NASA Contractor Report 179469

UTRC-R86-956480-.4

The Effects of Inlet Turbulence and Rotor/

Stator Interactions on the Aerodynamics

and Heat Transfer of a Large-Scale

Rotating Turbine Model

m ;

, IV--Aerodynamic Data Tabulation

R.P Dring, H.D. Joslyn, and M.F. Blair

United Technologies Research Center

East Hartford, Connecticut

November 1987

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FORENORD

This report was prepared for the National Aeronautics and Space

AdministrationD Lewis Research Center by the United Technologies Research

Center, East Hartford, Connecticut, under Contract NAS3-23717. The

performance period covered by this report was II April, 1983 to 11 June, 1986.

The project monitor was Dr. Robert J. Simoneau.
R86-956480-4

THE EFFECTS OF INLET TURBULENCE AND

ROTOR/STATOR INTERACTIONS ON THE AERODYNAMICS

AND HEAT TRANSFER OF A LARGE-SCALE

ROTATING TURBINE MODEL

VOLUME IV

AERODYNAMIC DATA TABULATION

TABLE OF CONTENTS

FOREWORD

INTRODUCTION ...........................

OBJECTIVES ...........................

DESCRIPTION OF EXPERIMENT ......................

Turbine Facility ......................

Airfoil Coordinates and Aerodynamics ..............

Inlet Turbulence ......................

Heat Transfer Instrumentation ................

Aerodynamic Instrumentation and Data .............

NOMENCLATURE ............................

REFERENCES

FIGURES

i

I

2

3

3

3

5

9

ii

34

ili
INTRODUCTION

The primary basis currently used by the gas turbine community for heat

transfer analysis of turbine airfoils is experimental data obtained in linear

cascades. These data have been very valuable in identifying the major heat

transfer and fluid flow features of turbine airfoils. The question remains,

however, as to how well cascade data translate to the rotating turbine stage.

It is known from the work of Lokay and Trushin (ref. 1) that average heat

transfer coefficients on the rotor may be as much as 40 percent above the

values measured on the same blades without rotation. Recent work by Dunn and

Rolt (ref. 2) supports the conclusions of reference 1. It is widely recognized that at this time a need exists for a set of heat transfer data from a

rotating system which is of sufficient detail to allow careful local comparisons between static cascade and rotor blade distributions. It is important

that this data set include sufficient flow field documentation to support the

computer analyses being developed today.

Other important questions include the impact of both random and periodic

unsteadiness on both the rotor and stator airfoil heat transfer. The random

unsteadiness arises from stage inlet turbulence and wake generated turbulence

and the periodic unsteadiness arises from blade passing effects. A final

question is the influence, if any, of the first stator row and first stator

inlet turbulence on the heat transfer of the second stator row after the flow

has been passed through the rotor.
0

OBJECTIVES

The first program objective has been to abtain a detailed set of heat

transfer coefficients along the midspan of a stator and a rotor in a rotating

turbine stage (fig. I). The experimental program was designed such that the

rotor data _oald be compared directly with data taken in a static cascade.

The data are compared to a standard analysis of blade boundary layer heat

transfer which is widely available today. In addition to providing this allimportant comparison between rotating and stationary data, this experiment

provides important insight to the more elaborate full three-dimensional

programs being proposed for future research. A second program objective has

been to obtain a detailed set of heat transfer coefficients along the midspan

of a stator located in the wake of an upstream turbine stage. The axial

location of the second stator relative to the upstream turbine stage is shown

in figure 2. Particular focus here was on the relative circumferential

location of the first and second stators. Both program objectives were

carried out at two levels of inlet turbulence. The low level was on the order

of I percent while the high level of approximately I0 percent is more typical

of combustor exit turbulence intensity. The final program objective is to

improve the analytical capability to predict the experimental data.
DESCRIPTIONOFEXPERIMENT

1. Turbine Facility

All experimental work for this program was conducted in the United

Technologies Research Center Large Scale Rotating Rig (LSRR) shown in figure

2. This test facility was designed for conducting detailed experimental

investigations of flow within turbine and compressor blading. Primary

considerations were to provide a rig which would: (I) be of sufficient size

to permit a high degree of resolution of three-dimensional flows, (2) possess

a high degree of flexibility in regard to the configurations which can be

tested, and (3) enable measurements to be made directly in the rotating frame

of reference.

The facility is of the open circuit type with flow entering through a 12-

ft diameter inlet. A 6-in. thick section of honeycomb is mounted at the inlet

face to remove any cross flow effects. The inlet smoothly contracts the cress

section diameter down to 5-ft. Flow is then passed through a series of three

fine mesh screens to reduce the turbulence level. Immediately downstream of

the screens is a telescoping section which slides axially and permits access

to the test section. The test section consists of an axial series of constant

diameter casings enclosing the turbine, compressor or, fan model assemblies.

The casings are wholly or partially transparent, which facilitates flow

visualization and laser-Doppler-velocimeter studies. The rotor shaft is

cantilevered from two downstream bearings thus providing a clean flow path to

the most upstream row of test airfoils. Axial length of the test section is

36-in. _ne rotor is driven or braked by a hydraulic pump and motor system

which is capable of maintaining shaft speeds up to 890 rpm. Downstream of the

test section flow passes through an annular diffuser into a centrifugal fan

and is subsequently exhausted from the rig. A vortex valve is mounted at the

fan inlet face for flow rate control.

2. Airfoil Coordinates and Aerodynamics

The surface hub, midspan, and tip coordinates (x,y) of the three airfoil

rows (stator I, rotor and stator 2) are given in Tables I, 2, and 3 respectively. The aerodynamic documentation of the turbine stage indicated that all

parameters were very close to data obtained during prior testing with this

turbine model, reference 3. As an example, the first stator and rotor

pressure distributions are shown in figures 3a and 3b for the case with the

small (15%) axial gap, at the design flow coefficient (Cx/U m = 0.78), and

with the inlet turbulence generating grid installed. Agreement with a twodimensional potential fl_w calculation (ref. 4) at this midspan location is

excellent. The computed surface velocity distributions are used as the input
to the suction and pressure surface boundary layer calculations (refs. 5, 6).

The resulting calculated suction and pressure surface Stanton number distributions are presented along with the measured results in Volumes I thru III.

3. Inlet Turbulence

As part of the present contract heat transfer distributions through the

LSRR turbine blading were examined for both low and high ievels of inlet

turbulence. Throughout this report the low and high levels are referred to as

"grid out" and "grid in" respectively. With the test facility configured in

the minimum inlet turbulence arrangement (grid out) the inlet turbulence was

approximately 0.5% at an axial location 22% of axial chord ahead of the first

stator leading edge. Higher levels of inlet turbulence were produced by

installing a biplane grid upstream of the first stator. The turbulence

generator consisted of a nearly square array lattice of three concentric rings

spaced uniformly in the radial direction with 80 radial bars evenly spaced

circumferentially. Both the rings and radial bars were of nearly square I/2

inch cross-sections. The mesh spacing of the bars was 2.1 inches radially and

4.5 degrees (2.1 in. at mid-annulus) circumferentially. With the grid

installed at the inlet turbulence intensity was typically 9.8%. The spanwise

distributions at four different circumferential locations (relative to the

stator leadit._ ge) are shown in figure 4. The data indicate that the turbulence is spatially uniform, nearly isotropic, and temporally (long time

average) steady. This is representative of the level of turbulence measured

at the exit of aircraft gas turbine combustors.

4. Heat Transfer Instrumentation

Heat transfer measurements were obtained in this study using low conductivity rigid foam castings of the test airfoils. A uniform heat flux was

generated on the surface of the foam test airfoils using electrically heated

metal foil strips attached to the model surface. Conduction and radiation

effects produced small departures fro_ complete uniformity. Local airfoil

surface temperatures were measured using thermocouples welded to the back of

the foil while the air temperature was measured using the rmocouples in the air

stream. The secondary junctions to copper wire were all made on Uniform

Temperature Reference blocks (Kaye Instruments, UTR-48N) and the data were

recorded using a Hewlett-Packard 300 channel data acquisition unit

(3497A/3498A), and an ice point reference (Kaye Instruments, K140-4). A 212

ring slip-ring unit (Wenden Co.) was used to bring heater power onto the rotor

and to bring out the thermocouple data. Instrumentation locations for the

first stage stator and rotor are given in figures 5a and 5b. Locations for

the second stator are given in Volumes I and Ill.

p °
t

IN

J

5. AeroOynamic Instrumentation and Data

The steady aerodynamic measurements'consisted of hub and casing flowpath

static pressures acquired downstream of each airfoil row, midspan surface

static pressure distributions obtained on each airfoil and circumferential

distributions of total and static pressures and the flow yaw and pitch angles

obtained from a 5 hole pneumatic probe (United Sensors USC-F-152) traverse

downstream of each airfoil row. The hub and casing flowpath static pressures

and probe traverse data were acquired at station_ 2, 3 and 4 (fig. 2). The

location of the airfoil surface static pressure measurement sites is given in

Tables 7 through 9 in terms of the axial distance (DIST = X/Bx) from the

airfoil leading edge tangency plane.

A dedicated online Perkin Elmer (PE 8/16E) minicomputer controls the

online calibration of all pressure transducers (Druck model PDCR-22), radial

and circumferential positioning and yaw nulling of stationary and rotating

frame probes (United Sensors USC-F-152) and the acquisition and online reduction of all steady aerodynamic data. Electrical commanication with the

rotating frame instrumentation package, transducers and traverse system was

through a Fabricast (model 1273) slip-ring assembly mounted on the rotor drive

shaft.

High response inter-row velocity and unsteadiness measurements were made

by traversing a radially oriented, single element hot film probe (Thermo

Systems Inc., TSI model 1211-20) downstream of each airfoil row (stations 2, 3

and 4, fig. 2) at midspan. The probe was calibrated from 40 to 200 feet per

second, was powered by a TSI Model 1050 anemometer and was traversed in the

stationary frame of r@ference. Positioning of the hot film probe and data

acquisition was controlled by the PE 8/16E minicomputer.

The aerodynamic instrumentation and data are presented in the following

Tables and Figures.

Airfoil geometry

Flowpath static pressures

Airfoil pressure distributions

Pitch-averaged unsteadiness

Stage-geometry

Inlet turbulence (Grid In)

Heat transfer instrumentation

5-Hole probe traverse data

Hot-Film probe traverse data

Tables I through 3

Tables 4 through 6

Tables 7 through 9, and

Figures 3, and 6 through 14

Table 10

Figures l and 2

Figure 4

Figure 5

Figures 15 through 32

Figures 33 through 41
A brief overview of the tables and figures containing the aerodynamic data

follows: -.

Flowpath Static Pressures

The hub, mean and outer casing flowpath static pressures at the exit of

the first stator, the rotor and the second stator are presented in Tables 4,

5, and 6 respectively. The hub and outer casing flowpath pressures preJented

are averages based on measured pressures and account for blade-to-blade as

well as circumferential (annulus) variations. The mean (i.e. midspan)

flowpath static pressure is calculated from a free vortex distrib:.tion between

the measured hub and outer casing flowpath static pressures (pitch and annulus

averages). Results are shown for all three flow coefficients (Cx/U m =

0.68, 0.78, 0.96), for two first stator/rotor axial spacings (x/B x = 0.15

and 0.50) and for two inlet turbulence levels (grid out and grid in).

Airfoil Pressure Distributions

Turbine stage (first stator and rotor) airfoil midspan pressure distributions obtained at all three flow coefficients and at axial spacings of 15 and

50 percent axial chord are presented in Tables 7a,b and 8a,b respectively.

Tables 7a and 8a contain the data acquired with the grid out; Tables 7b and

8b contain the data acquired with the grid in. The second stator midspan

pressure distributions acquired with the grid out and with the grid in for a

first stator/rotor axial spacing of 50 percent are presented in Tables 9a and

9b respectively. In all tables (7 through 9), the static pressure coefficient

(Cps) is tabulated along with the axial distance (DIST = X/B x) from the

airfoil leading edge tangency plane. The base pressures measured on each

airfoil at midspan are also included in the appropriate data set.

The airfoil midspan pressure distribution data are plotted as the symbols

in figures 3, and 6 through 14. In figures b through 11, all the data sets

are presented in terms of a pressure coefficient based on the inlet (station

1) total pressure and the first stator exit (station 2) dynamic pressure, Q2.

This permits all of the airfoil data to be compared directly on the same

basis. From these results it is clear that the addition of the grid had

little impact on the airfoil midspan pressure distributions. Also, it is

evident that the first stator midspan pressure distribution was virtually the

same at all three flow coefficients. The abbreviations (aS, PS, TE, BP, CG2,

CGTI) on the right hand side of the figures represent suction surface,

pressuxe surface, trailing edge, base pressure, airfoil exit static pressure

and the rotor inlet relative total pressure respectively. In figures 3 (grid

in) and 12 through 14 (grid out), the data is presented along with the results

of a potential flow -ulation (Ref. 4). 8ere, the pressure coefficient is

based on the inlet tot pressure and exit static pressure relative to a

particular airfoil row.
L_

Pitch-Averaaed Unsteadiness

The average total (UT) , periodic (Up) and random (U R) unsteadiness at a

single radlal/circumferential hot film traverse location in the turbine model

are defined in Table 10a. Vk(t) represents the instantaneous film speed

measured with a radially oriented single element hot film probe during a

specific rotor revolution. It is composed of a periodic component, V(t_ and a

random component, v_(t). Vo is the time average speed at this location. At

each radial/circumferential traverse location at stations 2, 3, and 4 (fig.

2), one hundred sets (Nre v = 100) of instantaneous speed data were acquired

and processed (ensemble and time averaged) to obtain the midspan circumferential distributions of average total, periodic and random unsteadiness

presented in figures 33 through 41. Measurements were made at all three flow

coefficients with the grid out and with the grid in. The midspan circumferential distributions of the average total, periodic and randcm unsteadiness were

pitch averaged and the results are summarized in Tables 10b, 10c, and 10d for

the flow coefficients of 0.68, 0.78 and 0.96 respectively.

5-Hole Probe Traverse Data

A single 5 hole pneumatic probe (United Sensor model USC-F-152) was

traversed circumferentially at midspan to measure total and static pressures

and the flow yaw and pitch angles downstream of each airfoil (stations 2, 3

and 4). The resulting circumferential distributions taken over two first

stator pitches are presented in figures 15 through 32. The results obtained

with the grid out and with the grid in at three flow coefficients are

presented for each airfoil (first stator, rotor and second stator).

The results for each airfoil are pre_ented in the same sequence as that

which follows for data in the absolute frame downstream of the first stator

(for flow coefficients of 0.68, 0.78 and 0.96).

Figure S_mbol Quantity Grid

15a-c CPTABS Total pressure Out

CTOT Flow speed

16a-c CPS Static pressure Out

CX/UM Axial velocity

17a-c YAWABS Flow yaw angle Out

PHI Flow pitch angle

18a-c CPTABS Total pressure In

CTOT Flow speed

r.
19a-c CPS Static pressure

CX/UM Axial velocity

In

20a-c YAWABS

PHI

Flow yaw angle

Flow pitch angle

In

For the data in the rotating frame downstream of the rotor these quantities

are as follows, CPTREL, _rrOT, CPS, CX/UN, YAWREL, and PRI.

Rot Film Probe Traverse Data

The midspan circumferential distributions of ensemble-time averaged flow

speed (VTAVG) and unsteadiness (total, periodic and random) at the exit of

each airfoil are presented in figures 33 through 4l. These results were

obtained with the grid out and with the grid in by traversing a radially

oriented single element hot film probe over two first stator pitches downstream of each airfoil row. Figures 33a to 35b show the results for the first

stator, rotor and second stator at a flow coefficient of 0.68 with the grid

out and with the grid in. The results obtained at flow coefficients 0.78 and

0.96 are presented in figures 36a and 39a to 41b respectively.

Access to AerodYnamic Data

Copies of the aerodynamic data can be obtained by contacting Robert Dring

of UTRC by phone at 203-727-7044.

8

4

q,
E X

Cp

CTo t

Cx

P

PT

qo

m

S

U

U

m

U

U

WTo t

X

NOMENCLATURE

airfoil axial chord

pressure coefficient (based on turbine inlet total pressure and

%m)

absolute flow speed normalized by Um

axial f'.ow speed

static pressure

total pressure

dynamic pressure based on Um

surface arc length from trailing edge

streamwise velocity

rotor midspan wheel speed

stage inlet flow velocity

unsteadiness (T: total, R: random, and P: periodic) (_T = _R + _P)

relative flow speed normalized by U

m

axial distance

{%

0

A

Cp

absolute flow angle from axial

relative flow angle from axial

density

flow coefficient (Cx/U m)

pressure coefficient (based on turbine inlet total pressure and

first stator exit dynamic pressure Q2)
Superscripts

S_bscripts

0

1

2

3

4

ABS

IN

REL

time average

model inlet upstream of turbulence grid

first stator inlet

first stator exit

rotor exit

second stator exit

absolute (stationary) frame

inlet properties relative to airfoil rows

relative frame

I0

I,,
II

o

o

m

o

o

P,_FERENCES

I_kay, V. I., and Trushin, V. A.: Heat Transfer from the Gas and FlowPassage Elements of a Rotating Gas Turbine. Heat Transfer - Soviet

R_search, Vol. 2, No. 4, July 1970.

Dun_, M. G., and Holt, J. L.: The Turbine Stage Heat Flux Measurements.

Paper No. 82-1289, AI_II_SME 18th Joint Propulsion Conference, 21-23,

June 1982, Cleveland, _.!o.

Dring, R. P., Joslyn, H. D., Hardin, L. W., and Wagner, J. H.: Turbine

Rotor-Stator Interaction. ASME J. Eng. for Power, Vol. I0_., pp. 729-742,

October 1982.

Caspar, J. E., Hobbs, D. E. and Davis, R. L.: Calculation of TwoDimensional Potential Cascade Flow using Finite Area Methods, AIAA

Journal, Vol. 18, No. I, January 1980, pp. 103-109.

Carter, J. E., Edwards, D. E. and W,erle, M. J.: Coordinate

Transformation for Laminar and TurbJlent Boundary Layers, AIAA Journal,

Vol. 20, No. 2, February 1982, pp. 282-284.

Edwards, D. E., Carter, J. E. and Werle, M. J.: Analysis of the Boundary

Layer Equations Including a Coordinate Transformation--The ABLE Code,

UTRC81-30, 1981.

Ii

|r

ii
k'_ _ qll'_% _=_ql,q_,'w,,,"-'mV

RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANP_LE (degr.)

TABLE 1a

AIRFOIL GEONETRY

AIRFOIL: FIRST STATOR (HUB)

PITCH (ins.): 6.88865

LEADING EDGE

0.44485

90.00395

31.79000

TRAILING EDGE

0.1O988

22.44246

6.85000

X(ins. ) YL (ins.) Yu(ins- )

! O.O00m9 5.98844 5.98844

2 0.05_32 5.16650 6.21038

0.11864 [.68598 6.29089

4 ,).17,96 5.63254 6.34433

0.2372_ 5.59498 _.38189

0.29660 5.56902 6.40786

" 0.35592 5.55114 G.42556

0.41524 5.53364 6.44182

9 0.47456 5.51555 6.45743

i0 0.53388 5.49688 6.47239

ii 0,59320 5.47760 6.48668

12 0.74150 5.42681 6.51919

13 0.88980 5.37219 e.54678

14 i 0381C 5.31366 _.56894

15 1.18640 5.25111 6.58508

16 1.33470 5.18440 6.59454

17 1.48300 5.11341 6.59667

18 1.63170 5.03800 6.59063

1_ 1.7796_ 4.95798 6.57559

_ 1.9279C 4.87318 6.55065

21 2.0762C 4.78]]9 6.51481

£_ 2.22450 4.68839 _.46704

2_ 2.3728C 4.58791 6.40627

24 2.52110 4.48160 6.33143

2_ 2.66940 4.36922 6.24143

26 2.81770 4.25033 6.13530

C7 2.96600 4.12450 6.01210

28 3.11430 3.99119 5.87111

29 3.26260 3.84973 5.71175

30 3.41090 ].69938 5.53366

31 3.55920 3.53930 5._3677

32 3.70750 3.36863 5.12118

?_ 3.8558(' 3.18656 4.88723

34 4.0041C 2.99229 4.635]4

_ 4.1524[ 2.78525 4.36603

3_ 4.30070 2.56517 4.07986

37 4.44900 2.33245 3.77749

_n _.&q73(, 2.08792 3.459_8

39 _.74560 1.83271 3.12684

40 4.89]t0 1,56797 2.78000

41 5.04220 1.29464 2.41981

42 5.1905C 1.01365 2 04697

41 5.33880 0.72592 1.66229

•;: 5.39812 0.60905 1.50524

_5 5.a5744 0.49120 1.34645

4f 5.51676 0.3724] 1.18595

47 5.57608 0.25271 1.02380

48 5.6354[ 0.13213 0.86004

4_ 5.69472 0.01077 0.69471

50 5.75404 -0.08624 0.52183

%1 5.81336 -0.I0952 0.35b17

5Z 5.87268 -0.09/55 0.18_66

53 5.93200 0.00001 0.00001

12

,.._ .'._a.-'r'.& " -
u -,._qp,sa-.,_-_,. ............

RADIUS (ins.)

METAL ANGLE (degr)

WEDGE ANGLE (degr)

TABLE ]b

AIRFDIL GEONETRY

AIRFOIL: FIRST STATOR (MIDSPAN)

PITCH (ins.): 7.71118

LEADING EDGE

O. 44484

90.00000

31,80000

X(ins. ) YL(ins. )

TRAILING EDGE

O. 10987

21.4ZOO0

6.84000

YO( ins. )

i O.O000C 6.80766 6.80756

2 0.U5932 6.44830 7.15365

3 0.11864 6.43405 7.17319

4 0.17796 6.41912 7.19210

0.2372_ 6.40354 7.21034

6 0.29660 6.38729 7.22791

0.35592 6.3703_ 7.24476

8 0.4152_ 6.35273 7.26089

U.47456 6.33441 7.27624

,C ".53388 6.31540 7.29080

!' 0.5932C' 6.29568 7.30453

1_ 0.7415C' 6.24325 7.33502

"3 0.88980 6.18623 7.35957

': 1.0331e 6.12447 7.37758

15 1.18640 6.05781 7.38835

16 i.]3470 5.98603 7.39114

_" 1.48300 5.90896 7.385]3

i_ 1.63136 5.82633 7.36940

":" !'_96_ 5.7378 _ 7.34300

20 1.92790 5.64326 7.30490

LL 2.07620 5.54212 7.25403

22 2.22450 5.43404 7.18927

2_ 2.37280 5.31852 7.10949

_', 2.52110 5.19498 7.01363

2_ 2.66940 5.06273 6.90066

26 2.81770 4.92096 6.76967

27 2.96600 4.76873 6.61989

28 3.11430 4.60490 6.45078

29 3.26260 4.42825 6.26202

30 3.41090 4.23771 6.05354

31 3.55920 4.03254 5.82550

32 3.70750 3.81279 5.57826

3 _ 3.85580 3.57948 5.31230

34 4.00410 3.33397 5.02816

35 4.15240 3.07798 4.72650

36 4.30070 2.81269 4.40803

3_ 4.44900 2.53937 4.07350

_c ,:.5073n 2.25873 3.72369

_9 4.74560 1.97172 3.35942

40 4.89390 1.67884 2.98147

41 5.04220 1.38062 2.59066

;2 5.19C5_ 1.07737 2.18773

4_ 5.33880 0.76951 1.77352

44 5.39812 0.64517 1.60482

45 5.45744 0.52020 1.43448

46 5.51676 0.39451 1.26252

47 5.57608 0.26816 1.08901

4_ 5.63510 0.14117 0.91397

49 5.69472 0.01364 0.73745

qO 5.75404 -0.11456 0.55950

ql 5.81336 -0.24329 0.38014

52 5.87268 -0.37263 0.19943

5_ 5.93200 0.00000 0.00000

13
ORIGINAL. PAGE Ig

OE K)OR QUALITY

RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANGLE (degr.)

TABLE ] c

AIRFOIL GEOMETRY

AIRFOIL: FIRST STATOR (TIP)

PITCH (ins.): 8.58371

LEADING EDGE

0.44487

90.0O401

31.79000

TRAILING EDGE

0.10986

0.25751

6 79000

!

2

3

4

'.;

i;

!3

14

15

16

L :

21

22

24

2:"

26

27

28

2Q

30

31

32

_4

3_

_6

3"7

39

4O

41

4 ?

43

44

45

46

47

49

5_

5'.

5_

53

X(ins. ) YL(ins. ) Yu(ins" )

O.COCOC

0.05932

0.11864

0.17796

0.23726

0.2966C

C.35592

0.41524

0.47¢56

0.53386

0.59_2"

8.741}"

0.88_,8[

i._381C

1.18640

1.3347C

1.4830C

-.63136

1,779&0

1.9279C

2.0762C

2.2245¢

2.3728C

2,52110

2.66940

2.81770

2.96600

3.11430

3.26260

3.41090

3,55920

].70750

3,85580

4,00410

4.1524C

4.]0070

4.44900

4.5q_30

4.74560

4.89390

5.04220

5.19_C

5.]3880

5.39812

5.45744

5,51676

5.$7608

5,63540

5.69472

5.75404

5.81336

5.87268

5.93200

7.35507

7 27456

7 22112

IC35_

7 15759

7 139_

7 12193

7.10338

7.08402

7.06383

7.00967

6.95010

6.88487

6.81377

6.73650

6.652"4

6.56207

6.46497

6.35817

6.24376

6.12004

5.98609

5.84072

5.68263

5.51023

5.32200

5.11693

4.89526

4.65850

4.40859

4.14741

3.87650

3.59714

3.31031

3.01688

2.71730

2.41223

2.10214

1.78726

1.46798

1.14458

0,8172]

0.68529

0.55272

0.41958

0.28587

0.15177

0.01698

-0.08620

-0,I0950

-0,09754

0.00001

_.5_702

7.7989 _

7.87949

7._3293

_.97749

7.99646

8.01409

8.02_8"

A.04449

8.05803

8.07044

8.09615

8.11406

8.12_74

8.12465

8.11627

8.09803

8.06935

8.029& c

7.97793

7.91381

7.83635

7.74477

7.63818

7.51_66

7.37624

7.21892

7.04264

6.84631

6.62883

6.]8910

6.12648

5.84072

5.53208

5.20125

4.84935

4.47775

4.98_C2

3.68183

3.26080

2.82654

2 _804 _

i 92403

l 7388 _

1 55219

1 36422

I 17502

0.98458

0,79299

0.60033

0.4066!

0,21192

0.00001
ORIGINAL PAGE 1:3

OF POOR QUALITY

RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANGLE (degr.)

TABLE 2u

AIRFOIL GEONETRY

AIRFOIL: FIRST ROTOR (HUB)

PITCH (ins.): 5.41251

LEADING EDGE

0.34867

39.56323

31.19000

TRAILING EDGE

0.19000

25.97078

5.31000

X(ins ) YL (ins.) VU (ins.)

" O.O000C 2.84604 2.86604

2 0.06341 2.66555 3.08102

3 0.12682 2.59706 ].21151

4 0.19C22 2.55545 3.33!8"

% ?.25364 2.53057 3.4434_

6 0.3170_ 2.518_I ].5472Z

_.38C4( 2._18q2 3.;44"-

9 0.4438- 2.53062 3.73464

z n.5_2f 2.5_5q ? t._ln<r,

i" 0.5706S 2.59558 3.89912

{_ O ._ "{4!_ 2.6 _74" 3.9738_

0.79262 2.73147 4.14166

_J 0.95115 2.81137 4.28528

14 1.1096" 2.87832 4.40_73

l_ 1.26820 2.93322 4.51126

16 1.42672 2.97676 4.59755

I" 1.58_25 3.00948 4.66_9_

i_ 1.74377 3.03180 4.72339

!9 1.9023C 3.04408 4._64--

2_ 2.06082 3.04653 4.7926 _

21 2.21935 3.03939 4.80757

22 2.37";87 3.02278 4.80981

Z3 2.5364[ 2.99681 4.79963

2< 2.69492 2.96157 4.77_15

?= 2.85345 2.91708 4.74242

2£ 3.01197 2.86339 4.6953_

2_ 3.17050 2.80050 4.63584

28 3.32902 2.72831 4.56359

_ 3.48755 2.64670 4.47823

30 3.6460_ 2.55547 4.37924

_i 3.80460 2.45445 4.26599

_2 3.96312 2.34348 4.13761

: 4.1_16., 2.2_34 3.99304

3; 4.2801 _ 2.09081 ].83080

{= 4.43870 1.94860 3.649¢.3

36 4.59722 1.795_5 3.44572

37 4.75575 1.63070 3.21968

';.91_2 _ 1,4=4n¢ 2.9_[ _

39 5.07280 1.26487 2.69996

40 5.23132 1.06245 2.40938

41 5.38985 0.84595 2.10143

42 5.5483" 0.61435 I.'_8_c

43 5.70690 0.36649 i._4378

:: 5.7703' C.26245 1.]068_

45 5.83372 0.i_541 1.16841

46 5.89713 0.04543 1.02861

47 5.96054 -0.06777 0.88753

';_ 6.62395 0.16117 0._4%2 _

4_ 6.087]a -0.19892 0 601Q4

%L. 6.15077 -0.20989 0.45759

_I 6.21418 -0.19908 0.112_

5, 6.27759 -0.16158 0 16621

53 6.34100 -0.01989 -0.01989

15

g
TABLE 2b

AIRFOIL GEOMETRY

AIRFOIL: FIRST ROTOR (MIDSPAN)

PITCH (ins): 6.05879

RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANGLE (degr.)

LEADING EDGE

O. 34 %72:

4Z. I£;646 3 I.. _4000

TRAILING EDGE

0.19000

ZS.Y7093

5.31000

.t'.

F., I"

P9

11

12

14

1-

16

]c

21

-"Z

t_

24

2_

25

2V

20

L9

]C

32

35

36

37

_P

J9

4O

41

,:2

4_

44

45

46

47

48

40

5O

5]

X(ins.)

_.00000

.06341

0.12682

0.19023

0.25364

0.31705

0.3804_

0.4438"

0.5n_2_

0.6341C

0.79262

0.95115

1.10967

1,2682C

1.42672

1.58525

1.74377

1.9029C

2.0608_

2.21935

2.37787

2.5364C

2.69492

2.85345

].01197

3.17050

3.32902

3.48755

3.64607

3.80460

3.96312

4.12165

4.28017

4.43870

4.59722

4.75575

4.91427

5.07280

5.23132

5.38985

5.5483"

5.70690

5.77031

5.83372

5.89713

5.96054

6.02395

6.0873_

6.15077

6.21418

6.27759

6.34100

YL(ins.

3.41970

3.21919

3.15069

3.10908

3.08419

3.07242

3.07243

3.08422

3,10q12

3.14694

3.18401

3.26583

3.33349

3.38822

3.43094

3.46228

3.48271

3.49248

3.49176

3.48053

3.45868

3.42596

3.38201

3.32633

3.25830

3.17735

3.08283

2.97433

2.85162

2.71488

2.56463

2.40136

2.22577

2.03852

1.84022

1.63139

1.41252

1.18402

0.94623

0.69955

0.44403

0.19008

-0.09214

-0.20337

-0.31578

-0.42949

-0.54448

-0.63800

-0.67575

-0.68673

-0.57591

-0.63841

-0.49672

16

) Yu( ins.)

3.41970

3.62774

3.74347

3.84906

3.94593

4.03518

4.11769

4.19414

4.26511

4.33106

4.39235

4.52752

4.63984

4.73220

4.80674

4.86506

4.90837

4.93760

495347

4.95652

4.94712

4.92555

4.89193

4.84632

4.78863

4.71868

4.63616

4.54063

4.43151

4.30799

4.16905

4.01334

3.83912

3.64406

3.42595

3.18387

2.91861

2.63221

2.32774

2.00932

1.67680

1.33571

0.9069q

0.8457J

0.70]59

0.56065

0.41698

0.27261

0.12765

-0.01791

-0.16397

-0.31052

-0.49672

!
ORIGINAL PAGE I8

OF POOI_ QUALITY

RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANGLE (degr.)

i

2

3

4

6,

8

Q

I0

!1

i:

14

15

16

17

I<.

t_

_x

22

2!

14

2'-

2_

27

28

?_

3C

7_

3=

_6

37

_e

39

4O

41

4 _

4%

4

45

46

4_

48

4_

5O

<I

r' t

TABLE 2c

AIRFOIL GEOMETRY

AIRFOIL: FIRST ROTOR (TIP)

PITCH (ins.): 6.70506

LEADING EDGE

0.34881

46.66805

31.26000

X( ins. )

O.O000C

0.06341

0.12682

0.19023

_.253_

0.31705

0.3£046

0.44387

0.50728

0.57069

0,6341C

0.79262

0.9511_

i.I0967

1.2682C

1.42672

1.58525

1.74377

1.90230

2.0608_

2.21935

2.]7787

2.53640

2.69492

2,8534_

].01197

].17050

3.32902

3.48755

3.64607

3.80466

3.96312

4.1216_

4,28017

4,4387C

4.59722

4,75575

4.91427

5.07280

5.23132

5.38985

_.54837

5.70690

5.77031

5,83372

5,89713

5,96054

6.02395

6,08736

6,15077

6.21418

6,27759

6.]4100

YL (ins. )

3.97348

3.77294

3.70443

3.66280

3.63790

3.62612

3.62611

3.63787

3.66275

3.69488

3.72462

3.78887

3.83974

3.87814

3.90472

3.91989

3.92388

3.91674

3.89838

3.86851

3.82665

3.77210

3.70385

3.62049

3.52015

3.40033

3.25903

3.09581

2.91352

2,71577

2.50562

2.28505

2.0558 _

1.81890

1.57520

I.]2521

1.06966

0.80884

0,54319

0.27306

-0.00136

-0,27975

-0,56201

-0.67597

-0,79046

-0.90562

-1.02119

-1.11481

-1.15257

-1.16355

-I,15274

-1,11524

-0.97355

tl

TRAILING EDGE

0.19000

25.96767

5.31000

YU (ins. )

3.97348

4.17548

4.27381

4.36353

4.44573

4.52127

4.59084

4.65499

4.71419

4.76883

4.81924

4.92848

5.01637

5.08539

5.13737

5.17369

5.19537

5.20321

5.19778

5.17950

5.14862

5.10529

5.04954

4.98122

4.90012

4.80585

4.69788

4.57543

4.4]757

4.28296

4.10990

].91608

3.69853

3.45544

3.18730

2.89675

2.58780

2,26420

1.92951

1.58629

1.23664

0.8820_

0.52368

0.37945

0.23478

0,08974

-0.05569

-0.20147

-0.34753

-0.49387

-0.64045

-0.78728

-0,97355
ORIGINAL PAGE IS

OE POOR QUALITY

RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANGLE (degr.)

4

8

,3

._

i.

l"

15

16

"C

2J

22

.%,

2"

2_

2:

_2

39

41

',:

4_

44

45

46

4:

48

4o

50

5_

ql

TABLE 30

AIRFOIL GEOMETRY

AIRFOIL:SECOND STATOR(HUB)

PITCH(ins.):5.41251

LEADING EDGE TRAILING EDGE

X( ins.

0.0900?

0.96452

0.12904

9.19356

?. t = __£

9. 32260

0.45164

0.5806F

0.80650

0.96_80

1.1291C

1.29040

1.45170

1.61300

1.77430

t.99<_ _

2.0969_

2.2582 q

2.41959

2.5808:

_._421 _

2.9_34 _

3.06473

3.22600

_38739

3.5486_

3._999]

3.8_120

4.:938[,

4. 3551_

4.51649

4.67770

4.83900

5.16160

5.32290

5.48420

5 64_5_

5._0680

5.87132

5.9]584

6.000]6

6.06488

6.12940

6.19392

6,25844

6.32296

6.38748

6.15200

0.34999

41.01068

29.91000

YL (ins. )

3.68263

3.48015

3.41120

3.36955

3.34493

3.33372

3.34773

3.41583

?.4_'39

3.55269

3.63560

3.70599

3.76376

3.80880

3.84106

3.86048

3.86072

3.84153

3.80950

3.76468

3.70714

3.63698

3.55430

3.45921

3.35188

3.23245

3.10111

2.95802

2.80339

2.63745

2.460]7

2.27244

2.07384

1.86483

1.645_ n

1.41563

1.17789

0.92975

0.67246

0.40629

0.29738

0.18710

0.07548

-0,03748

-0.13608

-0.1_738

-0.18997

-0.17996

-0.14267

0.00000

YU (ins.

; B%4"2

4.0186Q

4.244::

4.;4;'2

4. ":,:C*

4.94589

5.09C,_?

5.31424

5.39634

<.46037

5.50735

F._Sa_

5.55317

5.55319

5.53852

5.5094F

5.46629

5.4090£

5.33790

5.25273

5.15348

5.03995

4.91189

4.76892

4.61058

4.4362_

4.2452,

4.03662

3.80928

3.56222

3.00662

2.69784

2.]6890

2.02068

1.65431

1.50296

1.34900

1.19252

1.03361

0.87238

0.70890

0.54327

0.]756_

0.20595

0.00000

0.19000

4.98619

8.91000

18
TABLE 3b

AIRFOIL GEOMETRY

AIRFOIL: SECOND STATOR (MIDSPAN)

PITCH (ins.): 6,05879

.j

RADIUS (ins.)

METAL ANGLE (degr)

WEDGE ANGLE (degr) i23489

10

12

14

15

16

17

18

19

21

22

23

24

25

26

27

28

29

30

31

32

3_

34

35

36

37

39

aC

41

42

43

44

45

464 z

48

49

50

51

5£

53

X(ins.

0.00000

0.06452

0.12904

0.19356

0.25808

0.32260

0.38712

0.45164

0.51616

0.58068

0.6452$

0.80650

0.96780

1.12910

1.29040

1.45170

1.61300

1.77430

1.93560

2.0969G

2.25820

2.41950

2.58080

2.74210

2.90340

3.06470

3.22600

3.38730

3.54860

3.70990

3.87120

4.03250

4.19380

4.35510

4.51640

4.67770

4.83900

5.000_0

5.16160

5.32290

5.48420

_._4_

5.80680

5.87132

5.93584

6.000]6

6.06488

6.12940

6.19392

6.25844

6. 32296

6. 38748

6.45200

LEADING EDGE

0.34999

45.668OO

2.7.50000

YL( ins.)

4.10291

3.47786

3.52885

3.57793

3.62510

3.67035

3.7!3_F

3.7550@

3.79454

3.83206

3.86762

3.94796

4.01599

4.07162

4.11482

4.14552

4.16371

4.16934

4.16244

4.14298

4.11101

4.06655

4.00965

3.94037

3.85879

3.76498

3.65906

3.54111

3.41127

3.26967

3.11644

2.95172

2.77568

2.58849

2.39030

2.18130

1.96166

1._31_0

1.49128

1.24090

0.98064

0.71074

0.43141

0.31707

0.20126

0.C8400

-0.b3471

-0.15484

-0.27639

-0.39934

-0.52]68

-0.649]9

0.00000

19

TRAILING EDGE

0.19000

Z'5.00000

6.50000

Yu(ins.)

4.10;91

4.30650

4.40610

4.50013

4.58895

4.67285

4.95210

4.82695

4.89760

4.96425

5.0270_

5.16834

5.28865

5.38963

5.47259

5.53859

5.58849

5.62296

5.64258

5.64778

5.63888

5.61615

5.57973

5.52972

5.46611

5.38882

5.29771

5.19255

5.07300

4.93863

4.78891

4.62316

4.44053

4.24001

4.02052

3.78134

3.52218

3.24330

2.94535

2.62941

2.29682

1.94914

1.58790

1.4399_

1.29018

1.13867

0.98552

0.83080

0.67459

0.51699

0.35805

0.19786

0.00000

¢,

f

.4.,'
RADIUS (ins.)

METAL ANGLE (degr.)

WEDGE ANGLE (degr.)

1

2

3

4

6

10

12

13

15

16

17

18

?z

22

2_

24

26

2-

28

29

30

31

32

33

3,:

35

36

37

_o

39

4O

41

4:

43

44

45

46

47

48

4Q

_C

51

TABLE 3c

AIRFOIL GEOMETRY

AIRFOIL:SECONDSTATOR _IP)

PITCH(ins.):6.70506

LEADING EDGE

0.35006

50.49115

25.12000

x( ins. )

O. 0009C

O. 06452

O. 12904

O. 19356

?.2[-80._

0. 3226C

C, 38'12

O, 45164

O, 51616

O. 58068

O, 6452C

O. 8965C'

O. 96780

i. 12910

i. 29040

1.4517U

1.61300

i. 77430

1,93560

2. 0969C

2. 25820

2. 4195C

2. 5808C

2. 74210

2.9034C

3.06470

3. 2260C

3. 38730

3. 5486C

3. 7099C

3.8712C

4. 03250

4. 1938C

4. 35510

4. 51640

4. 67770

4. 83900

5. 0003,'

5. 16160

5. 32290

5. 48420

5.64-_5C

5. 80680

5.87132

5. 93584

6. 00036

6. 06488

6. 12940

6. 19392

6. 25844

6. 32296

6. 3874F

6. 45200

YL (ins. )

4 53429

4 33178

4 26282

4 22116

4 19652.

4 18530

4 18619

4 19929

4 22602

4 25762

4 28729

4.35297

4.40647

4.44777

4.47683

4.49364

4.49819

4.49045

4.47047

4.43822

4.39375

4.33706

4.26823

4.18728

4.09426

3.98924

3.87229

3.74348

3.60289

3.45062

3.28675

3.11139

2.92465

2.72666

2._1749

2.29731

2.06620

1.8242_

1.57187

1.30889

1.03553

0.75199

0.45841

0.33818

0.21639

0.09]02

-0.03190

-0.13607

-0.17738

-0.18996

-0.17995

-0.14267

0.00000

Yu (

20

TRAILING EDGE

0.1gO00

24.98778

4.09060

ins. )

4.53429

4.73679

4.81836

4.89463

4.96641

5.03396

5.09751

5.15728

5.21343

5.26613

5.31552

5.42538

5.51708

5.59]99

5.65117

5.69551

5.72567

5.7421§

5.74550

5.73590

5.71360

5.67874

5.63135

5.57140

5.49876

5.41323

5.31449

5.20215

5.07566

4.93435

4.77738

4.60366

4.41196

4.20118

].97077

3.72077

3.45177

3.1649 c

2.86176

2.54389

2.21304

1.87091

1.51902

1.37585

1.23140

1.08577

0.93902

0.79122

0.64244

0.49272

0.34214

0.19073

0.00000

,._..._- • . • . • . .,
TABLE 4

FLOWPATH STATIC PRES3URES AT,, 1ST STATOR EXIT (STA. 2)

RUN/PT

1311

31/2

79/1

83/3

12/1

30/3

80t4

8212

1411

32/2

81/2

81/7

0.08

8.78

8.98

Cps = (PTo - P) / QUm

GRID

IN/OUT XIBx HUB RERN = OUTER CRSING

O:)T 8.15 4.386 3.588 3.874

IN 8.15 4.927 4.225 3.722

OUT 8.58 4.186 3.395 2,887

IN 8.58 5.848 4.270 3.720

OUT 8.15 5.616 4.680 4.810

IN 6.15 6.518 5.599 4.942

OUT 0.58 5.414 4.477 3.886

IN 8.58 6.589 5.592 4.879

OUT 8.15 8.S95 7.261 6.235

IN 6.15 9.826 8.468 7.497

OUT 8.58 8.129 6.736 5.739

IN 8.58 9.892 8.422 7.370

. Calculzted from a free vorte_ distribution between the leasured hub and

outer casing flowpath static pressures (pitch and annulus averages).

=.

.-.I

= 21
TABLE 5

FLOWPATH STATIC PRESSURES AT ROTOR EXIT (STA. 3)

CPs = (PTo - P) / QUm

GRID

RUNIPT _) IN/OUT XIRx HUB MERN * OUTER CASING

8.G8 13/I OUT 0.15 5.271 5.308 5.334

31/2 IN 8.15 G.024 5.984 5,956

79/I OUT 8.58 5.042 5.861 5.075

83/3 IN 8.58 5,951 5.971 5.982

12/1 8.78 OUT 8.15 B.729 G.709 B.G94

38/3 IN 0.15 7.832 7.709 7.G21

88/4 OUT 8.50 6.535 6.509 G.490

82/2 IN 0.50 7.G38 7.G05 7.G32

14/1 0.G OUT 8.15 9,751 9.791 9.819

3212 IN 0.15 11.491 11.245 II.OG3

81/2 OUT 0.50 9.514 9.352 9.23G

81/? IN 0.50 11.286 11.108 10.930

e Calculated from a free vortex Distribution between the measured hub and

outer caslng flowpath static pressures (pltch and aqnulus averages).

22
TABLE 6

FLOWPATH STATIC PRESSURES AT 2ND STATOR EXIT (STA. 4)

CPs = (PTo - P) / OUm

GRID

RUN/PT _ IN/OUT X/Bx HUB MEQN I

13/I B.B8 OUT 8.15 5.405 5.3?7 5.35?

31/2 IN 8.15 G.Bal 5.991 5.955

96/4 OUT 8.58 7.606 7.009 6.582

90/2 IN 9.58 8.717 8_079 7.623

12/I 6.78 OUT 8.15 G.871 G.777 6.710

30/3 IN 8.15 7.807 7.724 7.684

87/i OUT 8.59 9.690 8.924 S.377

89/2 IN 8.50 ii.133 10.311 9.?22

14/I 8.96 OUT 8.15 I0.258 10.017 9.84E

32/2 IN 0.15 11.458 11.227 11.OGl

88/I OUT 8.50 14.157 12.942 12.074

88/3 IN 0.50 16.207 14.914 t4.828

OUTER CQSING

m Calculated from a free vortex _istrlbutlon between the measured hub and

outer casing flowpath static pressures (pltch and annulus averages).

23 r

.I
oRIGIN,_I; pAGE IS

OF pOOR QUALITY

TABLE 7a

TURBINE STAGE M,tDSPAN PRESSURE DISTRIBUTIONS

$ = 068

5TATOR- 1

CPT1 0.000

C_32 3.5r_

SUCT ]01_ gURFACE

gIST CP3

O.OIZ 1._5

0.070 Z.ZI5

O.ZSl _1.731

O. 426 5.275

0.554 B.O1B

0.651 4.65_

0.734 4.236

O. _.'07 4. OE:'

0,_79 3.9c,:

0.945 3.349

1.000 3.578

Pi_ ,._UPJE SURFACE

g; 57 CPS

0.005 O.O_q

0.01.7 0.10_

0.0_, 0.21_

0,251 0.233

0.423 0._ ,'P4

0,5_4 0.436

O. :,_.7 0.79;

0.7_ _ I • 3"_,2

0.$$c 2.2Z8

0.9¢,7 3.643

BA_E PRE _,SURE

D:_T CPS

0.990 3.75r,,

ROTOR-1

CFTR2 2.5_"

CP3 3 ¢ • "--_7

SLICTI ON SdRF ACE

D: 37 CPS

O.OO-_ 4.53_:

0.0.' I 4.893

0. _'z7 B.770

0,_: 6.311

0. _-,';; 6. 370

O. 57_ 6. 450

0_';_ 6.3e5

O. 7_'3 5.912

0.8c$ 5.73;,

O.?3T B.630

1.003 5.5,33

D] ST CF3

O.01Z 2.65,_

0.049 :P.791

0.039 1.975

0. ;,48 2.757

O. 42¢, 2. 723

0.570 2.1_3

o.67e 3.13e

0.775 3.$6_

0.863 4.2ai

0.9_: B._I5

BASE PRE cSS_:E

D:¢T CF--

O. 935 5.570

AXIAL GAP 15%

GRID OUT

CP = (PTO - P)! 112pUre 2

= 078 ¢ = 096

STATOIR- 1 STATOR- 1

0.000 .000

_TION LIRFkQ[ $UCT!OI,,i SURFACE

gIST '2PS ClST CF'E

0.070 0.012 i."Bg_ O.O:Z 0.070 3.3k>g 4.4¢5

0.Z51 4.8_;7 O.Z_I 7.507

0.426 6.Q41 0.4_6 10._.._

O. 5_4 &._19 0.554 10.0_7

O. e,._l 6.0¢! 0.¢,51 9.3;.2

0.734 5.589 0.734 B._BC

0.809 5.303 0.809 l.l_4

0.879 6.11G 0.879 T.(k>_

0.945 4.318 0.945 6.666

1.00_ 4.8_3 1.000 7.429

Pr<ESSUR_. SURFACE Iq_SSUk"E SL_FACE

DIST CPS DIST CPS

0,005 O, 103 0,005 O, !29

0.027 0.130 0.027 O.ZC7

0.0o6 0.285 O. Oct> 0.437

0.25: 0.292 O.Z_I 0.477

0.423 O. 3_';' 0.423 0.598

0.5o4 0.56,8 0.564 0.875

0.6_7 l .046 0.667 1.563

0.7E9 1.79_. 0.789 Z.771

0.880 Z.917 0. £'8o 4.45_

O. 967 4.73_ O. 9(>7 7.284

_AS£ PRESSURE BASE _RE

O!_l CPS giST CF3

C.990 4._._Z ,990 7.217

24
TABLE 7b

ORIGINAL PAGE IS

OE POOR QUALI'I_

"4

Ir

TURBINE STAGE MIDSPAN PRESSURE DISTRIBUTIONS

AXIAL GAP: 15°/#

GRID IN

CP -(PTO- P)/112p Um2

+=068

STATORl

CPT1 0.708

CPS2 4.ZZ5

SUCT IOml _RFACE

DI ST CPS

O.OIZ Z.3_

0.070 Z.891

O.ZSI 4.337

O. 426 5.778

0.554 5.574

0.651 5.Z57

0.734 4.900

0.809 4.711

O. 879 4,595

O. 945 3.997

1.000 4.407

PRESSURE SURFACE

DIST CPS

0.005 0.79Z

0.027 0.801

O. 0¢.6 O. 933

O. Z51 0.946

0.4Z31 .OO5

0.5_A 1.143

0.687 1.479

0.789 Z.069

0.886 Z. 8<)2

O. 967 _. 35Z

BASE PRESSURE

DI3T CPS

0.990 4.ZZ8

ROTOR-I

CPTRZ 3.447

CPS3 5.9,04

SUCTION SURFACE

DIST CPS

0.005 5.34Z

0.011 5.5Z9

0.117 6.436

0.Z69 7.1ZZ

0.437 7.15Z

0.578 7.Z06

0.695 7.145

0.7;_3 6,678

0.863 6.5OO

0.937 6.459

1.003 6.376

P_ESSURE SURFACE

DIST CP'S

O.O1Z 3.495

O. O49 3.7ZZ

0.089 3.8_9

0.248 3.645

0.426 3.593

0.570 3.786

0.678 4.039

0.775 4.441

0.868 5.068

0.95Z 6.335

i_SE PRESSURE

DIST CPS

0._8_ 6.3_

+ =0.78

ST ATOR1

CPTL 0.934

CPS2 5.599

SLK;TION SURFACE DIST CPS

O.OIZ 3. 190

0.070 3. 823

0.Z51 5.7Z3

0.426 7.678

0.554 7.426

0.651 6.937

0.734 6.596

0.009 6.237

0.879 6.056

0.945 5.276

1.000 5.88Z

PRESSURE SURFACE

DIST CPS

0.005 1.035

O.OZ7 1.066

0.0661 .Z24

O.ZSI1 .ZSl

O. 423 1. 334

0.564 1.509

0.687 1.97Z

O. 78_ 2.724

0.886 3.826

0.967 5.735

BASLEPRESSURE

DIST

0.990 5.638

/t= 096

$TATOR-I

CPTI 1.403

CPSZ 8.468

SUCTION SURFACE

DIST CPS

O.01Z 4.749

0.070 5.791

O.Z51 8.6¢,1

0,4Z6 1i.6.07

0.5_4 11.143

0.651 10.4_3

0.734 9.EP34

0.800 9.41_

0.079 9.123

0.945 7.930

1.000 8.744

ROTOR-t

CPTRZ 4.279

CPS3 7,709

SUCTION SURFACE

PRESSLRE SURFACE

DIST CP3

0.005 1.575

0.027 1.629

0.0¢6 1.8o2

O.ZSI 1.871

0.4Z3 Z.O00

0.564 Z.Z74

0.687 Z.969

0.789 4.113

0.886 5.817

0.967 8.712

BASE PRESSURE

DIST CP3

0. 990 8. 489

ROTO_-I

CPTRZ 5.778

CPS3 11.245

SI.KTION SURFACE

DIST CPS

O.OOIJ 7.839

0.011 7.986

0.117 8.795

0. Z69 9. 362

0.437 9. 123

O. 578 9. Z89

0.695 9.099

O. 786 8. 528

0.863 0.469

0.937 8. 188

1.003 8. 159

I_[SSIJ_ SURFJK_E

DI ST CPS

0.005 14.921

0.01l 13.4o3

O. 117 14.008

0.269 14.0£_

0.437 13o388

0.578 13.437

0.695 13.1Z8

O. 78_ 17.460

0.863 IL.Z41

0.937 IZ.Ob3

1.003 11.836

PRESSURE SURFACE

DIST C1PS

0.012 4.651

0.O49 4.402

0.049 4.663

0.Z48 4.46,1

0.4Z6 4.461

0.570 4.641

0.678 5.069

0. 775 5.579

0.84,11 6. 452

0.952 8. 145

8_SE PRES_R[

DIST CPS

0.91_ 8.Z17

DIST CPS

O.OlZ 7.499

0.0,49 5.779

0.089 6.1Z3

0.Z48 6.031

0.426 6.0P36

0.570 6.327

0.678 6.875

0.775 7.709

0.868 9.074

0.95Z 11._3

0.9015 IZ.O0_

25

=,

4
•

!

TABLE 8=.

TURBINE STAGE MIDSPAN PRESSURE DISTRIBUTIONS

AXIAL GAP: 50%

GRID OUT

CP-(PTO- P)/1/2p Urn2

_=068

STATOR1

CPTI 0.000

CPSZ 3. 395

SUCTION SUI_ACE

DI3T CPS

O.OIZ 1.617

0.070 Z. 156

0,251 3.557

0.426 5.043

0.554 4.848

0.o51 4.507

0,734 4. 170

0.809 3.943

0.879 3.816

O. 945 3. 639

1.000 3.6Z4

PRESSURE SURFACE

DIST CPS

O. 005 O. 086

0.027 0,084

O. 066 O. 19Z

O.ZSI O.ZZZ

0.423 O.ZO0

0.564 0.429

0.(>87 0.777

0.789 1.347

0.8_ Z. 166

0.967 3.49Z

BASE PRESSURE

DIST CPS

0.990 3.456

ROTOR1

CPTRZ Z. 585

CPS3 5,061

SUCTION SURFACE

DI ST CPS

0.00_ 4. b'5_Z

0.011 4.Z67

0.117 5.ZSZ

O. Z69 5.906

0.437 5.946

0.578 4.031

0.495 5.9O2

O. 78_ 5.497

O. %_)3 5.319

0.937 5.321 ! .003 5.Z14

mESSURE SURFACE

DIST CPS

O.OlZ Z.648

O. 049Z• 744

O. Oe9 Z._O

O. Z411Z• 707

O. 4Z4Z• 7Z4

0,,570 Z.841

O. 6711 3.003

O, 775 3.355

O. 86_ 3.7Z4

O. 95Z 5.063

BASE DIST I_E_

o.!qm 5.0_9

= 078

STATOR1

CPTI 0.000

CP_ 4. 477

SUCTION SURFACE

DIST CP$

O.OIZ Z.l17

O. 070 Z. 859

O.ZSl 4.705

O. 4Z6 6.731

0.554 6.4Z3

0.651 5.953

O. 734 5.532

0.809 5.Z16

O. 879 5.031

O. 945 4,808

1.000 4.705

PRESSURE SURFACE

DIST CP5

0,005 0.111

0.0,?.7 O. 108

O. 066 O. Z54

O. Z51 O. Z9Z

0.4Z3 0.374

0.564 0.563

0.687 1.019

O. 7891• 779

0.886 _,Bo4

0.967 4.650

BASE PRESSURE

I_ZST CPS

0.990 4.535

ROTOR-!

CPTRZ 3. 184

CPS3 6.5O9

0.005 6.477

0.011 6.507

0.117 7.Zll

O. Z69 7.903

O. 437 7,7ZZ

O. 578 7. 754

0.695 7.591

0.78_ 7.017

O. 863 6.9Z5

O. 937 6, g89

I. 003 6. 746

Iq_SlmE SU_ACE

DIST CPS

O.OIZ 3.579

0.049 3.Z31

o.o89 3.411

O.Z4e 3.Z67

0.4Z4 3.360

0.570 3.501

0.67t 3.681

0.77_ 4.Z16

0.8¢44 .e3o

U.95_ 4,569

IAM' I'qlIS$1RE

DIST CPS

0.986 6.636

/p= 0,96

STATOR1

CPTI 0.000

CPSZ 6. 736

SUCTION SURI_ iCE

DIST CPS

O.OlZ 3.Z15

O. 070 4.3?.8

0.251 7.115

0.426 lO. llZ

O. 554 9.7Z6

O. 651 8. 960

0.734 8.Z76

O. 809 7. 856

0.879 7.604

O. 945 7. Z32

1.000 7,173

PRESSURE SURFACE DI ST CPS

0.005 0.180

0.0:_7 O. 159

0.066 0.381

O.D31 0.435

0.423 0.565

0.564 0.843

O. 687 1. 536

0.789 Z.678

0.8_64 .Z98

0.947 6.971

BAS,E PRESSURE

D1ST CPS

0.99O 6.8_Z

ROTORI

CPTRZ 4.1 O0

CPS3 9. 352

SUCTION SURFACE

DlSr CPS

0.005 1Z.8_57

0.011 11.87.8

0,117 11,744

O. Z69 11.82")

O. 437 I I. ZSg

0.578 11,146

0.695 10.800

O. 78'3 10.Z78

0.863 10.001

O. 937 9,882

1,003 9.7Z2

PRES3U_ SU_ACE

DIST C:PS

O.OIZ 5.97_.

0.049 4.141

O. 089 4. 342

0.Z484 ,ZBO

O. 424 4. 463

0.570 4.662

0.678 5.06Z

0.775 5.9Z7

0.868 6.900

O. 9"A2 9.436

iA_ I_ SSU_

DIST CP'S

0.988 9.591

26

/

:3b,- -w_"
TABLE 8b OR/'C'/NAL PACE /8

OF POOi_ QUALITF

TURBINE STAGE MIDSPAN PRESSURE DISTRIBUTIONS

AXIAL GAP: 50%

GRID IN

CP- (PTC - P)/1/2 p Um2

+-068

STATOR- 1

CPTI 0.717

CPSZ 4. Z70

SUCTION SURFACE

DIST CPS

0.012 2.346

0.070 2.940

0.2'51 4.379

0.4Z6 5.977

0.554 5.745

0.651 5.345

0.734 5.11o

0.809 4 • 878

0.879 4.713

0. 945 4. 549

1.000 4.554

PRESSURE SURFACE

DIST CPS

0.005 0.797

0.027 C.799

0.O66 0.911

0.251 0.946

0.423 1.0013

0.564 1.160

0.687 1.520

0.789 2.105

0.886 2.990

0.967 4.438

BASE PI_SSUI_

DIST

0.99O 4.338

+ =078

STATOR- !

CPTI 0.934

CPSZ 5.592

SUCTION SURFACE

DIST CPS

0.012 3.105

0.070 3.890

0.251 5.819

0.426 7.921

0.554 7.569

0.651 7.054

0.734 6.711

0.809 6.408

0.879 6.230

O.945 6. 002

1.000 6.013

ROTOR-I

CPTR2 3.386

CPS3 5.964

0.005 5.203

0.011 5.272

0.117 6.240

0.269 6.8_5

0.437 6.837

0.578 6.981

0.69_ 6.83_

O. 78"J 6.356

0.863 6.Z25

0.937 6.174

1.003 6.178

PRESSURE SLI_ACE

PRESSURE SURFACE

DIST CPS

0.0OS 1.06o

0.027 1.060

0.066 1.214

0.251 1.240

0.423 1.329

0.5<54 1.532

0.687 2.011

0. 789 Z .SK)I

0.866 3.893

0.907 5.875

BAS£ PR[SSUI_

DIST QDS

0.990 5.721

ROTOR- I

CPTRZ 4.1Z8

CPS3 7.685

SUCTION SURFACE

D1ST CPS

0.005 7.971

0.011 7.6,84

0_117 8.700

0.269 9.157

0.437 8.9_

0.578 9.009

0.69_ 8.715

0.7115 8.311

0.863 7.91i

0.937 8.o98

1.003 7.831

M_SSIJSE SURFAOE

DIST CPS

0.012 3.401

0,049 3.4417

O.Oe9 3._15

0.2411 3.474

0.4Z6 3.531

0.678 3.7?3

0,775 4.158

0. _5_'

IMSE PRESStRE

DIST

0.91_ 6.017

DIST QI_

0.012 4.(hS4

0.0,49 4.194

0.069 4.392

0.2441 4.311

0.4Z4 4.31S

0.570 4.516

0.6TI 4.710

0. 775 5.282

0. IMdl 5.9e7

0.9_2 7.97.2

IMSE PRESSURE

DIST CPS

O.9816 7.894

+,, 0.96

STATOR- I

CPTI 1.418

CPS2 8. 422

SUCTION SUlW ACE

DIST CFS

O.OIZ 4.755

0.070 5.892

0.251 8.695

O. 42o 11.8'52

0.554 11.314

0.651 10.678

0.734 10.134

0.809 9.679

0.879 9.'_a3

0.945 9.080

1.000 9,051

PRESSURE SURFACE

DIST CPS

0.005 1.5_7

0.027 1.593

0.066 I .813

0.251 1.886

0.423 1.991

0.564 2.310

0.687 2.997

0.789 4. Z0_

0.886 5.v38

0.967 8.873

BASE PRESSURE

DIST CPS

0.990 8.591

ROTO_- I

CPTRZ 5.710

CPS3 11.194

SUCTION SURFACE

DIS7 CPS

0.005 15. 107

0.011 13.042

0.117 13.722

0.269 13.92c

0.437 13.121

0.578 IZ.949

0.695_ 12.685

0.785 12.06o

0.863 I ! .836

0.937 11.670

1.003 I 1.603

PRESSURE SURf ACE

DIST CPS

O.Old 7.767

0.049 5.712

0. 089 5.946

0.248 5.8_4

0. 426 6. 002

0.570 6.Z65

0.678 6.6Z0

0.775 7.532

0.8d41 8.63_

0.952 II._88

0.9_ !1.517

27
TABLE 9a

STATOR-2 MIDSPAN PRESSURE DISTRIBUTIONS

AXIAL GAP: 50°/o

GRID OUT

CP =(PTO - P)/1/2 p Um2

_t=O 68

STATOR-2

CPT3 4.551

CPS4 7. O09

SUCTION SURFACE

_=078

STATOR-Z

CPT3 5.570

CPS4 8.924

SUCTION SURFACE

DIST CPS

0. 000 5.39Z

0.0:'2 5.096

0.135 6.106

O.ZC)| 7.4Z8

0. 459 8.004

0.598 8. ]60

0.704 8. 144

0.791 7.894

0.8(,8 7.670

O. 933 7.6Z9

0.995 7,587

PRE$_IRE SURF&CE

DI ST CPS

0.000 7.479

0.022 6.796

0.135 8.110

0.291 9.658

O, 459 1O, 176

0.598 10.385

0.704 10.428

0.791 10.115

0.868 9.807

O. 933 9. 706

0.995 9.681

PRESSURE ,_ACE

DI_,T CPS

0.023 4.602

O. 107 4.9_6

0.Z65 4.747

O. 4_5 4. 750

0.564 4.861

0.b79 5.117

0.777 5.551

0.865 6.13Z

0.946 7. 192

BASE PRESSUR_

DJST CP_

0.9596 7.271

DIST CPS

0.023 6.019

0.107 6.146

0.Z65 5.870

0.425 5.83Z

0.564 5.983

0.679 6.341

0.777 6.901

0.865 7.706

0.946 9.128

BASE PIqESSI.JRE

DIST CPS

0.9516 9.29"Z

=0.96

STATOR-2

CPT3 7.700

CPS4 12.942

SUCTION SURFACE

DIST CPS

0.000 IZ.329

0.022 11.687

0.13_ IZ.670

0.291 14,41_

0.459 14.932

0.59¢ 15.217

0.7O4 15.258

0.791 14.705

0.868 14.303

0.933 14.091

0.995 14.065

PRESSURE SURFACE

DIST

0.023 9.708

0.107 8.424

0.265 8.117

0.425 0.070

0.564 8.423

0.679 9.028

0,777 9,989

o.e65 I1.Z53

0.946 13.418

BASE PRESSUmE

DIST CPS

0.906 13.535

28
ORIGINAL PAGE IS

OF POOl{ QU.kLrTy

TABLE 9b

STATOR2

MIDSPAN PRESSURE DISTRIBUTIONS

AXIAL GAP: 50%

GRID IN

CP- (PTO- P)/112p Urn2

_=068

STATOR-_..

CPT3 5.483

CPS4 8.079

SUCTION SURFACE

I)]ST CPS

O. 000 6. 380

O. OZZ 6.099

0.135 7.167

0.Z91 8.51Z

0.4_9 9. 107

0.5_ 9.273

0.704 9.Z97

O. 791 9.01Z

0.868 8.785

O. 933 8. 695

0.995 8.691

PRESSURE SURFACE

DIST CPS

0.023 5.601

0.107 5.901

O. Z65 5.67Z

O. 415 5.7O0

0.564 5.810

0. 679 6. 078

O. 777• 500

0.865 _. 170

O. 946 8.30I

BASE PR_SSUIRE

D/ST CF'S

O._M 8.3211

STATOR-Z

CPT3 6.801

CPS4 10.311

SUCTION SURFACE

DIST

0.000 8.669

O.OZZ II.Z37

0.13_ 9.477

0.191 11.113

0.459 11.64B9

O. 598 11.944

0,704 11,910

0.791 11.57B

O. 868! 1.165

0.933 11.170

0.995 !1,061

PRESSURE SURFACE

D/ST CPS

O.OZ3 7.Z88

0.107 7.344

0.Z65 7.0¢_9

0.4Z5 7.074

0.564 7.L:_O 0 • 679 7.633

0.777 8.219

0.865 9.076

0.946 10.551

BASE RqESSURE

D/ST CPS

0.91_ 10.679

_=096

STATOIR-Z

CPT3 9. 560

CPS4 14.914

SIJCT_ON SURFACE

O/ST CPS

0.000 14.162

O. OZZ 13.4O8

0.13_ 14.706

o.zgl 16.57E

O, 459 17. Z06

0.598 17.370

0.f34 17.341

0.791 16.716

0.868 l<>.Z_

0.933 15.980

0.99_ 16,003

PRESS_E SU_QE

DIST CPS

0.013 11.83_

0.107 10.193

O. Z65 9.8<_9

0.4_ 9. 945

0.564 10.158

0.679 10.8G8

0.777 11 ._t9

0.865 13.2:67

0.946 15.433 D! ST CPS

0.986 15.400

f
-IIM_ _ ," - - . ._ ,m_ _ _-.r, .... _ ......

TABLE lOa

DEFINITION OF AVERAGE TOTAL, PERIODIC, AND

RANDOM UNSTEADINESS

FLD¥

SPEED

_(t) ._ KthREV

4,0 v It)

0 T

m m m

UT " Up + Ue

3O
TABLE lOb

PITCH AVERAGED UNSTEADINESS RESULTS AT Cx/Um = 0.68

1st STATOR EXIT

TOTAL V_ T RANDOM v_ R PERIODIC v_p

• GRID OUT 0.024 0.018 0.014

• GRID IN 0.034 0.030 0.014

ROTOR EXIT

• GRID OUT 0.155 0.i15 0.101

• GRID IN 0.154 0.132 0.078

2nd STATOR EXIT

• GRID OUT 0.057 0,054 0,017

• GRID IN 0.058 0.056 0.016

]1
TABLE 10c

PITCH AVERAGED UNSTEADINESS RESULTS AT Cx/Um = 0.78

1St STATOR EXIT

TOTAL _T RANDOM V_R PERIODIC V_p

• GRID OUT 0.030 0.022 0 019

• GRID IN 0.036 0.031 0.017

ROTOR EXIT

• GRID OUT 0.155 0.120 0.096

• GRID IN 0.155 0.137 0.069

2ncl STATOR EXIT

• GRID OUT 0.061 0.058 0.020

• GRID IN 0.061 0.058 0.017

32

.,_ .: '5,.-=_-_---
• °

TABLE lOd

PITCH AVERAGED UNSTEADINESS RESULTS AT Cx/Um = 0.96

1St STATOR EXIT

TOTAL _T RANDOM V_ R PERIODIC _;

• GRID OUT 0.028 O018 0.020

• GRID IN 0,037 0.030 0020

ROTOR EXIT

• GRID OUT 0.159 0.123 0,098

• GRID IN 0.169 0.146 0.084

2nd STATOR EXIT

• GRID OUT 0.071 0.066 0.026

• GRID IN 0.073 0.068 0.025

33
IF o

STATOR

FIG. 1

RDTAT|ON

ROTOR

TURBINE STAGE AT ]SX AXIAL GAP

3z_
-i

-'i

Z

o

o-

_8

..J

).-

,(

Iqt

CO

E

_o

_r

2...2.2

E Fty /I////

//0 /_

E

E

oC--

v o 0 o

c

"_000

£

c_o

&

_ g _ e_

Z

I1:

w

Z

LJ

"!"

LI

It) Z

1,3 '(

C3 t--

_J C3

C3 a,,

Z

Z UJ

LJ _J

14.1 ,_

I-- I-;

t/t

14J _J

t.- L3

n_

Z

...J

.I, ,"

i 35
FIRST STATOR

PRESSURE DISTRIBUTION

X/Ox : 8.X5, GRID IN, Cx/Um : 8.78

_o QOOO a

0,0090 --

O. OOgQ --

•. 4004) _

ilo 2000 _

O.OIOO

-0. IIHle .

,.4.4OOO _

-4.0000 _

•.(1. _lN14 .

11n

'"I .i: , .,., , T , '_ , ,

O.OOQQ . OO0 O.Iogo • 0.4000 O.IDOOO Oo|OO0 O._OqPO OoelUO O.tO4DO |.OOO0

FIG. 3a

.36

. ,,=.v_ ,o_ .. -_ o
J

ROTOR PRESSURE DISTRIBUTION

X/Bx : 8.X5, GRID IN, Cx/Um : 8.78

O.OOO0 _

O.IOO0_

o,4q_o0_

0

_u

FIG. 3b

37
STREAMWISE TURBULENCE (RMS)

I sv.'i "P,Tc_;

| Ts

141 I_ CENTER _,_OFSPAN =l

L i- _L

12

i 10

---MEAN 9.8 _ __._ O,,0.46

! I I I

0 20 40 60 80

% SPAN

100

FIG, 4

38
P

L

O?.IGINAI: _-_G_ IS

i

i

FIG.

Bx = 5 932 in. TOTAL ARC LENGTH = 20 334 in

$=O It li'='13. |1 In,

I I I I I i

3_ 3;' 33*

29

28

27

6_

63 26

65

64 22*

6_ , 18

73

74 17

75 , _6

_5

8_

84

85

8

89

5

9

I l l 1 !

1 2 3 4 5 6 7

X --inches

NOTE -- ORIGIN OF ARC LENGTH (S) IS THE AXIAL TRAILING EDGE

(MAXIMUM XL S INCREASES MOVING COUNTERCLOCKWISE

SUCTION SURFACE AIRFOIL TCs 1-60

PRESSURE SURFACE AIRFOIL TC s 40-9/

T C # )UB x SLID. T C ¢ _/B SltBp, T C • XJ8 S_' B

1 0995 0012 39 0073 1 698 59 0084 ' 94:

2 0 968 0 096 40 0 007 1 782 60 0 092 _ 9 t-'

3 0941 0 181 41 000_ 1 791 6 _ 0 13C ' 993

m.

4 09't5 0265 42 000_ 1 799 62 0'72 2C35

5 0887 0349 43 000C 1 808 63 0209 207?

6 08_4_ 0434 44 0000 1 816 64 024( _ 2 1!9

7 0829 0518 45 0001 I 824 65 0285 2 16;

11 _ 0799 0602 46 00(32 1 833 69* 035£ 2246

15 0767 068E 47 0005 _ 84,

, 73 0 42' 2 33:

16 0735 0771 48 000_ 1 856 74 ,,_ 0484 24"4

I 7 0 7C_ 0 855 49 0 0_ _ 1 858

75 0 53_ 2 49 _,

18 0663 0939 50 0018 i _57 ?9* 05_L 2 583

• 22 =, 0620 1 024 51 0023 1 875 83 063" 266 _

215 0575 i I08 52 0030 1 883 8A 0679 2 %:

27 0524 1 192 53 0037 1 892 8f 0 723 283t

_'m 0 464 1 277 54 0 044 1 900 89* 0 764 2 9..

29 039_ 1 361 55 0052 i 909 93 08C. 3 r,x,4

33* 0324 1 445 56 0060 _ 917 94 084_ 3089

37 0 169 I 529 57 0 068 I 926 95 0 878 3 _'3

3_ 0155 16_4 58 0076 _ 934 _ 0914 3257

_7 0 949 3 342

" AT THESE AXIAL STATIONS TCs LOCATED AT 50% SPAN AND -+83, 166 AND 25% AWAY FROM MIDSPAN

5a INSTRUMENTATION DIAGRAM FOR THE FIRST STAGE STATOR

39

'z
_. "" - vlr

03

(D

t"

(.)

q:

I

>-

6

4  ̧

3

0

I I I I I I I

2? 26

32 e_

- ".Z.

- "N X

.,\ \

0 I 2 3 4 5 6

X -- inches

NOTE -- ORIC, IN O= ARC LENGTH (S) IS THE AXIAL TRAILING EDGE

(MAXIMUM ,'_). S INCREASES MOVING COUNTERCLOCKWISE

SUCTION SJRFACE AIRFOIL TC s 1-58

PRESSURE SURFACE AIRFOIL TC s 38-93

1

7

T C # X/S= St'B, I" C # X/B= SttB, T C # X/B= S t 8=

0975 0069 39 0001 1 575 59 0 139 _ 764

2 0945 0148 40. 0000 1583 60 0172 ;804

3 09'2 0227 4_ 000C 1 591 6! F211 1 843

4 0878 030(5 42 00O? 1 599 62 0251 1 883

8* 0845 0385 43 0 004" I607 63 029_ I 92;

12 0811 0&6_ 44 0007 1 615 67g 037_ 2000

13 0 773 0 542 45 0 012 _ 62_. 71 0 445 2 08£.

14 0 735 0 62' 46 0 0_ 7 1 630 "I2 0 513 2 159

15 0 69-" C 70_ 47 0 023 I 638 73 0 574 2 237

77 • 0 629 2 316

16 0643 0779 4_i 0030 1646

J 81 0 68_ 2 395

20" 0 588 O 852 49 L' 037 1 654

82 0 730 2 474

24 0 525 0 936 50 0 044 I _5_

83 0 ?74 2 553

25 0 45_5 1 0_5 51 0 052 _ 870

215 03_2 1094 52 0061 1678 8_'* 0820 263_

21 U 303 1 173 53 0 068 I 686 91 0 858 2 711

28 0 226 1 252 54 0 076 1 693 92 0 899 2 789

32* S lt5 I 33' 55 0083 1 701 93 J 0940 2868

345 0_5 1 4_0 56 0090 I ?09

37 004,' 1 488 5; 0 o_ _ 7_7 " AT THESe_ AXIAL STATIONS T C s LOCATED

A1 50% SPAN AND ±83 166 AtND 25% 3/B 0003 1 567 _ 0 103 I 725

AWAY _ROM MIDSPAN

FIG. 5b INSTRUMENTATION DIAGRAM FOR THE FIRST STAGE ROTOR

4o

ORIGINAL PAGE I_]

OE POOR QUALITY

- . J

= ). u_.;..'. _ .......
0.6

1.el °

!

b,.

It

" 2.9_

STATOR-I IIOTOR STRTOR-2

0 0 o

0

0

0

0

0

÷ % 0 0 O0

0

_u o

0 O0 0

0 '0

0

0

0 0 0 0

CX_= 6 .I;8G

X/BX

0 SS

0 PS

o TE

W BP

• CG2

+ CGTI

FIG. 6a AIRFOIL MIDSPAN PRESSLIRE DISTRIBUTIONS,

X/Bx = 0.15, GRID OUT, C×/Um = 0.68
0.0

N

1.11

!

I

Q,.

It

2._-

STRTOR-I ROTOI_ STATOR-?

J_ 0 O 0

)

0

0

0

0

0

0

0

+ % 0 0 0

0 0

O0 _ 0 0

0 D

o g

o oO_

0 0 0 0

(X/U= 11.£99

3.0 I i I 1 I I I 1

.00 .SO i.011 .09 .511 1.110 .110 .SO 1 .(JO

XlllX

o ss

O PS

0 TE

* BP

0 CC2

+ CCTL

FIG. 6b AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/B× = 0.15, GRID IN, Cx/Um = 0.68

I,

42
8.0 _ STATOW-1

D 0

Q

_ log_

g.

I

Q.

II

Q- 2.0_

0

0

0

,5e

tJ

0

÷

0

0 O0 I_ 0

0

1,110

ROTOm

_0 (3 0 O

0

0

0

CX/U: 0.788

STATOI_-2

0 00(_ O

0

0 0 0 0

.OO .SO X.OO .60 .SO

X/OX

1 ,O0

0 ss

0 PS

o T[

6P

0 CC2

+ CGTI

! Q

t

,f t

!

/.

FIG. 7a AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/B× = 0.15, GRID OLIT, C×/Um = 0.2'8

_3

.4_ b,_e_ _1_ _.'_ ,I
_ll.wl _ _ __q_._l_,vw I.... TT,._.._ .1 . •

O°O ,

¢_ L.0_

I

II

L 2.0_

(¢,J

i

I

i

!

i

i

3.0 i

STltTm*|

o o o

0

)o

ItOTOt

o

0

+ _l 0 0 0

0 0

0 0

001_ II

0 13

0

0

o tl •

o 0 oIUlP

o 0 0 o

CX/U:. I.?lO

! I I I I I 1 I

•00 .SO 1.00 .OO .SO l,Oe .09 .50 1.00

X/OX

o ss

o Ps

¢ T[

w p

• CG2

+ CGTJ.

FIG. 7b AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/Bx = 0.15, GRID IN, Cx/Um = 0.78

44
0.0 • I_

)

0

(_ z.o

Q.

I

O.

(t

o. 2.0-

¢t_)

3.0

.00

STILT01-1 ROTOR

O0 o

0 CX/U: O._O

0

0

STATOR-2

O

O

O

0

0 ÷ 130 0 0 0

0

O 0

0

O o O

O

0 0 o

0

I I I I I I I I

,60 1.00 .00 .50 1.00 .09 ,50 Z.OO

X/BX

0 sS

0 PS

o T(

'_ BP

0 CC2

÷ CGTL

FIG. 8a AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/B× = 0.15, GRID OUT, C×/Um = 0.96

t

i

_5
O,O •

1.8

i

i-,o

li

a,. 2.eST#TW-I IIOTOR STRTOII-2

)

0

0 0 0

0

0

0 ÷

0

o oOd_ m

0

0

0

0

O0 0 0 0

0

0 0

0

0

0

0 0

0 0 0

CX/U: 9.966

0

I 1 I i I I I

•SO 1.99 .ke .SB 1.60 .80 .$8

X/BX

0 SS

0 PS

o TE

8P

0 CG2

+ CGTI

I,-- J

1 .CO

i"

d.

FIG. 8b AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/Bx = 0.15, GRID IN, Cx/Um = 0.96

t,6
.l

'%.

G.

!

oQ,.

w

II

a..

8.0 . IIOTOR STRTOA-2

o

o

o

+ % n 0 O

0

o

o o o o

(:X/U= I1.1;110

o

o

i"1

+ o O o O

0001 _ 0 o0 O 0

o

o

o

oo

0

n

_o

o ooo

I I I I I I I

•SO 1.00 .00 .SO 1.80 .OO .SO

XlBX

I

Z,OO

0 S$

C3 PS

0 TE

* Be

Q CG2

+ CGT!

FIG.

9a AIRFOIL MIDSP_N PRESSURE DIST,_;BUTIOlYS,

X/B× = 0.50, GRID OUT, Cx/Um = 0.68

.'4

:'7
0.0

r

STRTOR-I ROTOR STRTOR-2

0 0 0

r,

i

I

Im

0

CX/U: 0.$00

D

0

÷ % 0 0

0

000 0

o •

0 + 0

o o 00,.. • oo0

" 2.0_

¢c,.,_

3.0

0 0 0 0

0 0 0

0

0

0 0

0

00o

0

0 O0

I I I I I I I I

•O0 .50 1.O0 .OO .50 1 .OO .OO .50 1.00

X/OX

0 SS

0 PS

o TE

OP

0 CG2

+ CGTI

O

FIG. gb AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/B× = 0.50, GRID IN, C×/Um = 0.68

48
e.B STATOII-! ItOTOP STATOQ-2

F

" 1.0 I 0

g.

I

II

Q- 2,11_

II.._

0 0 0

0

0

0

0 000( _ 0

0

0

0

_/U: 0.78e

0

0

4_

0 0 o

0

0

+

0 o

00 q_ill_ • 0

0 0 0 0 0

0

0 O 0

0

0

0

Ok 0

0 0 oO°

0 O0

I I I I I I I I

.SO 1.09 .OG .SO 1.00 .OO .Ge 1.06

X/BX

FIG. lOa AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

×/B× = 0.50, GRID OUT, C×/Um = 0.2'8

49

0 SS

0 P$

o TE

* 8P

0 (C2

+ CCTI

b

t
0.0

1.0

.%

!

D,.

li

o.. 2.0_

((.,J

$TATOIt-I IOTM

0 D 0

0

0

)

0 0

CX/U: 0.709

+ nOD 0 0 O0

ST_TOI-2

0

0 _0 0

0 o

0 + 0 0

0 O0 O

0 0_11 0

0 _ 0 0 O

0 0 0

0 0 0

0

0

o,

0 000 o

0 O0

i I I I I I I

._0 1.0e .iN) .SO 1,00 .OO .50 1.00

X/BX

0 SS

D P$

o TE

8P

0 CC2

+ CGT!

0

4.

FIG. lob AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/B× = 0.50, GRID IN, C×/Um = 0.78

50
.................... . , ._ •................

r 0,o STMOII.I

 °Oo • o

IIOTO_

D 0

1.0

!

tO.

I!

a. 2.0_ ( (,.,_

0

0

0

.SO

000_ IJ

0

1,00 .IN)

D

O0 0

0

0 0 o

X/BX

STRTON-2

CX/U:'. 0.550

+

O0 _ 0 0

0

0

0 0 0

0

0

0

0

0

O0

,I. O0 .Oe .SO

0

0

! .00

FIG. 11a AIRFOIL MIDSPAN PRESSURE DISTRIBUTIONS,

X/B× = 0.50, GRID OUT, C×/Um = 0.96

0 $5

O PS

¢ TE

8P

Q CG2

•4- CGT2

O

51
( ¢._'1

0.e

)

o

1.0

I

I!

_.. 2.0-

3.0

.N

STRTOIt-2 ROTOR STRT91_-2

0 0 0

0

0

0

0

0 +

000_ 0

0

0 0

" 0 O

0 0

O

0 0 o°

0 0

0

CX/1J: 0.960

,4-

0

00 i_ilC_0 0

0

0

0

0 0 0

0

0

0

o o °_

0 O0

I I I I I I I I

.60 1 .O0 .00 .50 1 ,e8 .OO .SO 1.00

X/ilx

0 Ss

o PS

O TE

9P

0 CC2

+ COT1

t

I,

i

l

FIG. 11b AIRFOIL MIDSPAN PI_ESSURE DISTRIBUTIONS,

X/B× = 0.50, GRID I_, C×/Um = 0.96

52
I

1.0

8.0

8.4

Q.

, e.2

e_

e.e

0.

,_ -0.2

-e.4

-o.s

°8.$

-1.o

!

PRESSURE SUkr_C£

0 SUCTZON SURFACE

R^S£ PRESSURE

XtBX

L

FJC,. 12

FIRST STATOR PRESSURE DJSTR,IBUTJDN. _= D.?8

$3
-¢

i"

1.0

e.f

0.C.

8.4

Q.

!

0.2

D.

¢L

I

O.

I_ -0.2

G.

-0.4

-O.G

-G.8

-1.0

[3

[3

-- 0

e.o

PR[SSURr SURIr liCE

SUCTZOI_ SURIrRCE

Bf4$r PR_SSURr

I I "

O.I 3.2 1 I 1 I 1 1 1 I

8.3 G. 4 0.5 8.$ 0.7 O.G 0.9 1.0

X/BX

.¢,

FJG. 13a ROTOR PRESSURE DJSTRJBUTJON. _- O. 68

It

,I
1.0

e.8

e.$

0.4

G.

I

8.2

G.

r.

G.O

Q.

=i -0.2

0.

-0.4

-9.G

0 ° g

-I.0

0

0

PRESSURE |UkF_C[

0 SU_;ZON SURFACE

8_S[ PRESSURE

e.O

1 1!

e.| 0.2

I I I I I I I I

G.3 @.4 0._ O.[ t 0.," C.I_ e.9 1.0

X/BX

,L

++:.

F]G. 13b RDT(R PRESSURE D]STRIBUT/DN, _- D.?B

v,

55
1.0

0._

@,4

r..

' e.2

r,

" -0.2

-8,4

-8.$

-8.e

-1.0

m

j o o 5/

PRESSURE SURFACE

0 SUCTZON SURFACE

B_SE PRESSURE

1 I 1 I I 1 1 l ; I

0 g.I 8.2 e.S 0.4 0._ 0.6 8.;' 0.8 0.9 1.8

X/BX

FiG. 13c ROTOR PRESSURE DISTR,]BUTJON. _ - 0.95

I"

r"

56
_ j,

G.

I

G.

II

1.0

0.4

e.2

e.0

-0.2

-G.4

-0.G

°9.8

-1.0

i

\

o o

PR(SSUR( SUkF_C(

0 SUCTZOX SURFACE

I_S( PRESSURE

- I 1 I l 1 l I I 1 I

e.O 6.1 8.2 e.9 9.4 0.5 e.6 O.7 0.11 e.9 1.1_

X/BX

.d

J

FiG. 14a SEEDND STATOR PRESSURE DISTRJBUTJDN, ¢_- 0.68

.i

57
!

Q.

O,

II

Q,

_,0

e,[.

0,4

8.0

-8.2

-e,4

-O.G

-0,t

-t,e

(

Q PRESSURE $URrmC[

O SUCTZO_ SURFACE

B_SE PRESSUR[

! I I i ] ' 1 1 I r...... I

0.0 O.t e.2 0.3 0.4 0._ O.S 0.7 0._ O.Q t.O

X/DX

FiG. 14b SECOND STATOR PRESSURE DiSTRiBUTiON, ¢ = 0.'78

58
_1_1. _ " ._ _ _m. Im_ ,_, ---.-.-Tw-_._ _ _ _

4

,v

1,0

0.8

0.6

0.4

G,.

o 0°2

o.

Q.

d.

00 -0.2

-0,4

-8.6

-0,0

-t.O

rl

o

o

!=1 PI[SSUR[ SURF_C[

0 $UCTZON SURF_C[

|_S[ PR[SSUR[

0

I I I 1 T- 1 I 1 1 v

_.0 0.! e.2 0.!1 0.4 0.S G.S B.? 0.8 O.O 1.0

X/BX

FIG. 14c SECDND STATDR PRESSURE [').]STR.IBUT]O;;. ¢ = D. 96

f

59
- o

_

1.5°STAGE TURIIDIE, $TA. 2-MIS, _ZI) OUT, X,'BX: O.S8

RUN NO.= S/ I lllJ_ RVG.= 0.116

RADXUS: 27.88 CX/U AVG.= 0.6?0

4.00

CPTRBS

3.00,

0.00.

O .00

Cx/Um = 0.$8

PITCH

",t

CTOT

3.01

2.50

2.00

I .'_0

1.00

RUN NO.: 5/ 1 QUAN RUG.: 1.830

RRDIUS : 27.00 CX/U RVG.: 0.678

1 I 1

0.00 0.58 1.00

PITCH

1.50 2.00

FIG. 15a ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID OUT

6O f
t

!

CPTW$

4.0_.

1.5-STaGE TUIIIIZNEo STA. 2-lOS, GRID OUT, X/IX- II.M

_,: 4/ 2 _ IW' ,: I,LSS

II_ZUS : 27,110 x/U _.: 8.782

3.eo

2,o_,

8.oe. =-- __

i

0.01

A_ A_ AXA_A_ _

-I........ F v -- -T

0.50 1.00 1.50

Cx/Ut : O.?ll

PZTCH

2.00

?

°

CTOT

3.0B

RUN NO.: 4/ 2 QURN RV(.: 2.099

RRDZVS : 27.00 CX/U .3_;.: 0.782

2.50

1.50

1.09 ]

I I f I

0.90 0.50 1.09 1.50

PITCH

2.00

FIG. 15b

ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 6-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx - 0.17), GRID OUT

61
CPT_BS

4.00

1.5-STAGE TURBINE,

RUN NO.: 5/

RAPlU5 : 2?.00

STA. 2-RBS, GRID OUT, X/BW: B.5O

QUAN _VG.: 0.237

CX/U AVG.: 0.960

3.00

2.00

1.00

0.00

0.00

¢

Cx/UJ : 0._

0.50 1.00 1.50

PITCe

'.00

CTCT

3.00

RUN NO.: 5/ 2 QUAN AVG.: 2.591

RADIUS : 27.00 CwIU aUG.: 0.960

2 .SB

2.00.

1.50

1.00

l I i

.00 0.50 I .nO I .:,0 2.00

PlTE_

FIG. 15c ABSOLUTE TOTAL PRESSURE ANB VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EX!T (X/Bx : 0.1Z), GRID OUT

62
6.09

RUN NO,: 5/ I QURN AVG.: 3.465

RnDIU$ : 27.80 CW/U nvG.: 0.E78

CPS

5.00

4.00

3.00

2.00

0.00

Cx/Um : 6.£8

I I I

0 .SO 1.00

PZTCH

1.50 2.00

CX_U_

O.BOO

RUN NO.: 51 I QURN five.: 0.E,95

R"DI'J c, : 27.00 CXiU AVG.: O.G?8

l

n.75o t

0"7001/

0.650.

0.600

0.550

0.500

.00

!

0.59 1.00

PITCH

1,56 2.00

|, *

/,'4 ' FIG. 16a STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID OUT

63

.: ._
........... o

1.5-STRCE TURBINE, STY. 2-ABS, GRID flUT, X/BX= 0.50

RUN NO.: 4/ 2 QURN RVG.: 4.482

RRDIUS : 27.88 CX/U RUG.: 0.782

E.00

IL

CPS

5.08

'1.09.

3,00 _

Cx/U_ : B.78

2.00

I I I

0.00 8.59 1.00 1.59

PITCH

2.00

t

)

CX/UM

0.900

RUN NO.: 4/ 2 QURNAUC.: 0.790

RADIJ£ : 27.00 CX/U AVC.: 0.702

l

0 .BOO

q

@

0.750 t_

o .700 i

0 .C50

0 .GO0

i I I

0.00 0.50 ].00 1.50

PITC_

2.00

,ORIGINAL PAGE 18

POOR Q! L\I.ITy

a

FIG. 16b STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = O.17), GRID OUT

64

't
ORICclN/kl] p_Glg IS

OF POOR QU'/kLgrY_

l.r3"$T_,,E TUPBIN[, _IR. _-_$. GRID OUT, I/gX_-- 8.50

mUN NO.= 5/ 2 OURN_VG.: G._34

RRDIU.¢, = 27.03 (X,"U f4','G.: F ._E9

8.OO

CPS

?.OO

g .00

5.00

0.00

Cw/U_ : 6.9G

' 1 I

0.50 1.(,I 1.50

PITCH

2.00

/ -

R_DIUE : 27.00 CXIU QUa.= 0.960

1.100

1.050 1

• 0.50 1.00 _.58 2.80

PITCH

¢.

f;8' FIG. 16c STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = O.17), GRID OUT

65

_. ° ,
"15.O0

1.5-$TnGE TURBINE, STA. 2-ABS, 6RZO OUT, X/BX: 0.50

RUN NO.: 5/ I OU_N hVC.: GT.E19

RRDXUS : 27.00 CX/U A_G.: 0.678

65.00.

"L68.00

,.00

Cx/Um : 6.&8

I 1 I

0.50 1.90 1.50

PITCH

.00

ORIG_N_AL PACE [3

OE P._R QUALITy

FM] CDEG)

RUN NO.: 5/ I QUAN AVG.: -1,936

RADIUS : 27,e8 CX/U _VG.: 0.678

4.00 _

8.00.

-4.oo

-8 ,oo

-1_.00

1

.30 0.50 1.00 i .50 2.00"

PITCH

If FIG. 17a ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 1ST S_'ATOR EXIT (X/Bx = 0,17), GRID OUT

66

&
t

i

f

z ._*STAGE TURBINE,

RUN NO.: 4/ 2

.... ',, • RRDIU$ : 27.00

_.., ,, ! I" *_ ,_,_,,_

- -,_.t:_ /STs.oo

Gz ": -, _.kLIT_

STR. 2-q$, GRZO ool, X/hA: U._

QUAN AVG.: E7.595

CX/U AVG.: 0.782

Cx/Um : 0.75

70.OO_

YAWAB$ (DEG)

l

65.00

60.00

.00

I I I

0.50 1.00 1.50

PITCH

2,0_

PHI (OEG)

RUN NO. :

R_DI,.JS :

,1.oo.

I

I

J

[

0.00

-4.O0

-q .00

-12.00,

41 2 @UAN _'.'C.: -1.948

27.00 CX/U f_VC. : 0.782

I I I

0.00 g.50 1.00

PITCH

1.50 2.00

e

¢,

FIG. 17b

ABSOLUTE YAW AN[ PI CH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 1ST S'rbTOR EXIT (X/Bx = 0.17), GRiD OUT

67
RUN NO.: 5/ 2 QUAh RVG.:

RRDIUS : 27.00 CX/U hUG,:

75.00 ,

X/Sx: _.S0

67.341

8.960

Cx/Um : 8.5r

$D.08

0.00

t I I

B.50 1.00 1.50

PITCH

2_00

PHI (DEC}

4.00

-4.00

RUN NO,: 51 2 GUQN AVG.: -2.359

RQDIUS : 27.00 CXIU RUG.: 8.960

)

I I I

0.50 1.00

PITCH

1.50 2,00

ORIGINAL PAGE IS

OF POOR QUALITY

FIG. 17c ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID OUT

68
Z.S-$Tl_ IIIIIMNE, Ma. _lN, $l_l 110, X/OX= 0.M

IMI NO.= S/ 6 Olgm lug;.: 0.004

I_]LUS - 27.N _ lilUi.: 0.171

Cx/U,', : 0.$e

¢PIMS

2.00

0.00 0.50 1 .N ! .M

PZTCH

2.00

4

I-

/

CTOT

3.00

NO.: 5/ 5 _ It_,.: 1.04)

bO|US : 27.00 C)L/U #WT,.: 0.673

2.64

2.0e

1.54_

1.0e

I T I

0.0A 1.60 L.N 1 .SO 2.0_

P][TCll

FIG. 18a ABSOLUTE TOTAL PRE,SSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = O.17'), GRID IN

69
4.00

1.5-STAGE TURB%IE, STA. 2-A83, GRID iN, x/Bx: 0.50

RUN MO.: 5/ 4 QURN RUG.: 1.061

RRDIuS : 27.00 CW/U AUG.: 0.77R

CPTAB$

3.00.

2._0

1.00

6.00 I

0.00

Cx/UJ : 0.78

0.50 1.00

PITCH

1,50 2.00

CTCT

?.00

RUN NO.-- 51 4

RADIUS : ."7.00

r

p _bQN ¢_.'C.: 2.115

B C),/l AVG.: 0.778

2.00

1,50.

1.00

[ I 1

.00 0.50 I,P? ;.5C 2.On

FITCh

Ol,_ i)OOR QU-LI.,I'."Y,

FIG. 18b ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = O.17), GRID IN

7O
CPTkgS

4,ee

),Be

2,8e.

1,Be

e.H

INN I_.: 5/ 3

II_IUS : 27,ee

mK;.: 1.$1o

cx/u Av(; .: o,9s?

(x/Ua : 0.96

__--T-'_ "[ ]

8.B6 G.Se 1 .GO .I, .SG

PZTCH

2.90

I

• T

.,,.

CTOT

3.00

"2.5G.

2.0G

1 .SN

RUN NO.: S/ 3 QUAN AVG.: 2.E01

RAD%U$ : 27.B0 CX/U _UG.: 0.95?

1.00

0.00 O .50 1.00 1.50 2.80

PITCH

FIG. 18c

ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID IN

71
ORIGINAL PAGE TS

DE JE'OOR QUALITy

L

W

CP_

5.00 _

4.00 _

3J10

Cx/Ua = 0.60

2.08

I I I

0.00 0.50 1.00 1.50

_ITCH

2.00

i.  ̧

RUN NO. :

RH['I'J5 :

0.800

0.750 i

0.600

0.550

5/ 5 GURN AVC.: 0.E88

27.00 CXlU AVG.= O.E,79

I

0.51]0

I 1 1

0.00 0.50 1.00 1.50

PITCH

2.00

4,

FIG. 19a STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = O.17), GRID IN

72

/

i
CPS

.go.

4.0e

3.00

I.S-STRGE TUR|INE, STR. 2-RI_S, GIIID 1N, X/0X: 8.50

RUN NO.: 5/ 4 gUM I_,UG.: 5.452

IlROIUS: 27.90 CX/U RVS.: e.778

2.0e

f I I

0.00 0.50 1.00 1.50

Cx/U_ = e.78

PITCH

2.00

!

o.go0

R;)NNO.: 51 4 0URN RVC.: 0.790

RH[)IJS: 27.00 CX/U H_,'(.: 0.770

CX/UR

0.850

e.8oo.

i

0.750 _

0.700

0.&50

0.600

0.00

I I I

6.50 1.00 1.50

PITCH

2.00

FIG. lgb STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (.X/Bx = O.17), GRID IN

73

J
ce$

9.00

1.5-$TRCE TURBINE, STA. 2-RB3, GRID IN, X/B)I: 0.50

RUN MO.: 51 ) QURNRUG.: 8.251

RRD|J_, : 27.00 CX/U AuC.: 0.957

B.00

7.BO.

6.00

5.00

I I I

O.00 0.50 1.00

PITCH

1.50 2.00

1.100

A,[._._ : 27.0'3 C_ . , L. ;.Z_57

CXIUX

X.050

1.000

0.950

0.9O0.

0.850

0.800

0.00 0.50

0

/

1 I I

1.53 .00

OP.IGII'TAC PAGF_, IS

(_:" ['_X)l,t 0UALITX_

FIG. 19c STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID IN

74

&

q.
_5.88

1.5-$TRGE TURBINE, STA. 2-AI_, GRIO IN, X/OX: 0.50

RUN #0.= 51 5 GUI_¢RVG.: 68.06L

IROZUS = 27.80 CX/U AVG.: 0.$79

Cx/Um : 6.$8

70.00

YAWABS(DEG)

$5.06

60.00-

0.00 0.50 1.00 1.50

PITCH

2.00

PHI (0EG)

4.00

RUN NE_.: 51 5 QUANAVC.: -2.248

RADIU_ : 27.00 [X/U AVC.: 0.6?9

0.00

-4.00

I

-P.OO

-12.00

,p

1

0.00 i.50 2.00

i I

O. 30 1 .O0

PITCH

v ;

J,.& •

FIG. 2Oa ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = O.17), GRID IN

75

q
RUm NO.:

hDIUS :

75.08 __

I

70.00

• ,_..d4., .i, --h_-.o u',,I,_ .,o, _d_A. u.

5/ 4 QUAIl _tG.: 67._1G4

27.88 CX/U RVG. -.- 8.778

YaMABS (OEG)

65.00

Cx/Um = 0.78

60.00.

0.00

0.58 L .O0 J..50

PITCH

2.00

PHI (DE_)

4.00.

0 .t]O

-4.00

RUN N[.I. :

Rf*DI J_ :

r

5/ 4

27.00

QUflN AVC,: -2.458

CX/U RVG,: 8.778

-12 .o0 •

0.00

II I

i

0.50 1.00

PITCH

1.50 2 .GO

FI_. 20b

ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID IN

76
.L.O-btRbk IimULP,¢., bJ.N. _'-14_, biitJ.U 111, X/IJX: O.S(J

llrlN NO.= S/ 3 _ AVG.: 67.875

;_ZuS : 27.00 Cx/o nvC.: O.M?

?S.e0.

SS.O0

60.00

fx/Um = 0.95

1 I 1

O. O0 ;). 59 1 . OO 1.50

PITCH

.oo

i"

, o

,//s

PHI (PEG)

RUN NO.: 5/ 3

RQDIoS : 7.09

4.60 I

o.oo t

-4.00.

-8. O0, t

-12.09

_UAN RUe,: -2.£,80

CX/U RVG.= 0.957

/

!

J

I I I

O.OO 0.50 1.90 1.50

PITCH

.oo

I

t

FIG. 2Oc ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 1ST STATOR EXIT (X/Bx = 0.17), GRID IN

77
6.00

1.5-.eTnCE TURBINE, STR. 3-REL, GRID OUT, _/BX-- O.SO

RUN N_.: 3/ 2 _UAN RV_.: 3.(,55

RADIUS : 27.80 [X/U AVG.: O.FRO

CPTREL

Cx/Um : O.E8

5.80.

0.00 G,58 1.50 2.00

P.OOR QUALITY

WTCT

RUN NO. --

RflDI:J. ¢, :

3.00 -1

3/ 2 QUAN A"E.: l..C.

27.110 [)(/U A"[ .: rJ. [ 8(

2.00

L .,_0 -I

1 T T

( .q(_ 0.50 J..qP j rr_

PITrH

FIG. 21a RELATIVE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx "- 0.36), GRID OUT

78
,m

OF POOR QUAl,i'lY

CPTREL

6 .no

_._0 .

4.00

3.00

2.00 ].

o.00

RUN NO.: 1/ 4 QUAN RVC.: 3.E98

RrIDI'_ c- : 27.00 CX/U fi::C.: 0,776

Cx/Um : e._8

I 1 1

0.50 1.00 1.50

FITCH

i2.00

WT_4

9.qO

2.50

2.00

1.50

1 .nO

RUN NO.: 1_ 4 CUh'J _=C.: I.T05

R,+D])C ": 2?.O r. _"/:I _"E._ 0.77_

0.00

I I I

0.50 I .00 i .50

PITCH

2.00

/ , FIG. 21b RELATIVE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE Al" ROTOR EXIT (XtBx = 0.36), GRID OUT

79
CPTREL

9.00,

? .06

6.00

5.00

4.00

1.5-STAGE TURBINE, STA. 3-RELo GRID OUT, X/BX= 8.5B

RUN NO.: 31 5 QURN RVC.= 5.612

RRDIUS : 27.00 CX/U RUG.: 9.959

C×/Um : 0.96

0.00

I I i

0.5C i.D0 !.50

FITCH

2.00

WTOT

3.00

2,00,

RUN ND.: 31 5 @UQN AVG.: 2.088

RQDIUS : 27.00 [X/U _VG.: 0.959

I. 50 _i

1.00

0.00 0.50 1.00 1.50

PITCH

2.0fl

.-4 FIG. 21c RELATIVE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE Al" ROTOR EXIT (X/Bx = 0.36), GRID OUT

8O

&
9.00

1.5-STRG[ TURBZNIE, STR. 3-REL, GRID OUT, X/BX= B.Se

RUN NO.: 31 2 _URN AVG.: 5.278

RADIUS = 27.09 CXIU RVG.: @.600

,..,.." CPS

8.00

? .OO

6.00

5.00

¢x/Um = 8.69

0.00 0.50 1,0Q 1.50 2,C0

PITCH

CX/UM

RUN NU.: 3/ 2

RADZUS : 27.00

8.900

0'650 l

OUAN AVC.: 0.758

CX/U AVC.: 0.680

0.800.

0.750

o, 7oo.

0.650

O.GO0

0,00

I I I

0.50 1,00 1.50

PITCH

2.00

FIG. 22a STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/B× = 0.36), GRID OUT

81.

9

4

°
%11p_ w • •

CPS

9 .no

8.qo.

7.00 _

6.00

5.00

I,-_-_.TN[,E TURBINE, STN. ]-REL, CgIi, OU1, :','C : 0.50

RUN NO.= l/ 4 Qtl_i W'[,- _.;4 =.

RhDIJ_, : 27.00 CX/U _vC. _.77£

[x/Um : 0,78

I I I

0.00 0.50 1.00 J .50

F-ITCH

2.00

.... -,,"L,E,.L,_

CX.,U_

RLrN NC.= 11 4 QU_N N"'.: O.E3O

R_[,Ij_ : 2-.0C, £X,'U _vC.: 0.77E

1.000- r

I

0.35C, _

0.300

0.85C

0.800

0,?50 _

0. lO0 ,

I I I

.00 0.50 1.00

PITCH

1.50 .00

FIG. 22b STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (,X/Bx = 0.36), GRID OUT

82
1.5-STAGE T'JgG_WE, STR. 3-REL, CRZO OUT, _/8x: 0.50

RUN NO.: 3/ 5 QUAN AVG.: 9.89@

gAD]US : 27°00 CX/U AVG.: 0.9_3

12=00.

CPS

11.88

10.00

9.00

Cx/UI : 0._£

8.00

I I I

0.00 0.50 1.00 1.50

FITC_

2.00

1.200

_i,,r;C,.: 3/ 5 QOfiN A'.'C.: 1.087

RADIOS : 27.00 CX/U AVC.: 0.959

CX/UX

1.150

1 Io0

1.050 _

1.000 _

0.9+:_

0.900

1 1 I

0.00 C .50 t oo

FITCH

1.5_ ?.00

FIG. 22c STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID OUT

83
-50.00

RUN NO.: 3/ 2

RADIUS : 27.8B

QUAN RUG.: -59.719

CX/U AVG.: 0.686

-55.00 _

YAMREL (OEG)

CxlUm = 0.G9

-ss.oo I I 1

o.oo o.5o I.oo 1.so

PITCH

.00

PHI CDEG)

RUN N(_.: 3/ 2 QUAN AVC.: -0.1B0

R£DI,JE : 27.00 [X/U AVC : 0,680

4.00 _

8.00

-4. oo

-9 .oo

-12,00 _

] t I

0,00 0.50 1.00 J._0

PITCH

!.00

K,,

FIG. 23a RELATIVE YAW AND PITCH ANGLES FROM 6-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID OUT

84
-50.0O

-55.09.

¥_WREL (OEG)

-69, O0

1.5-ST_E TUIIt|INE, STA. 3-1_IEL, GRID OUT, X/BX: 0.50

IIUN NO,= L/ 4 _ I:_G.= -50.299

III_IUS : 27.00 CXtU AVG.: O.??E

Lx/Ua : 6.76

-65.00

I I 1

0.08 9.50 1.00 1.59

PITCH

_t,IU'y

.90

4.00

RUN NO.: 1/ 4 QURN AVC.: -9.026

RADIUS : 27.00 CX/U AVC.: 0.776

PHI (OEG)

p ,00

-4.00.

-8 .oo

-12.00

0.00

I i I

0.50 1 .OO 1.50

PITCH

.6O

&

FIG. 23b RELATIVE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID OUT

85 t
-50 .DO

1.5-STRGE 'IL_BINE, STA. 3-REL, GRID OUT, X/BX: 0.5B

RUN NO.= 3! $ QU_# AVG.-- -SS.381

RQDIIJS : 27.00 CX/U AVG.: 0.959

-55.00_

YAWREL(DEC)

-60,00

-$$.00

Cx/U_ : 0.%

1 I I

O.OB 0.50 1.00 1.50

PITCH

.00

PHI (DEC)

'1.00

0.00

-4.oo

-8.00 _

-12.00

RUN N_.: 3/ 5 GUQN AVE.: -G.295

RQDIUS : 27,00 CXlU ARC.: 0.959

I I I

0.00 0.50 1.00 1.50 2.00

PITCH

FIG. 23c RELATIVE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID OUT

86
6.00

I._-$TAGE TURBINE, STA. _-REL, GR_D _X, :_,'P;': _.5(

RUN NO.: 3/ 8 QUAN AVG.: 3.79_

RADIUS : 27.00 (X/U RVG.: 0.E81

¢.

CPTREL

5.00

4 .GE_

3.00

2.00

(x/IJll : 0._6

1 I I

8.00 0.50 1.00 1.50 2.00

PITCH

l

.i

MTOT

3.00

2 .SQ

2.00

P!IN N r ._- _' _ ( It,,'c.,r._ :.r!-

RHD],S,, : 27.0,) " . , _,"_i .: i,.' f

1.50.

1.00

0.00

1 T I

0.50 1.00 I .50

PITCN

.00

FIG. 24a RELATIVE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0,36), GRID IN

87

&

.!.,_L.__
]

CPTRZL

8 .t30

5.00

4.00

3.00

2.00

0.00

..t.S-CT_GE TURBIflE, STfi. 3-REL, GRID IN, XtBX: 0.50

RUN NO.: 3/ 7 QURN RVC.: 4.928

RNDIUS : 27.00 [X/U fiVG.: 8381

/

Cx/Um : 0.78

I I [

0 .SO 1.00

PITCH

1.50 2.00

WTC.T

3. O0

2.50

2.00

1.50

1 .r10"l

RUN 'WC:.: 3/ 7 _U_N _'JC .: 1.717

R_qC,l'Jf = 27.00 CX/U AVg.: 0.781

I { I

0.00 0.50

I .50 .00

I' FIG. 24b RELATIVE TOTAL PRESSURE AND VEI.OCITY FROM 8-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0,36), GRID IN

88 J

_..¶ tb-'7._.-
¢PTREL

9.09

5.08

1.S-STAtE TLII_INIE, STIr. 3-1EL. rAtiO IN, X/IX: 11._8

RUN NO.: 31 6 _l_N AVG.= 7.173

ItAD1'US : 27.00 CX/IJ AVG.: 0.966

I I I

9.08 9.50 1 .GO 1.56

PITCH

2.90

WTOT

3.06

2.58.

RUN NO.: 3/ 6 GU_N AVG.: 2.0?8

RADZ_5 : 27.00 £X/U AVC.: 0.960

2.09

1,50

1.00

.00 3.50 ).00 1,50 2.00

PITCH

;i

|

,,r

'b FIG. 24c RELATIVE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID IN

8o
9.00

1.5-$TRGE TURBINE, STR. 3-REL, GRID IN, W/BX: 0.50

RUN _0.: 3/ 8 GUAN AVG.: g.031

RADIUS : 27.00 CX/U AVC.: O.E81

CP5

8.00.

7.0B

G .00

5.00

Cx/Um : 0.68

I

I I I t

0.00 0.50 1.00 1.50

PITCH

2.00

RUN N_.: :/ 8 QURN RVC.: 0.707

RRDIJ_ : 27.00 [X/U AVE.: 0._BI

C.900

i

CK/UX

0.050

o.6oo

0.750

0.700

O.GqO -

0.Go0 1

0.00

1 I 1

0.5[' 1.00 1.50 2 ,OO

PITCM

J,

FIG. 25a STATIC PRESSURE AND AXIAL VELOCITY FROM 5-1-_OLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID IN

90 ,/
CPS

9.80

8.00.

7,00.

G.O0

5.00

1.800

1.5-$T_IGE TURBINE, 5TA. 3-REL, GRID IN, X/8;:: 0.50

RUN NO.: 3/ 7 QUANA_IC.: 7.E14

Rr_D_JC. , = 27.00 (_/U _uC.: n.TRl

Cx/Um : 8.78

0.00

I I I

0.50 1.00 1.50

FITCH

2.00

RUN NO.= 3/ 7 _UAN _VC.: 0.88E;

EHDIJE = 27.00 Ck/U 8vC.: 0.781

/.

CX,'UR

0.350

8.900

8.850

0.800

8.750

0.700

I I i i

o,0o 0.58 i .oo 1.5o

PITCH

2.00

FIG. 25b STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (×/B× = 0.36), GRID IN

9l
1,5-STRGE TURBINE, ,TR. 3-REL, GRID IN, X/BX: 0.50

RUN NO.: 3/ 6 QUAN AUG.: 11.417

RAOIU$ : 27.80 CX/U AVG.: 0.960

12.80 1

11.00_ _

CP_,

10.08.

9.00

B .00

0.02

Cx/Um : O.SG

I I I

0.50 1.00 J .50

PITCH

2.00

CX,'UM

c'h 'J . _/ 6 QUATJ _'_E.: 1.i19

_H[_]); : 27.00 f,(.'U _'{ .: 3.'-,_0

1.230 _

1.150

1.100

1.050

1.000

0.950.

LoJ 

0.900

; l I

O.O0 0.50 1.00 1.50

PITCH

.0C

FIG. 25c STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID IN

g2
-58.00

-55.00

YAilREL (DEG)

-60.09

-65 .o0

1._-£?RC( TURBZNE, STA. 3-REL, CRZD ZN, k,_k= _,50

RUN N0.: 31 8 QURN nVG.: -59._5£

RgOZU_ : 27.80 CXlU AUG,: 8._81

Cx/Um = 8.GO

8,00

I I I

8.50 1.80 1,58

PITCH

1.00

°P4c, r v4.

PNI (DEG)

RUN NO,: ?/ :: @UgN gVG.: 0.098

RaL,1Jt : 27.00 CXtU AVC.: 0.661

4.00

-4,00.

-8.00

-12.00

I I I

0.08 0.50 1.09 1.50

PITCH

2.80

FIG. 26a RELATIVE YAW AND PITCH ANGLES FROM a-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = O._6), GRID IN

g3 t
-SO .OO

X.5-$TRGE TURBINE, STR. 3-REL, GRID IN, X/BX: O.SO

RUN NO.: 3/ ? QURN RVG.: -58.175

RADIUS : 2?.00 CX/U RVG.: 0.781

-55.00

YAWREL (DEG)

-60.00

Cx/Um : 0.78

-6S.OO.

I t I

0.88 0.58 1.00 1.50

PITCk

.00

PHI CDE_)

RUN NO.: 3/ ? QUAN AV_.: -0.123

RHDIJE : 27.00 CX/U AVG.: 0.781

4.00 ]

I

0.00

-8.0G

-12oo, I ; I

ooo e so i.oo _.so .00

PITCH

FIG. 26b RELATIVE YAW AND PITCH ANGLES FROM S-HOLE PROBE

TRAVERSE AT ROTOR EXIT (XJBx = 0.36), GRID IN

94

&

q,
-50.00

-$5.00

1.5-STRGE TUR@INE, STR. 3-REL, GRID ZN, X/BX: 8.50

AUN MO.: 3/ 6 @UnNOUG.: -56.990

RADIUS : 27.00 CX/U OVG.: 0.950

Cx/U. : 0.96

0.90

1 I I

8.50 l.OO 1.50

PITCH

2.00

PXI (DEG)

4.00

9.08

-4.0

-8.00 _

R_DIa_ : 27.00 CX/U _vZ.: 0.960

I l I

9.50 1.50 2.88

FI3. 26c RELATIVE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT ROTOR EXIT (X/Bx = 0.36), GRID IN

95
CPT_£$

0.00

7.00

6.00

5.00

4.00

1.5-STRCE TURBZN[, STR. 4-RBS, GRID OUT, X/BX: 8.50

RUN NO.: B/ [ QUAN RUG,: 4,612

RRDIU5 : 27.00 CX/U RUG.: 0.676

CxlUm : 0.68

I t 1

0.00 0.5£ L.O0 1.50

PITCH

2.00

3.00

RUN NO.: B! I @UAN AVG.: I.ETO

RADI'JS : 27.00 CXlU AVG.: 0,676

CT,rT

2.50

2.00

I .50

1 ,00

I

q

I

-l T I i

0.00 n.50 1 Oil 1._0

PITS_

.00

FIG. 27a ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 6-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = O.14), GRID OUT

96
CPTAB$

O.OO

7,09.

6.00

_l.OO

4.OO

Cx/Llm : 0.75

I i I

0.00 0.50 1.6e 1.50

PITCH

2 .GO

_!lkl N'. : ¢ ,";', flOP,': (_l,rr ..- 1 .¢n:

R_DIJ', : 2:.00 CJ(_U _"C.: ,.q.?E,_

3.00 _

2.50

CTCT

1.50

1 ,_O

.00 0.50 I .r)O _.50 2,00

_ITC.

FIG, 27b ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 6-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = O.14), GRID OUT

97
RIIN N(!.': _/ 2 QU_N gl',.'C.: _.,_'¢',

PtlOl'Jc : ??.80 CW/U _"C.: 0.%2

CPTO?S

9. ,]0

Cx/Um : 0.96

0.00

I ] T

r :T(F.

rl,

ETCT

. 'qC

2.50

;..d30

1.50

I .00

R'd,/ NF .: " _ q_';',_, C .: :. :"

p,.[,.'t:, ? .,',- Cv,_ , .( .: p.:¢.-

.00

I I [

0.50 I .00 : .50

PITCF

i

,

,.. ( .. ,-

_'' I:'O()R _t,r.: ; . "'

a.

2 .FT[n

FIG. 27c ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 6-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID OUT

98

&

o ,
10.00

$.8e

CP5

6.00

I 7.90.

1.5-$T_%GE TURBIN[, STY. 4-A8S, GRID OUT, X/[:x: 0.50

RUN NO.: 8/ I QUAN &lVC.: 7.281

ReID]US : 27.00 £X/IJ _UC.: 0.(76

Cx/Um : 0.50

I I -- 1

0.50 1.0_ !.50

PITCH

2.00

CX,U_

C,800

O. 750

0. 700

0.658

0.600

C ,55_

0.5L}O

RHN _[ .: 81 1

RHC,[ J." : 27.00

\

\

_.00

I),50 I .00 1.50 2.00

PITCH

FIG. 28a

STATIC PRESSURE AND AXIAL VELOCITY F,4OM 5-HOLE PROSE

TRAVERSE AT _ND STATOR EXIT (X/B× = O. 14), GRID OUT

99
CPS

9.00

8.00 _

7.00 _

6.00

0.00 O.SO l.O0 1.50

CxlUi : 0.T8

PITC_

2.00

CX/U_

0.960

0.850

0.800 _

0.750 _

0.71)0 .

0,6_0

0 .GOC

RUN NO. :

R_DI,J¢, :

6/33 QURN RVG,: 8.763

27.00 CK/U AVG.: 0.782

I I [

0,00 G.59 I ,00 1.50 2.00

PITCH

,¢

FIG. 28b STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBF

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID OUT

't

i00
• +f,_ ..+ ..++

1[, ._I0

1.5-SltlGE TURBJ't:-", $Tfi. 4-_._]3, C,RZD (,LIT, Y/[:X: _.SO

RUN NO.= 8t 2 OUfiN fi:.'G.: JZ:.7.3!

R(IDIIJ_ , -" 2/.00 CX/U Ave.: 0._,6_'

Cpc.,

15 ._0 _

14.00 _

13.00.

Cx/Um : e.gE

12.00

I I [

0.00 0.50 1.00 i .SO

PITCH

2.00

1.100

E/ 2

27.00

_U+lrl +H/L.: _.913

CX,U _'..'C.: O._G2

CX/UM

1.050.

1.000 _

0.950

0.850

0.800

0.00

I I I

0.50 1.00 1.50

PITCH

2.00

I

FIG. 28c STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TR,.'_VERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID OUT

101
75.00

I.$-STRGE TURBINE, STR. 4-ReS, CRZD OUT, X/BX: 8.50

RUN NO.: 8/ i GU_N RVC.: E£.33B

RRDIUS : 27.00 CK/U AVG.: 0.6?6

CxlUm : O.gB

70.00

YQWQBS (DEG)

E5,n?

0.00

I I I

0.50 I.OC i .50

PITC_

2,_N

4 ,qo

RUN N[,.: E/ i QUAN _V[.: -1.752

, r, c R,q.'_J : 27.00 [wIU h','C.: O.E?£

PHI CDEG)

0.0G

-4.00

-B .00

-12,00

0.00

I I I

0.50 1.00 1.50

PITCM

2.00

F IG. 2ga ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID OUT

102
75.00

$5.80

S8.80

I.-_-_TNG£ TUPBIN_, _T_. 4-Op-, ¢_!D OU'r. X/F_X: 0._

I_LINNO.: [,'_:' Qur,q r,_,P{._-. _,r'.:O, 1

RQDI:J'.: 2T.O_ r_'_ q"C.: _;.7C:

Cx/Uu : 8.78

0.09

I i [

0.50 1.00 .t .50

PITCH

2 .CO

ORTC_'AL PACE IS

OE POOR QUALITY

4.08

0.00

PHI (OEG)

-4.00

-8.00

-12.00

RUN NO.: g/33

RRDIu$ : 27.08

QURN RVG.: -X.532

CX/U aVG.: 0.782

0.00

I I 1

0.'50 1.00 i .50

PITCH

2.00

lr

u

FIG. 2gb ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 2MD STATOR EXIT (X/Bx = 0.14), GRID OUT

103
75.08

1.5-STRGE TURBZNE, STR. 4-RBS, GRZO OUT, XlBX: e.se

RUN NO.= 8/ 2 QURN RVC.: 6E.S73

tROIU$ : 27.89 CX/U RUG.: 6.962

70.00.

YRgRBS (OEC)

65.00_

60.0O

0.00

Cx/Um : 0.9E

T _ I

0,50 1.00 1.50 2.08

PITC_

PHI (DEG_

4.00

0.00

-4.00

-8.00

-12.00

RUN NO.: _/ 2 QUkN _VC.: -1.204

RADI:J_ -- 27.00 CXIU _VC.: 0.9E2

0.00 0.50 1.00 1.50 2.00

PITCH

,s,

FIG. 2gc ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/B,K .-- 0.14)o GRID OUT
L.S-$TAG£ TURBZNE, STA. 4-ABS, GRZD TN, X/BX: 8.50

RUM NO.: 8/ 5 GUAN AVG.: 5.419

RADIUS : 27.00 CX/U AVG.: 0.683

6.00-

CPTABS

? .OO.

6 .O0

5.00

4.00

Cx/UI : 0,68

I ! i

0.00 0.50 1,00 i .50

PITCH

2.00

CTOT

RUN NO,:

RQDIUS :

3.00

2.S0_]

_I 5 QUAN AVG.: i._93

27.00 CK/U AUG.: 0.E83

2.00

1 .SO ._

i

1.00

.00

I 1 I

0,50 1,00 I,SO

PITCH

2.00

FIG. 30a ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = O. 14), GRID IN

105 t
i

CPTRBS

1.5-STQGE TURBINE, STQ. 4-ABS, GRID IN, X/BX: 0.50

RUN _0.: $/ 4 QUAN RVG.: 6.763

RQDIUS : 27.80 CX/U RVG.: 0.7?8

0.86

7.00,

6.08

5.00 _

'q.00

I I I

0.00 0.50 1.00 J .50

Cx/um : 0.78

PITCH

2.00

CTOT

3.00

2.50

2.00

1,58

RUN NO.: 81 4 QUQN QUC.: 1.922

RQDIUS : 27.80 CXlU AVG.: 0.778

l.O0

1 1 I

0.00 0.50 1.00 1.50

PITCW

2.00

FIG. 30b ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID IN

106

&

o,
CPTABS

1.5-STHG( TURBINE,

RUN NO.: 8/ 3

R_IUS : 27.00

12.80.

STR. 4-RBS, GRID IN, X/BX: 0.50

QURN RUG.= 9.651

CX/U RUG.: 8.953

11.00 _

_0.00

9.00

8.08

Cx/Um : 0.E

1 I I

0.00 0,50 1.96

PITCH

1.50 2.00

3.00

_UN NO.: 6/ 3 GURN AVG.: 2.360

RRDIU$ = 27.09 CXtU AV&.: 0.959

CTOT

2.50

2.00

1.50

1,00

0.00 0.50 1.00 1.50

PITCH

2.00

FIG. 30c ABSOLUTE TOTAL PRESSURE AND VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 2MD STATOR EXIT (X/Bx = 0.14), GRID IN

I07
113 .GO

1.5-.C.T,_GE TURBINE, STA. 4-ABS, OPit', _'N, Y/B>I: O.

RUN NO.: _/ 5 @URN _%C..: 8.15_

RRDIUS : 27,00 CX/U AVC,.: 0.E, B3

Cx/Um : O.EB

5.00

CP_

B .00

F

7.00

E,.rl0

P t I

0.00 0.53 !.O0 1.5_ 2.00

PITCH

CX, U'_

8.800

O. 750

0.730 _

0.6fi0

0.600

P,bN 'd..: P/ _ _UA4 r,'[.: O.E6_

P_[,_JI : 2_.OC CY,,U _'JC.: 0.683

\

O_gj i

I

I

C'=.O t

0. O0

?

0.50 1.00 1.50 2.00

PITCH

FIG. 31a STATIC PRESSURE AND AXIAL VELOCITY FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = O.14), GRID IN

108
12.00

1 J, O0

CPS

mmm,

18.00. ,!

p 9.06 _

1,5-STAGE TURB;NE, STA. 4-ABS, GR2D IN, X/BX: 8.50

RUN NO.: 8/ 4 QUA% AVG.: 10.300

IAOIU$ : 27.80 C_/U AVG.: 0.778

CxlVm : 0.76

8.00 "i

f l I

0.00 0.50 i .08 1.50

PITCH

I

.08

CX_U_

RUN NO.: 8/ 4 _U_N _v_.= 0,761

R_IJ_ : 27,00 CX/U AVe.: 0.77e

8.900

0.350

0 .eO_

0.750

0.?00

0.650

O.GO0

0,00

I

0.50

i .00 1.5C 2.00

PITCH

FIG. 31b

STATIC PRESSURE AND AXIAL VELOCITY FROM ,.-5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID IN

109
• o P,O"

CPS

loS-STaGE TURBINE, STn. 4-nSs, GRID IN, X/BX: 0.50

RUN NO.: 8/ 3 _UAN _vG.: 14.995

RADIUS : 27.00 CX/U FVG.= 0.95g

16.00_

_.o_ ..,e_

14.00

Cx/,im : C.gE.

13.00

F

I

I

12.00 "'l

_.00

J

I

;

I 7 7

PIT,I_

_% L'q

U ,nC

/

\

T 7 7 7

e.59 i .C r " ._C .7.fin

_IT,h

OPJGnNAL PAG_ 18

O_ POOR QUALITy

FIG. 31c

STATIC PRESSURE AND AXIAL VELOCITY' FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = O.14), GRID IN

lt0 j
Cx/um : O.E8

I I !"

0.50 1.00 I .r,O

PITCH

2.09

,JN N{ .:

R.[ I J. :

4 .O0

!

0.00 _

PHI (DEG)

-4.00

-8.00

-12.00

c, 5 gU_'J _,'.r.: -I.;Z'9

27.00 Cx,:J .'[.: r, ¢.'7

d

1 I v I

O.OC 0.50 I .00 i .'_0 2.00

PI'CH

FIG. 32a ABSOLUTE YAW AND PITCH ANGLES FROM 6-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID IN

Ill
!

(

75.00

65,00

69.00

0.00

1.5-STACE TUReINE, FTA. 4-RB_, GRID _N, X/BY: 0.58

RUN NO.: 8/ 4 OURN RUC.: 6(;._8(;

RRbZU$ : 27.08 CXIU RUt,,: 0.778

Cx/Um : 8.78

I I I

0.53 1,00 1.50

PI_C_

•ORIGINAL PAC_ T,_

QUALrTy

2,00

4.00

RUN NC_.: 8/ 4 QUAN AVC,: -1.465

R_DIuS, : 27.00 CX/U AVG.: 0.778

/I

0.00

PHI {DEC)

-4.00

-8.00

-12.00

0.00

0.58 1.00 1,50 2.00

PITCH

$.

/..i

FIG. 32b ABSOLUTE YAW AND PITCH ANGLES FROM 5-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID IN

112
RUN lO.: 8/ 3 QURN_VG.: 67.989

P_DIU_ : 27.00 (X/U RU_.: 0._59

75.oe,

?O.OO

YAVRBS (DEG)

ti5.00.

60.00

-- Cx/Us : 9.%

I 1 l

•00 0.50 I ,00 1.50

P1TCH

2.00

4.00.

0.00

PHI (DEG)

-*.00

-8.00

-12.00

RUM MO.: 8/ 3 QURN RVC.: -1.241

RRDIO$ : 27.90 CX/U RVC.: 0,959

\

\

O.00

1 1 I

0,50 I .OO 1.50

PITCH

2.00

FIG. 32c ABSOLUTE YAW AND P:TCH ANGLE,..H FROM 6-HOLE PROBE

TRAVERSE AT 2ND STATOR EXIT (X/Bx = 0.14), GRID IN

113

i,
3.co

CTOT

2,50

2.00

1 50

1.00

Cx/Um : 8,68

ORIGINAL PAGE iS

t !'" ,. >R QUPtLIT_j

l I T

•0_, O. 50 I .50 .C,O

0.C08.

8.150

0.188

8.050

0.080

TOT hVC.: '}.e23G RAN A'-'C.: 0.1180 PER AVG.: 8.014120

....o.o

/L ;;

I 7 T

8.BO 0.50

I .50 2.00

FIG. 33a CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 1ST STATOR EXIT, GRID OUT

114
ClOT

3.8e

1.50

l.oe

STA 2 HOT trILU, (X/tin: 8.U, X/IX: O.Se, GRIt) XN

C][ItC Ira;.: X.'it!

C_/Lm : 8.$|

i.60 O,SO l .Oe 1 .SO

PITCH

.ee

II. LIlt

0.e"-Je

o.eoe

TGT It_.: 0.0338 RRN AVG.: 0.(,302 P[It IWG.: 0.014403

too..e,

, , . - . .................. -

...... ., ,..._, _ ........ •

I I 1

.O0 O.SO l .SO ' .00

FIG. 33b CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 1ST STA'TOR EXIT, GRID IN

115
2.00

0

,,Ip" CTOT

1.50

1.00

0.5e,

0 .O0

Cx/Ua = a.$0

I 1 I

O .00 O.SO 1.06 1.56

PITCH

2 .Be

Jf

0.200

0.1S6.

0.128

0.080 _

0.040.

O.BOO

TOT AVG.: 0.1549 RkN RVG.: 8.1147 PER CVG.: 0.[00805

/. . .,.

'"'.. '. "

/........"

,/T;',

,lo,ooo

•.. :'

_. ..'

•. .."

1 I I

.00 0.59 1.90 ! .50

PITCW

.60

.V

/:o FIG. 34a CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT ROTOR EXIT, GRID OUT

I16
2.00

STA 3 HOT FILN, CX/UR: O.S8, X/|x= O.SO, GRID IId

CZI_ AVG.: 0.045

CTOT

1.58

1.00

O.SO

Cx/Um : O.E8

0.00

I I I"

O .00 0.50 1.00 1.50

PITCH

2.00

TOT AVG.: 0,1541 RAN AVG.: 0.J321 PER AVG.: 0.070345

G.2OG

8.160

0.189.

_.OSO

\

\

..... ',.',..

,: ..,.

_.DQ ....

.......-.,....... ./i

/

0 .OOO

[ J f

O.O0 6. SO 1.00 1. $6 .00

PITCH

"r,

FIG. 34b CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT ROTOR EXIT, GRID IN

I17
CTOT

2.00

1.75

1.50

1.25

1 .O0

Sln 4 HOT FXLN, CX/UM: 0.60, x/OX: 6.50, GRID OUT

CIRC RVG.: 1.559

Cx/Ua : 0.59

I I T

•00 0.50 1.00 l.SO

PITCH

.08

O.?eO

0.150

0 ,leo

O.85P

8.000

TOT RVG.: ].0570 R_N RVG.: 9.054] PER nVG.: Q.61_550

.l,.,o.

0 ,GO

• .,' .. ....

• , " /

• ., _., ....,

I -T

8.50 1,08

• , . " •

1

1.50 2.00

PITCH

.L

,i

FIG. 35a CIRCUMFERENTIAL DISTRIBUTIOR OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 2ND STATOR EXIT, GRID OUT

118
,h

2.NSI'Iu 4 NOT IrlLn, CX/UII: O.U, X,o119(:0.94, GltlrO III

¢Z_ RVG.- A.rAil

,_.7S

1.2';

l.oe

Cx/Ue : 0.60

I l I

0.90 0.50 1.00

PITCN

I.SO 2.00

r. I

0.790

0.150

0.100

0.050

0.008

TOT AVG.: 0.0563 RH RVG.: 0.0550 PER A_.: 0.015600

q_l

.' '°,.,.

,. ,,,

' "'".' • .*--,,! • • , o'"-....," "-%..

,%.o° .,°"

I 1 I I --

0.90 0.50 I .00 1.50 2.00

PITCH

FIG. 35b CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 2ND STATOR EXIT, GRID IN

119
3.OO

STA 2 N0T F_I.No CX/UN: 0.711. X/IX: It.N, GIIZD OUT

CXRC AVG.: 2.Otis

CTOT

Z .se

2.OO

X.59

1.80

Cx/Ua : 6.78

T I- T

e.oo 8.5o 1.06

PXTCH

1.59 2.96

0.296 -

9,150

o.100

6.059

9.060

TOT nVG.: 0.9309 RAN AVG.: 6.0217 PER AVG.: 8.919285

S P S P ,

] T T

1,09 0.56 1.90 1.50

PIICH

,90

FIG. 3Ga CIRCUMFERENTIAL DISTRIBUTION OF TIME

AND UNSTEADINESS AT ]ST STATDR EXIT.

120

AVERAGED

GRID OUT

SPEED

/
5ql_ -

FIG.

CTOT

UNSTEnDTN[$S

(SQRT)

3,n ,

STA 2 NOT FZLM, CX4JOI=.0.11, X41X: 0.541, ;IZD Xi

CZRC AVG.: 2.115

36b

2.5e

2.No

1.so

1.oo

CxlUa : 0.70

I ! I

0.00 0.50 ! .Oe 1.50

PZTCH

2.OO

0.200

0 450.

0.JO6

O.OSO

O,OOO

TOT AVG.: 0.0357 IIMi _l%q;.: 0.031e PER AVG.= O.0170eO

eele •

emo oo_

..--.-./, ....... -.,,:.:..:..-.-.-...-..-.:.,;,.,,."--. .......

O.co

1 I I

0.50 I.N 1.56

PIT(H

Z.O9

CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED

AND UNSTEADINESS AT IST STATDR EXIT. GRID IN

SPEEn

.

L 121
CTOT

2,N°

l.N .

0._ .

0.08

STA 3 NOT F'ZLM, tXA/01-'- 0.?0, X_n_.O.eA, GJID OUT

CI_ IKJC.: X.047

Cw/Um : 9.78

I 1 I

0.00 0.50 1.00 1.50

PZTCH

2.00

TOT AVG.: 0.1547

0.288

RAN AVG.: 8.!197 PER RVS.: 0.095611

8.160.

0.128

0.808

8.948

0.808

i"% s

e ,%_.

%r " " - .:'". . .....

. • ..,,'

• :' :,,,° •,/:"" "'" °". ./"

•.' ": •

/

.. /

_ oJ°,,,,

1 T 1

8.99 8.50 I .88 I .58

PZTCM

.88

,'..|

FIG. 37a CIRCUMFERENTIAL DISTRIBUTION OF TIME

AND UNSTEADINESS AT ROTOR EXIT. GRID

122

AVERAGED

OUT

SPEED

j
_TOT

2.N

1.50

_.0O ,

e.se

STA 3 NOT FILM, ¢X_II: |.11J, X/IX: O.SO, R2D Ill

CI_C fl_ .: 1.0S4

Cx/LOo : Oo?O

I I I

0.5e 1.50 2.00

TOT I_VG.: 0.1S45

O.200

_flN AVG.: 0.1372 PER AVG.: 0.K8406

0.150

O.lOe

O,OSO

OOO0

." ",

.,' •

.. \

.:

...

:.'

_p 0,...*.

I

.:%•,..

;'."' "L .'* '*r' ' •, ., ,.'

• ,,*' *% ....

I 1

,..,

O.00 0.50 1.00 t .SO

PIIC,4

2.00

FIG. 37b CIRCUMFERENTIAL DISTRIBUTION OF TIME

AND UNSTEADINESS AT ROTOR EXIT. GRID

123

AVERAGED

IN

SPEED
.o ,.

2.58.

STA 4 1407 FILN, CX_llg: 0,'/11, X/IIX: O.SO. gRID OUT

CXIt( I_u.: 1.903 I

CTOT

2.25 _

1.75

1.50

CxlUm : G.78

l 1 i

.gO 0.5£ ! .Oe .!..SO

PITCH

2.06

TOT @VC.: _.06L3

0.200

Qlm AVG.: 8.0577 I_P RVG.: L.815755

O. 150

O.!N]

I

8. eSe. I

I . 004B

'., :"', . .

,. ,." /' ".. . ....... . "',,

.. ....... .,,'"

I I l

0.00 O.SO I ._a J .50 2.110

PITCH

I'

..., FIG. 38a CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED

AND UNSTEADINESS AT 2NO STATOR EXIT. GRID OUT

124

SPEED
i

STn 4 HOT FILll. _ I1.111. _ 0.50. r,dlID Ill

(ILK; IWG.: 1.8S2

Cr0T

2.25

2.N

1.75

CxtUe : B.7d

1 I I

O.Oe 0.50 1.00 1.50

PITCH

2.0e

0 .?CO

0.150

0 .lOe

TOT _VG.: O.KIO IAN AVG.= 0.0_02 P[_ mVG.: 0.01S011

m

0

e.OO 0.56 1,00 1.50

PITCX

2.00

FIG. 38b CIRCUMFERENTIAL DISTRIBUTION OF TIME

AND UNSTEADINESS AT 2ND STATOR EXIT.

AVERAGED

GRID ]M

SPEED

125
3.N

CTOT

2.56

2.89

1.58

z.ee

Cx/Ua : _.9£

I I i

6.00 9.50 1.08 1.56

PITCH

2.e9

FIG. 39a

6,299

8.156

0.199

9.e50

o.ooo

. TOT AVG.: 0.0286 RAN AVG.: 9.018[ • PER AVG.: 0.920120

_'-- ' "I ...... 1--" ' l ...... 1

I,O0 9.5g I .90 I .50 2.60

PITCH

CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 1ST STATOR EXIT, GRID OUT

126
STA 2 HOT FILM, CX/UM: 0._. X_BX: 0.50, CRID IN

CIRC I_G.: 2.506

L'

CTUT

2.58.

2,N.

1.50.

1.00

P

C_/Uo : 8.9£

1 I I

O.90 0.50 t .00 ! .50

PXTCN

2.00

Jf

0.280

0.1S0.

0 ,IN.

0 ._0.

0,900

TOT RVG.: 0.0366 RAN AVG.: 0.C302 PER AVG.: 0.019778

eoeoot.

............. ' "',. .... _'..:','_':"":"_"'_"'-":'_'. "...... ' L .." " -- :'.--.:'--''''_ :'i.

1 I I

.00 Q,SO I .O0 !,50

PITCM

? .00

L

4,

I' B

/:4 FIG. 39b CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 1ST STATOR EXIT, GRID IN

127
2.80

$TR 3 HOT FILN, CXAHq: 0.96, x/ex: e3o, GRID IN

CIRC fl',tG.: 1.427

CTOT

). 36

1.90.

0.59

8.69

CxlUm : 0.96

.00

I I I

0.50 1.00 i.50

PITCH

2 .co

9.200

9.160

101RVG.: 9.1691 RAN AVG.: 6.1456 I_g AVG.: 0.003674

9co

PITCM

!.OO

FIG. 40a CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AIND UNSTEADINESS AT ROTOR EXIT, GRID IN

128
CTOT

STII $ NOT FXLli, CX_IN: It.I, X/ilK: t.N, _XID OUT

CXllC iWI; .: 1.444

t._ _

0.00

e.oe f I I

0.50 t .00 ! .50

PIT¢_

Cx/Um : O._N_

2.00

TOT _.: 0.1507 RM AVG..- 0.1;733 PEN aWC.: 0.058853

0.210 _____._.._

0.00 0.50 I .N 1.50 2.00

PXTCN

FIG. 40b

CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT ROTOR EXIT, GRID OUT

129

._4".._ _'_B..-,4_-_-_,._v-_--

J-
2.50

CTOT

2.25

2 .O0

1.75

1.50

,oo

I 1 i

0.50 I . 0,? 1.50

PITCH

.60

0.200

0.150

O.zOO

0.050

O.OeO

TOT AVG.: 9.0715 RAN AV_.: 0.0559 PER AVG.: 0.025529

t,

1 , T

0.00 0.5e ! O0 1.50

PITCN

?O0

FIG. 41a CIRCUMFERENTIAL DISTRIBUTION OF TIME AVERAGED SPEED

AND UNSTEADINESS AT 2ND STATOR EXIT, GRID OUT

[30
i

I

y

t

CTOT

2.U

2°2_,

_a 4 mT F_oe, _ e.So x_l=: O.N, _D Zl

Clte IWG.: 2.2S6

I.N

I I I

0.0e 0.50 1 .Be ! ,_W

Cx/U_ : O.S

PITCH

2,0e

TOT A_.: 0.073! RU AVG.: 0._82 _R _.: 0.024G68

I._

O. J,50,

O,fllO

0.050

*o*,eeo

_me o oo o

/

,....

..... •,.,, . ....,

"".... :" ,,

", ..:

,, "....,

o.eeo

I I |

O.OO 0._0 I .00 l .SO 2.60

PITCH

W FIG. 41b

CIRCUMFERENTIAL DISTRIBLITION OF TIME AVERAGED SPEED

AND UNSTEADINESS ,_T 2ND STATOR EXIT, GRID IN

131

,I

. . r
Report Documentation Page

1. Relx_ No. 2. Govemmem _ No. 3. FlectlSent's Cs_og No.

NASA CR- 179469

4.

g.

12.

'ring She 8uettt_

The Effects of Inlet Turbulence and Rotor/Stator Interactions on the

Aerodynamic_ and Heat Transfer of a Large-Scale Rotating Turbine Model

IV--Aerodynamic Data Tabulation

k.tt_s)

R.P. Dring, H.D. Joslyn, and M.F. Blair

Performing Organization Name _ Adclree8

United Technologies Research Center

Silver Lane

East Hartford, Connecticut 06108

Sponsoring Agency Nm and Addrm

National Aeronautics and Space Administration

Lewis Research Center

Cleveland, Ohio 44135-3191

5. Report Date

November 1987

6. Performing Orgamization Code

8. Porforming Orgenization _ No.

UTRC-R86-956480-4

I0. Work Unit No.

533--04-1 l

11 Contract or Grant No.

NAS3-23717

13. Type of Report and Period Covered

Contractor Report

Final

14. Sponsoring Agency Code

15. Su_t_ry Notes

Project Manager, Robert J. Simoneau, Internal Fluid Mechanics Division, NASA Lewis Research Center,

Cleveland, Ohio 44135.

16.

17

Al_trncl

A combined experimental and analytical program was conducted to examine the effects of inlet turbulence on airfoil heat transfer.

The experimental portion of the study was conducted in a large-scale (approximately 5 x engine), ambient temperature, rotating

turbine model configured in both s;ngle-stage and stage-and-a-half arrangements. Heat transfer measurements were obtained using

low-conductivity airfoils with miniature thennocouples welded to a thin, electrically heated surface skin. Heat transfer data were

acquired for various combinations of low or high inlet turbulence intensity, flow coefficient, first-stator/rotor axial spacing, Reynolds

number and relative circumferential position of the first and second stators. Aerodynamic measurements obtained as part of the

program include distributions of the mean and fluctuating velocities at the turbine inlet and, for each airfoil row, midspan airfoil

surface pressures and circumferential distributions of the downstream steady state pressures and fluctuating velnciues. Analytical

resells included airfoil heat transfer predictions produced using existing two-dinnensiona; L"3undary layer computation schemes and an

examination of solutions of the unsteady boundary layer equations. The results of this program are reported in four separate

volumes. All four have a common report tit!e -,.n¢lthe following volume subtitles:

Report Title: The Effects of Inlet Turbulence and Rotor/Stator Interactions on the Aerodynamics and Heat Transfer of a LargeScale Rotating Turbine Model.

Volume Titles: Volume I: UTRC-R86-956,4gO-I

(NASA CR-4079)

Volume lh UTRC- R86-956,480-2

(NASA CR- 179467)

Volume III: UTRC-R86-956480--3

(NASA CR- 179468)

Volume IV: UTRC-Rg6-9564g0-4

(NASA CR- 179469)

Key Woods (Sugg_lted by Autl_s))

Heat transfer

Aerodynamics

Turbines

Rotor/stator

Turbulence

Unsteady flow

Airfoils

Final Report

Heat Transfer Data Tabulation 15% Axial Spacing

Heat Transfer Data Tabulation 65% Axial Spacing

Aerodynamic Data Tabt)lation

Dale fo, |enenll relea_

STAR Category 34

May 19A8

Unc lassi fled Unclassi fled i 34 A07

l II I I II l I

N_ FO_I ION OCT I_

i