HUB 47.35 37.84 9.51 269.35 366.33 6.81 513.08 486.16 1.04

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 313.13 169.30 263.42 1110.09 0.28 2.16 1.89 8.34

 MEAN 16.57 317.52 175.29 264.75 1108.91 0.29 2.24 1.97 6.35

 HUB 13.89 340.91 212.94 266.23 1107.75 0.31 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 355.13 322.37 185.83 0.29 3198.07 0.92 0.91

 MEAN 311.75 297.85 136.46 0.27 2906.61 0.92 0.91 0.91 1.48

 HUB 261.27 270.58 48.33 0.24 2958.91 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.49 1.06 7.10 527.69 1.02 519.81 491.02 0.85

 MEAN 7.45 1.06 7.04 526.81 1.02 518.71 490.59 0.88

 HUB 7.46 1.06 6.99 526.97 1.02 517.63 490.69 0.91

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 32.73 35.20 31.50 3.70 0.93 0.40 1.40

 MEAN 33.51 27.27 23.50 3.77 0.93 0.40 1.62

 HUB 38.65 10.29 6.50 3.79 0.93 0.41 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.998 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 339.6500 176.2715 290.3282 1108.0208 0.3065 -0.1079 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4633 6.9985 517.8882 490.7696 0.9036 31.2638 32.4000 1.1362

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 293.4555 65.8135 285.9803 1110.5311 0.2642 0.1652 2.2705

 

NASA/TM—2013-218094 O–346
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4624 7.1134 520.2381 490.7352 432.2457 0.0122 0.3304

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 290.9993 0.0000 290.9993 1110.6487 0.2620 0.2379 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.1091 520.3535 490.7127 0.0000 0.0600 0.0370 0.1550

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8793 7.4519 1.0573 527.1576 9.1328 235.2894 1.8239

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 56837.234 0.451 101.751 301030.781 0.193195E-03 

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc = 6.473 EfDer = 1.000 SH = 0.194071E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 31.679 2155.433 7.452 527.158 1.000 1.000 0.980

 W Kg/sec = 14.400 Wdry = 31.673 WH2O = 0.006 lbm/sec H2O = 0.116g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 62.999 2138.072 1.381 0.249 53.355 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 50988.102 24855.018 2.763 509.668 184.438 384.739 2.086

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 240.10 -0.08 240.10 0.22 0.38 341.81

 MEAN 15.91 0.00 -0.02 240.10 -0.08 240.10 0.22 0.34

 HUB 13.07 0.00 -0.02 240.10 -0.08 240.10 0.22 0.31

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 55.14 47.36 7.78 344.59 420.06 7.22 522.53 490.69 0.80

 MEAN 51.27 44.80 6.47 299.32 383.78 7.22 522.53 490.69 0.80

 HUB 45.69 38.84 6.85 245.84 343.70 7.22 522.53 490.69 0.80

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 299.12 155.96 255.25 1119.23 0.27 2.05 1.78 7.43

 MEAN 15.50 301.49 158.33 256.57 1118.01 0.27 2.13 1.86 5.75

 HUB 12.59 320.26 189.76 257.99 1116.80 0.29 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 337.45 313.19 181.49 0.28 2799.43 0.92 0.91

 MEAN 291.51 289.07 133.18 0.26 2454.99 0.92 0.91 0.91 1.46

 HUB 236.81 262.25 47.06 0.23 2390.13 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.86 1.05 7.48 535.62 1.02 528.43 494.77 0.67

 MEAN 7.81 1.05 7.43 534.58 1.01 527.27 494.28 0.69

 HUB 7.80 1.05 7.37 534.38 1.01 526.14 494.20 0.72

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.43 35.41 31.50 3.91 0.93 0.39 1.40

 MEAN 31.68 27.43 23.50 3.93 0.93 0.37 1.64

 HUB 36.34 10.34 6.50 3.84 0.93 0.37 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 333.5404 161.2290 291.9836 1116.5609 0.2987 -0.1965 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.8115 7.3485 525.9213 494.4188 0.7205 28.9068 33.0000 4.0932

 

NASA/TM—2013-218094 O–347
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 300.2073 68.5526 292.2755 1118.3617 0.2684 0.0176 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.8087 7.4322 527.6185 494.3918 410.5396 0.0271 0.2993

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 292.0342 0.0000 292.0342 1118.7695 0.2610 0.2113 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4463 528.0074 494.3752 0.0000 0.0600 0.0423 0.0536

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8740 7.8027 1.0471 534.8594 7.7021 262.0067 2.0311

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 47937.957 0.421 85.819 317406.688 0.194713E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.1126 Tt4 = 534.8594 T1 = 480.7375

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 336784.28 602.9142 80.1669 1.3953 0.8549 13.9025 1.1126 37.3740

NASA/TM—2013-218094 O–348
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 25666 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 9.157 EfDer = 0.995 SH = 0.315676E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.693 1971.414 6.513 491.412 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.681 WH2O = 0.013 lbm/sec H2O = 0.178g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 87.203 2025.409 1.381 0.249 53.359 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67690.359 31141.309 3.257 831.557 255.309 619.754 2.427

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 195.36 -0.07 195.36 0.18 0.38 364.63

 MEAN 17.06 0.00 -0.02 195.36 -0.07 195.36 0.18 0.33

 HUB 12.51 0.00 -0.02 195.36 -0.07 195.36 0.18 0.27

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 61.17 50.47 10.70 354.92 405.19 6.37 488.35 472.94 4.18

 MEAN 56.36 47.20 9.16 293.50 352.63 6.37 488.35 472.94 4.18

 HUB 47.78 38.62 9.16 215.22 290.72 6.37 488.35 472.94 4.18

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 340.73 211.21 267.37 1082.33 0.31 7.29 6.52 16.04

 MEAN 18.04 353.46 229.10 269.16 1080.87 0.33 7.43 6.80 12.53

 HUB 15.00 394.41 285.42 272.19 1078.62 0.37 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 354.92 303.54 143.71 0.28 4358.58 0.92 0.91

 MEAN 310.29 281.14 81.19 0.26 4133.17 0.92 0.91 0.91 1.42

 HUB 258.06 273.57 27.37 0.25 4282.20 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.06 1.08 6.59 503.46 1.02 494.13 480.12 3.44

 MEAN 7.03 1.08 6.53 502.84 1.02 492.80 479.80 3.60

 HUB 7.05 1.08 6.43 503.25 1.02 490.75 480.12 3.85

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 38.31 28.26 24.20 4.06 0.93 0.40 1.80

 MEAN 40.40 16.79 12.70 4.09 0.93 0.35 2.22

 HUB 46.36 -5.74 -9.30 3.56 0.93 0.23 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.995 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 368.3945 228.6532 288.8463 1080.2924 0.3410 -0.0596 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.0373 6.5000 492.2796 480.0137 3.6625 38.3654 35.4000 -2.9654

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 291.8607 71.3980 282.9929 1084.7347 0.2691 0.3352 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.0349 6.6942 496.3392 479.8731 554.9116 0.0145 0.4354

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 289.7263 0.0000 289.7263 1084.8362 0.2671 0.3472 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.6865 496.4390 479.8489 0.0000 0.0600 0.0396 0.3205

NASA/TM—2013-218094 O–349
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8757 7.0217 1.0782 503.1821 11.7699 200.8754 1.5572

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 73263.953 0.582 164.338 394696.438 0.318897E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 7.303 EfDer = 1.000 SH = 0.321853E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.693 1971.414 7.022 503.182 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.680 WH2O = 0.013 lbm/sec H2O = 0.189g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.845 2001.582 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 65135.910 31141.232 2.464 590.487 239.624 468.502 1.955

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 264.74 -0.09 264.74 0.24 0.41 358.94

 MEAN 18.08 0.00 -0.02 264.74 -0.09 264.74 0.24 0.38 

 HUB 15.21 0.00 -0.02 264.74 -0.09 264.74 0.24 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 53.18 46.36 6.82 353.54 441.75 6.74 497.55 479.82 3.12 

 MEAN 49.60 42.30 7.30 311.02 408.50 6.74 497.55 479.82 3.12

 HUB 44.68 37.84 6.84 261.67 372.30 6.74 497.55 479.82 3.12

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 322.95 151.21 285.36 1092.35 0.30 2.33 2.04 9.02

 MEAN 18.01 329.61 163.10 286.43 1091.52 0.30 2.40 2.13 7.35

 HUB 15.22 356.33 210.26 287.68 1090.71 0.33 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 351.30 348.53 200.09 0.32 3089.53 0.92 0.91

 MEAN 309.84 321.84 146.74 0.29 2939.00 0.92 0.91 0.91 1.38

 HUB 261.89 292.27 51.63 0.27 3202.23 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.42 1.06 6.99 511.72 1.02 503.34 484.57 2.59

 MEAN 7.40 1.05 6.96 511.31 1.02 502.58 484.36 2.65

 HUB 7.44 1.06 6.92 512.03 1.02 501.83 484.80 2.71

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 27.92 35.04 31.50 3.54 0.93 0.33 1.40

 MEAN 29.66 27.13 23.50 3.63 0.93 0.33 1.63

 HUB 36.16 10.17 6.50 3.67 0.93 0.36 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 1.000 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 361.9558 163.5539 322.8964 1089.9751 0.3321 -0.1640 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.4186 6.8802 501.1627 484.6134 2.7686 26.8632 30.6000 3.7368

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 317.1631 67.2408 309.9534 1092.6304 0.2903 0.0959 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.4164 7.0005 503.6061 484.5348 491.5697 0.0147 0.2547

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 328.4410 0.0000 328.4410 1091.9910 0.3008 0.1471 0.5911

NASA/TM—2013-218094 O–350
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 6.9594 503.0214 484.5302 0.0000 0.0600 0.0414 0.0079

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8713 7.4040 1.0544 511.6864 8.5044 251.4100 1.9489

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 52943.348 0.429 118.757 363837.750 0.322693E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc = 4.378 EfDer = 0.994 SH = 0.323573E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.693 1971.414 7.404 511.686 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.680 WH2O = 0.013 lbm/sec H2O = 0.196g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 78.273 1984.879 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 62960.801 31141.213 2.380 545.479 229.169 424.468 1.852

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 277.02 -0.10 277.02 0.25 0.40 347.63

 MEAN 17.74 0.00 -0.02 277.02 -0.10 277.02 0.25 0.38

 HUB 15.05 0.00 -0.02 277.02 -0.10 277.02 0.25 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 51.27 46.36 4.91 345.28 442.74 7.09 505.52 484.46 2.42

 MEAN 47.78 43.40 4.38 305.17 412.22 7.09 505.52 484.46 2.42

 HUB 43.08 38.84 4.24 258.92 379.24 7.09 505.52 484.46 2.42

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 325.91 129.79 298.95 1099.82 0.30 2.26 1.98 8.75

 MEAN 17.51 333.47 146.42 299.60 1099.37 0.30 2.34 2.07 6.78

 HUB 14.85 361.13 200.38 300.44 1098.93 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 340.81 365.93 211.02 0.33 2573.05 0.92 0.91

 MEAN 301.18 337.21 154.76 0.31 2565.01 0.92 0.91 0.91 1.32

 HUB 255.48 305.45 55.09 0.28 2977.12 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 7.75 1.05 7.30 518.80 1.01 510.27 488.25 2.09

 MEAN 7.75 1.05 7.28 518.78 1.01 509.84 488.25 2.12

 HUB 7.80 1.05 7.25 519.91 1.02 509.44 488.88 2.14

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 23.47 35.22 31.50 3.72 0.93 0.28 1.40

 MEAN 26.05 27.32 23.50 3.82 0.92 0.29 1.62

 HUB 33.70 10.39 6.50 3.89 0.92 0.33 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.994 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 368.1973 147.3811 337.4138 1097.6655 0.3354 -0.1767 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 7.7622 7.1880 508.2733 488.4970 2.2181 23.5955 31.5000 7.9045

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 337.1264 73.5419 329.0073 1099.5669 0.3066 0.0000 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 7.7570 7.2738 510.0334 488.4377 451.3937 0.0205 0.2125

 

NASA/TM—2013-218094 O–351
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 342.9689 0.0000 342.9689 1099.2192 0.3120 0.0913 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.2404 509.7144 488.4139 0.0000 0.0600 0.0571 -0.0676

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8404 7.7390 1.0452 519.1622 7.4761 272.2463 2.1104

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 46544.914 0.401 104.405 366478.500 0.324376E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc = 1.779 EfDer = 0.974 SH = 0.325202E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.693 1971.414 7.739 519.162 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.680 WH2O = 0.013 lbm/sec H2O = 0.203g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 75.430 1970.536 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 61217.633 31141.193 2.324 513.330 220.846 395.845 1.792

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 286.21 -0.10 286.21 0.26 0.40 331.19

 MEAN 16.97 0.00 -0.02 286.21 -0.10 286.21 0.26 0.37

 HUB 14.32 0.00 -0.02 286.21 -0.10 286.21 0.26 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.19 46.36 2.83 331.35 437.92 7.39 512.58 488.34 1.95

 MEAN 45.58 43.80 1.78 291.96 408.92 7.39 512.58 488.34 1.95

 HUB 40.73 37.84 2.89 246.36 377.70 7.39 512.58 488.34 1.95

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 325.94 106.23 308.14 1106.16 0.29 2.16 1.89 8.34

 MEAN 16.57 332.82 124.97 308.47 1105.96 0.30 2.24 1.97 6.35

 HUB 13.89 358.57 181.85 309.03 1105.78 0.32 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 324.81 377.79 218.57 0.34 2007.59 0.92 0.89

 MEAN 285.13 347.57 160.17 0.31 2072.88 0.92 0.89 0.89 1.26

 HUB 238.96 314.26 57.11 0.28 2527.36 0.92 0.89

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.01 1.03 7.55 524.71 1.01 516.18 491.19 1.75

 MEAN 8.02 1.04 7.54 524.89 1.01 515.99 491.29 1.76

 HUB 8.08 1.04 7.52 526.15 1.01 515.82 491.95 1.77

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.02 35.35 31.50 3.85 0.93 0.22 1.40

 MEAN 22.05 27.44 23.50 3.94 0.91 0.24 1.62

 HUB 30.48 10.47 6.50 3.97 0.91 0.29 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.974 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 361.5842 125.6707 339.0428 1104.6222 0.3273 -0.1443 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.0312 7.4641 514.7484 491.4971 1.8224 20.3379 32.4000 12.0621

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 345.5403 77.4946 336.7383 1105.6017 0.3125 -0.0622 2.2705

 

NASA/TM—2013-218094 O–352
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.0219 7.5035 515.6594 491.4562 432.2457 0.0285 0.1760

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 343.2746 0.0000 343.2746 1105.7341 0.3104 0.0375 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.4853 515.7848 491.4044 0.0000 0.0600 0.0811 -0.0983

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7706 7.9955 1.0332 525.2490 6.0870 313.1828 2.4278

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37899.063 0.359 85.011 379731.969 0.325959E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-0.629 EfDer = 0.940 SH = 0.326795E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 39.693 1971.414 7.996 525.249 1.000 1.000 0.980

 W Kg/sec = 18.042 Wdry = 39.680 WH2O = 0.013 lbm/sec H2O = 0.209g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 73.436 1959.085 1.381 0.249 53.359 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 59865.035 31141.176 2.370 509.668 215.011 384.739 1.789

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 281.90 -0.10 281.90 0.25 0.38 313.19

 MEAN 15.91 0.00 -0.02 281.90 -0.10 281.90 0.25 0.35

 HUB 13.07 0.00 -0.02 281.90 -0.10 281.90 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 48.20 47.36 0.84 315.17 422.92 7.65 518.87 491.33 1.62

 MEAN 44.17 44.80 -0.63 273.76 393.02 7.65 518.87 491.33 1.62

 HUB 38.59 38.84 -0.25 224.85 360.65 7.65 518.87 491.33 1.62

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 317.41 90.75 304.16 1112.01 0.29 2.05 1.78 7.43

 MEAN 15.50 322.77 107.11 304.48 1111.81 0.29 2.13 1.86 5.75

 HUB 12.59 344.32 159.71 305.04 1111.61 0.31 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 308.64 374.15 217.88 0.34 1629.90 0.92 0.86 

 MEAN 266.62 343.73 159.51 0.31 1661.46 0.92 0.86 0.86 1.23

 HUB 216.60 310.30 56.89 0.28 2011.96 0.92 0.86

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.21 1.03 7.77 529.75 1.01 521.66 493.57 1.49

 MEAN 8.22 1.03 7.75 529.84 1.01 521.47 493.61 1.49

 HUB 8.26 1.03 7.74 530.81 1.01 521.29 494.11 1.50

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 16.61 35.62 31.50 4.12 0.93 0.19 1.40

 MEAN 19.38 27.65 23.50 4.15 0.90 0.21 1.64

 HUB 27.63 10.56 6.50 4.06 0.90 0.25 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.940 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 364.4805 109.0721 347.7776 1109.6598 0.3285 -0.2489 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.2203 7.6361 519.4648 493.7935 1.5808 17.4128 33.0000 15.5872

 

NASA/TM—2013-218094 O–353
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 361.2628 82.4947 351.7179 1109.8644 0.3255 -0.2733 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.1948 7.6223 519.6521 493.7408 410.5396 0.0736 0.1439

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 351.4767 0.0000 351.4767 1110.4623 0.3165 0.0039 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.6383 520.2122 493.6998 0.0000 0.0600 0.1045 -0.2396

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6784 8.1800 1.0231 530.1336 4.8849 365.2444 2.8314

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 30416.695 0.319 68.227 402388.938 0.327615E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0788 Tt4 = 530.1336 T1 = 491.4125

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 241067.97 540.7379 87.2027 1.2560 0.8233 9.1568 1.0788 37.3740

NASA/TM—2013-218094 O–354
*********************************************************************

**************** AXIAL & CENTRIFUGAL COMPRESSOR BLADE DESIGN 1-D  

** ******************* COMDES Version 19.0 ************************

**************** with Stator Vane, Gasplus Prop ******************

*********************************************************************

 

 Fan Core + 4 Stage LPC 10% 20047 ft 05-13-2013 

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 1

 BLEED = 0.000 DPInc = 5.575 EfDer = 0.999 SH = 0.594204E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.728 1793.769 7.939 506.410 1.000 1.000 0.980

 W Kg/sec = 22.149 Wdry = 48.699 WH2O = 0.029 lbm/sec H2O = 0.397g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 89.149 1815.407 1.380 0.249 53.368 32.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 70315.680 38225.246 3.185 831.557 261.060 619.754 2.374

 

ROTOR LEADING EDGE CONDITIONS, STAGE 1

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.63 0.00 -0.02 202.94 -0.07 202.94 0.19 0.35 326.82

 MEAN 17.06 0.00 -0.02 202.94 -0.07 202.94 0.19 0.31

 HUB 12.51 0.00 -0.02 202.94 -0.07 202.94 0.19 0.26

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 57.86 50.47 7.39 322.93 381.47 7.75 503.10 483.57 5.34

 MEAN 52.77 47.20 5.57 267.05 335.47 7.75 503.10 483.57 5.34

 HUB 43.99 38.62 5.37 195.83 282.06 7.75 503.10 483.57 5.34

 

ROTOR EXIT CONDITIONS, STAGE 1 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.700 0.050 0.950 32.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.63 329.04 171.86 280.58 1095.84 0.30 7.29 6.52 16.04

 MEAN 18.04 343.81 197.08 281.72 1095.00 0.31 7.43 6.80 12.53

 HUB 15.00 387.32 263.15 284.19 1093.30 0.35 7.49 7.25 9.22

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 322.93 318.67 151.07 0.29 3547.00 0.92 0.91

 MEAN 282.33 294.33 85.24 0.27 3555.82 0.92 0.91 0.91 1.27

 HUB 234.80 285.60 28.35 0.26 3948.15 0.92 0.91

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.41 1.06 7.91 515.32 1.02 506.63 488.69 4.78

 MEAN 8.41 1.06 7.86 515.34 1.02 505.86 488.74 4.89

 HUB 8.47 1.07 7.77 516.33 1.02 504.29 489.41 5.13

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 31.49 28.30 24.20 4.10 0.93 0.29 1.80

 MEAN 34.98 16.83 12.70 4.13 0.92 0.26 2.22

 HUB 42.80 -5.70 -9.30 3.60 0.92 0.15 3.05

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.999 1.812 33.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 18.0711 360.7960 196.7020 302.4601 1094.3040 0.3297 -0.0736 5.2355

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.4249 7.8219 505.2181 488.9590 4.9907 33.0376 35.4000 2.3624

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 18.0711 307.6680 75.2650 298.3199 1097.3843 0.2804 0.2279 5.4957

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.4228 7.9812 508.0682 488.8027 554.9116 0.0136 0.3486

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 18.0829 305.3533 0.0000 305.3533 1097.5015 0.2782 0.2522 1.3089

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 7.9740 508.1822 488.7753 0.0000 0.0600 0.0385 0.2154

NASA/TM—2013-218094 O–355
 

 STAGE EXIT CONDITIONS, STAGE 1

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.8729 8.4083 1.0591 515.6645 9.2549 222.9111 1.7280

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 57670.254 0.553 158.803 474177.094 0.598192E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 2

 BLEED = 0.000 DPInc = 3.130 EfDer = 0.987 SH = 0.601533E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.728 1793.769 8.408 515.664 1.000 1.000 0.980

 W Kg/sec = 22.149 Wdry = 48.698 WH2O = 0.029 lbm/sec H2O = 0.411g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 84.939 1799.041 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 68612.461 38225.133 2.374 590.487 248.734 468.502 1.884

 

ROTOR LEADING EDGE CONDITIONS, STAGE 2

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.55 0.00 -0.02 278.87 -0.10 278.87 0.25 0.39 322.62

 MEAN 18.08 0.00 -0.02 278.87 -0.10 278.87 0.25 0.36

 HUB 15.21 0.00 -0.02 278.87 -0.10 278.87 0.25 0.33

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 49.09 46.36 2.73 321.68 425.80 8.04 509.42 488.72 4.41

 MEAN 45.43 42.30 3.13 282.99 397.37 8.04 509.42 488.72 4.41

 HUB 40.50 37.84 2.66 238.09 366.75 8.04 509.42 488.72 4.41

 

ROTOR EXIT CONDITIONS, STAGE 2 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 20.42 321.97 105.71 304.12 1102.45 0.29 2.33 2.04 9.02

 MEAN 18.01 329.16 125.33 304.37 1102.31 0.30 2.40 2.13 7.35

 HUB 15.22 355.52 182.95 304.83 1102.17 0.32 2.45 2.27 4.53

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 319.65 371.83 213.93 0.34 2160.62 0.92 0.90

 MEAN 281.92 342.29 156.59 0.31 2258.94 0.92 0.90 0.90 1.25

 HUB 238.29 309.82 55.34 0.28 2786.51 0.92 0.90

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.70 1.03 8.21 521.09 1.01 512.77 491.65 3.98

 MEAN 8.72 1.04 8.20 521.34 1.01 512.64 491.79 4.00

 HUB 8.79 1.05 8.19 522.66 1.01 512.52 492.54 4.01

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 19.17 35.12 31.50 3.62 0.93 0.22 1.40

 MEAN 22.38 27.22 23.50 3.72 0.91 0.24 1.63

 HUB 30.97 10.29 6.50 3.79 0.91 0.28 1.97

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.987 0.567 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.9595 365.8097 125.6826 343.5413 1100.4889 0.3324 -0.1938 2.3644

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.7298 8.0952 510.9611 492.0714 4.2000 20.0948 30.6000 10.5052

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.9595 339.3846 71.9520 331.6698 1102.1013 0.3079 -0.0444 2.4513

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.7215 8.1737 512.4562 491.9808 491.5697 0.0254 0.1608

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.8235 352.0559 0.0000 352.0559 1101.3420 0.3197 0.0234 0.5911

NASA/TM—2013-218094 O–356
 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.1101 511.7533 491.9761 0.0000 0.0600 0.0714 -0.1628

 

 STAGE EXIT CONDITIONS, STAGE 2

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.7981 8.6968 1.0343 521.6989 6.0344 303.4442 2.3523

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 37605.926 0.368 103.553 439695.031 0.602622E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 3

 BLEED = 0.000 DPInc =-0.258 EfDer = 0.946 SH = 0.603804E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.728 1793.769 8.697 521.699 1.000 1.000 0.980

 W Kg/sec = 22.149 Wdry = 48.698 WH2O = 0.029 lbm/sec H2O = 0.421g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 82.601 1788.606 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 67365.469 38225.102 2.255 545.479 241.888 424.468 1.755

 

ROTOR LEADING EDGE CONDITIONS, STAGE 3

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 20.07 0.00 -0.02 296.39 -0.10 296.39 0.27 0.39 313.25

 MEAN 17.74 0.00 -0.02 296.39 -0.10 296.39 0.27 0.37

 HUB 15.05 0.00 -0.02 296.39 -0.10 296.39 0.27 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 46.68 46.36 0.32 314.17 431.99 8.28 514.65 491.84 3.76

 MEAN 43.14 43.40 -0.26 277.67 406.21 8.28 514.65 491.84 3.76

 HUB 38.49 38.84 -0.35 235.59 378.68 8.28 514.65 491.84 3.76

 

ROTOR EXIT CONDITIONS, STAGE 3 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 19.81 333.88 80.38 324.06 1106.71 0.30 2.26 1.98 8.75

 MEAN 17.51 340.63 105.82 323.78 1107.02 0.31 2.34 2.07 6.78

 HUB 14.85 366.76 172.18 323.83 1107.32 0.33 2.38 2.20 4.28

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 310.10 397.22 229.72 0.36 1594.31 0.92 0.87

 MEAN 274.04 364.87 168.22 0.33 1854.28 0.92 0.87 0.87 1.19

 HUB 232.46 329.40 60.28 0.30 2558.39 0.92 0.87

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 8.91 1.02 8.37 525.70 1.01 516.76 493.94 3.53

 MEAN 8.94 1.03 8.38 526.36 1.01 517.05 494.28 3.49

 HUB 9.04 1.04 8.39 528.13 1.01 517.33 495.22 3.46

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 13.93 35.33 31.50 3.83 0.93 0.15 1.40

 MEAN 18.10 27.45 23.50 3.95 0.90 0.18 1.62

 HUB 28.00 10.54 6.50 4.04 0.90 0.25 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.946 0.550 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 17.3924 380.5377 106.5103 365.3279 1104.9381 0.3444 -0.2082 2.2836

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 8.9574 8.2608 515.1096 494.5651 3.6945 16.2539 31.5000 15.2461

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 17.3924 367.2710 80.1177 358.4260 1105.7963 0.3321 -0.1494 2.3726

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 8.9412 8.2922 515.9054 494.4981 451.3937 0.0377 0.1164

 

NASA/TM—2013-218094 O–357
 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 17.1214 374.5553 0.0000 374.5553 1105.3300 0.3389 -0.0412 0.5709

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2321 515.4718 494.4566 0.0000 0.0600 0.1022 -0.2523

 

 STAGE EXIT CONDITIONS, STAGE 3

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.6735 8.9035 1.0238 526.7288 5.0300 344.6506 2.6717

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 31348.182 0.326 86.322 445256.500 0.604816E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 4

 BLEED = 0.000 DPInc =-3.347 EfDer = 0.887 SH = 0.605915E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.728 1793.769 8.904 526.729 1.000 1.000 0.980

 W Kg/sec = 22.149 Wdry = 48.698 WH2O = 0.030 lbm/sec H2O = 0.427g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 81.071 1780.045 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin 

 66664.461 38225.070 2.162 513.330 237.410 395.845 1.667

 

ROTOR LEADING EDGE CONDITIONS, STAGE 4

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 19.26 0.00 -0.02 311.68 -0.11 311.68 0.28 0.39 299.17

 MEAN 16.97 0.00 -0.02 311.68 -0.11 311.68 0.28 0.37

 HUB 14.32 0.00 -0.02 311.68 -0.11 311.68 0.28 0.35

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 44.06 46.36 -2.30 301.49 433.71 8.43 518.93 494.30 3.29

 MEAN 40.45 43.80 -3.35 265.65 409.60 8.43 518.93 494.30 3.29

 HUB 35.74 37.84 -2.10 224.16 383.98 8.43 518.93 494.30 3.29

 

ROTOR EXIT CONDITIONS, STAGE 4 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 18.88 344.18 53.13 340.05 1109.90 0.31 2.16 1.89 8.34

 MEAN 16.57 349.16 82.06 339.38 1110.56 0.31 2.24 1.97 6.35

 HUB 13.89 372.42 153.75 339.20 1111.20 0.34 2.26 2.10 4.19

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 295.54 417.61 242.41 0.38 1005.10 0.92 0.81

 MEAN 259.44 382.94 177.38 0.34 1361.81 0.92 0.81 0.81 1.14

 HUB 217.43 345.12 63.67 0.31 2137.19 0.92 0.81

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.03 1.01 8.46 529.25 1.00 519.75 495.60 3.21

 MEAN 9.07 1.02 8.48 530.15 1.01 520.37 496.04 3.15

 HUB 9.17 1.03 8.50 532.10 1.01 520.97 497.03 3.09

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 8.88 35.48 31.50 3.98 0.93 0.08 1.40

 MEAN 13.59 27.59 23.50 4.09 0.89 0.13 1.62

 HUB 24.38 10.63 6.50 4.13 0.89 0.20 1.94

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.887 0.524 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 16.4812 382.8065 82.5174 373.8070 1108.8212 0.3452 -0.1708 2.1803

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.0866 8.3768 518.7424 496.2909 3.2978 12.4483 32.4000 19.9517

 

 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 16.4812 383.3687 85.9784 373.6031 1108.7888 0.3458 -0.2029 2.2705

 

NASA/TM—2013-218094 O–358
 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0629 8.3529 518.7076 496.2522 432.2457 0.0485 0.0804

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 16.0960 381.7982 0.0000 381.7982 1108.8925 0.3443 -0.0917 0.5451

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.3117 518.8039 496.1608 0.0000 0.0600 0.1311 -0.2699

 

 STAGE EXIT CONDITIONS, STAGE 4

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.4675 9.0121 1.0122 530.5002 3.7714 425.4954 3.2984

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 23505.115 0.269 64.725 463875.813 0.606896E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 

COMPRESSOR INLET CONDITIONS - ANALYSIS, STAGE 5

 BLEED = 0.000 DPInc =-6.213 EfDer = 0.824 SH = 0.608025E-03

 

 W act RPM act Pt Tt POTS POTH AeroBl

 48.728 1793.769 9.012 530.500 1.000 1.000 0.980

 W Kg/sec = 22.149 Wdry = 48.698 WH2O = 0.030 lbm/sec H2O = 0.430g/m^3

 

 W cor RPM cor GAMMA Cp R Blades THK

 80.380 1773.707 1.380 0.249 53.368 77.000 0.050

 

 CFM SCFM A1/A* Area1 A* AthrRotor ChokeMargin

 66324.656 38225.035 2.165 509.668 235.388 384.739 1.634 

 

ROTOR LEADING EDGE CONDITIONS, STAGE 5

 

 R1 Stator Alfa C1 CU1 Cm1 Mabs Mrel U1cor

 TIP 18.32 0.00 -0.02 312.32 -0.11 312.32 0.28 0.38 283.56

 MEAN 15.91 0.00 -0.02 312.32 -0.11 312.32 0.28 0.36

 HUB 13.07 0.00 -0.02 312.32 -0.11 312.32 0.28 0.34

 

 BetaFlo BetaBlade Incid U1 W1 Ps1 Ts1 TwetBulb1 RH

 TIP 42.57 47.36 -4.79 286.77 424.08 8.54 522.67 495.99 2.93

 MEAN 38.59 44.80 -6.21 249.10 399.56 8.54 522.67 495.99 2.93

 HUB 33.24 38.84 -5.60 204.59 373.42 8.54 522.67 495.99 2.93

 

ROTOR EXIT CONDITIONS, STAGE 5 SOLUTION IS CONVERGED

 B2 axial THK AeroBl Blades2

 0.500 0.050 0.950 77.000

 

 R2 C2 Cu2 Cm2 Ao2 Mach2 Chord AxChord Rcircle

 TIP 17.94 343.05 35.04 341.26 1112.98 0.31 2.05 1.78 7.43

 MEAN 15.50 346.34 62.92 340.58 1113.71 0.31 2.13 1.86 5.75

 HUB 12.59 365.32 132.51 340.44 1114.41 0.33 2.14 1.98 3.85

 

 U2 W2 Wu2 MachRel2 DelRCu Eff2uC Eff2incC AvgREff Ws1/W2

 TIP 280.83 420.56 245.78 0.38 630.65 0.92 0.75

 MEAN 242.59 385.07 179.68 0.35 976.78 0.92 0.75 0.75 1.10

 HUB 197.08 346.51 64.57 0.31 1669.72 0.92 0.75

 

 Pt2 PR Ps2 Tt2 TR Ts2 TwetBulb2 RH 

 TIP 9.09 1.01 8.51 532.08 1.00 522.64 496.80 2.93

 MEAN 9.13 1.01 8.54 532.95 1.00 523.33 497.22 2.87

 HUB 9.21 1.02 8.56 534.69 1.01 523.99 498.07 2.81

 

 Alfa2 Beta FLO Beta BLADE Deviat Slip F. DiffFct Solidity 

 TIP 5.86 35.76 31.50 4.26 0.93 0.04 1.40

 MEAN 10.47 27.81 23.50 4.31 0.87 0.08 1.64

 HUB 21.27 10.74 6.50 4.24 0.87 0.16 2.01

 

 

 blockage3 Cor/U1 Cor/Incid XBladeGap Vane# 

 0.950 1.000 0.824 0.495 73.000

 

 ROTOR-STATOR GAP EXIT: STATOR LEADING EDGE

 R3m C3 Cu3 Cm3 Ao3 Mach3 cp 2-3 Stat Ax Chd

 15.2185 395.6109 64.0710 390.3882 1110.8925 0.3561 -0.2830 2.0437

 

 Pt3 Ps3 Ts3 TwetBulb3 RH3 FloAlpha3 VaneAlpha3 Incid3

 9.1283 8.3720 520.6870 497.4655 3.0862 9.3204 33.0000 23.6796

 

NASA/TM—2013-218094 O–359
 STATOR / VANED DIFFUSER THROAT IS NOT CHOKED:

 RCG Cth Cuth Cmth Aoth Machth cp 2-Th Stat Chord

 15.2185 408.8428 93.3596 398.0407 1109.9884 0.3683 -0.4403 2.1315

 

 BlockageTh PtTh PsTh TsTh TwetBulbTh AreaTh w2-Th DiffFact4

 0.9500 9.0738 8.2725 519.8324 497.4118 410.5396 0.1106 0.0535

 

 VANED DIFFUSER EXIT:

 R4 C4 Cu4 Cm4 Ao4 Mach4 cp 3-4 Stator Gap

 14.7013 397.6245 0.0000 397.6245 1110.7661 0.3580 -0.1011 0.5109

 

 Blockage4 Ps4 Ts4 TwetBulb4 VaneAlpha4 Vane Thk4 w2-4OD cp 2-4 

 0.9500 8.2956 520.5580 497.3412 0.0000 0.0600 0.1449 -0.4021

 

 STAGE EXIT CONDITIONS, STAGE 5

 Eff4 Pt4 PR4 Tt2avg Del T Ns Ns nondim

 0.2415 9.0531 1.0045 533.2441 2.7440 538.7312 4.1762

 

Del Enthalpy Del_H/U^2 GHP Reynolds# SH

 17101.982 0.217 47.093 493841.344 0.609046E-03

 

Melt Ratio at Stator LE, Throat, TE

0.00000E+00 0.00000E+00 0.00000E+00

 trTOT = 1.0530 Tt4 = 533.2441 T1 = 506.4096

 

 OVERALL EXIT CONDITIONS; ALL 5 STAGES

 

 Del Enthalpy GHP MassFloS1cor OPR Efficiency Rotor1Inc TR AxHubLen

 167231.45 460.4963 89.1486 1.1403 0.6953 5.5749 1.0530 37.3740

NASA/TM—2013-218094 O–360
References 1

Mason, J. G., Strapp, J. W., Chow, P., “The Ice Particle Threat to Engines in Flight,” AIAA-2006-206-739. 2

Mason, J. G., Chow, P., Fuleki, D. M., “Understanding Ice Crystal Accretion and Shedding Phenomenon in Jet Engines Using a 

Rig Test,” GT2010-22550. 3

Mason, J. G., Grzych, M., “The Challenges Identifying Weather Associated With Jet Engine Ice Crystal Icing,” SAE 2011-38-

0094. 4

Jorgenson, P. C. E., Veres, J. P., Wright, W. B., May, R. D., “Engine Icing Modeling and Simulation (Part I): Ice Crystal 

Accretion on Compression System Components and Modeling its Effects on Engine Performance,” SAE International, 2011-38-

0025. 5 Veres, J. P., Jorgenson, P. C. E., Wright, W. B., “Modeling the Effects of Ice Accretion on the Low Pressure Compressor and 

the Overall Turbofan Engine System Performance,” NASA/TM-2013-217034. 6

Jones, S. M., “An Introduction to Thermodynamic Performance Analysis of Aircraft Gas Turbine Engine Cycles Using the 

Numerical Propulsion System Simulation Code,” NASA/TM-2007-214690. 7

Veres, J. P., “Axial and Centrifugal Compressor Mean Line Flow Analysis Method,” AIAA-2009-1641, NASA/TM-2009-

215585. 8

Wright, W. B., Potapczuk, M. G., and Levinson, L. H., “Comparison of LEWICE and GlennICE in the SLD Regime,” 

AIAA-2008-0439. 9

Wright, W. B., Jorgenson, P. C. E., Veres, J. P., “Mixed Phase Modeling in GlennICE with Application to Engine Icing,” 

AIAA-2010-81093. 10Struk, P., Currie, T., Wright, W. B., Tsao, J.-C., Broeren, A., Vargas, M., Knezevici, D., and Fuleki, D., “Fundamental Ice 

Crystal Accretion Physics Studies,” SAE-2011-38-0018 or NASA/TM−2012-217429, 2011. 11Fowler, J. R., “GASPLUS User's Manual,” NASA LEW−15091, 1994. 12Incropera, F. P., and DeWitt, D. P., Fundamentals of Heat and Mass Transfer, John Wiley & Sons, New York, 1990. 13Çengel, Y. A., and Boles, M. A., Thermodynamics: An Engineering Approach, McGraw-Hill, New York, Inc., 1989. 14Currie, T. C., Struk, P. M., Tsao, J.-C., Fuleki, D., Knezevici, D., “Fundamental Study of Mixed-Phase Icing with Application 

to Ice Crystal Accretion in Aircraft Jet Engines,” AIAA 2012-3035. 15McCullers, L. A., “Aircraft Configuration Optimization Including Optimized Flight Profiles,” Proceedings of the Symposium 

on Recent Experiences in Multidisciplinary Analysis and Optimization, NASA CP 2327, April 1984. 16Veres, J. P., Jorgenson, P. C. E., Wright, W. B., Struk, P., “A Model to Assess the Risk of Ice Accretion due to Ice Crystal 

Ingestion in a Turbofan Engine and its Effects on Performance”, AIAA 2012-3038.

NASA/TM—2013-218094 R–1
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4. TITLE AND SUBTITLE

A Model to Assess the Risk of Ice Accretion Due to Ice Crystal Ingestion in a Turbofan 

Engine and its Effects on Performance 

5a. CONTRACT NUMBER

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6. AUTHOR(S)

Jorgenson, Philip, C. E.; Veres, Joseph, P.; Wright, William, B.; Struk, Peter, M. 

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5f. WORK UNIT NUMBER

WBS 648987.02.02.03.20 

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

National Aeronautics and Space Administration 

John H. Glenn Research Center at Lewis Field 

Cleveland, Ohio 44135-3191 

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 REPORT NUMBER

E-18790 

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This publication is available from the NASA Center for AeroSpace Information, 443-757-5802

13. SUPPLEMENTARY NOTES

This report is a revised and expanded version of AIAA-2012-3038 presented at the Atmospheric Space Environments Conference sponsored 

by the American Institute of Aeronautics and Astronautics, New Orleans, Louisiana, June 25-28, 2012. 

14. ABSTRACT

The occurrence of ice accretion within commercial high bypass aircraft turbine engines has been reported under certain atmospheric 

conditions. Engine anomalies have taken place at high altitudes that were attributed to ice crystal ingestion, partially melting, and ice 

accretion on the compression system components. The result was one or more of the following anomalies: degraded engine performance, 

engine roll back, compressor surge and stall, and flameout of the combustor. The main focus of this research is the development of a 

computational tool that can estimate whether there is a risk of ice accretion by tracking key parameters through the compression system 

blade rows at all engine operating points within the flight trajectory. The tool has an engine system thermodynamic cycle code, coupled with 

a compressor flow analysis code, and an ice particle melt code that has the capability of determining the rate of sublimation, melting, and 

evaporation through the compressor blade rows. Assumptions are made to predict the complex physics involved in engine icing. 

Specifically, the code does not directly estimate ice accretion and does not have models for particle breakup or erosion. Two key parameters 

have been suggested as conditions that must be met at the same location for ice accretion to occur: the local wet-bulb temperature to be near 

freezing or below and the local melt ratio must be above 10 percent. These parameters were deduced from analyzing laboratory icing test 

data and are the criteria used to predict the possibility of ice accretion within an engine including the specific blade row where it could 

occur. Once the possibility of accretion is determined from these parameters, the degree of blockage due to ice accretion on the local stator 

vane can be estimated from an empirical model of ice growth rate and time spent at that operating point in the flight trajectory. The 

computational tool can be used to assess specific turbine engines to their susceptibility to ice accretion in an ice crystal environment.

15. SUBJECT TERMS

Flow simulation; Aeropropulsion; Engine icing; Aircraft turbine engine system simulation; Turbine engine; Compressor 

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