NUREG/CR-4566

ORNL/TM-10005

OAK RIDGE"

'NATIONAL

LAORATORY;:

4-6 F AW & FW#"-0 W. EAmNr

COMPBRN IIl - A Computer Code

for Modeling Compartment Fires

Vincent Ho

Nathan Siu

George Apostolakis

George F. Flanagan

Prepared for the

U.S. Nuclear Regulatory Commission

Office of Nuclear Regulatory Research

Under Interagency Agreement DOE 40-550-75

.Y

T. ~ -

. . .E 'A .

S.. ,-t .. 1⁄4
NOTICE

This report was prepared as an account of work sponsored by an

agency of the United States Government. Neither the United

States Government nor any agency thereof, or any of their

employees, makes any warranty, expressed or implied, or

assumes any legal liability or responsibility for any third party's

use, or the results of such use, of any information, apparatus

product or process disclosed in this report, or represents that its

use by such

rights.

hird party would not infringe privately owned

Available from

Superintendent of Documents

U.S. Government Printing Office

Post Office Box 37082

Washington, D.C. 20013-7982

and

National Technical Information Service

Springfield, VA 22181
NUREG/CR-4566

ORNL/TM-10005

Distribution Category RG

Engineering Physics and Mathematics Division

COMPBRN III - A COMPUTER CODE FOR MODELING COMPARTMENT FIRES

Vincent Ho*

Nathan Siu*

George Apostolakis*

George F. Flanagan

NRC Monitor: Ben Buchbinder

Division of Risk Analysis and Operations

Program Manager: G. F. Flanagan

Oak Ridge National Laboratory

Principal Investigator: G. F. Flanagan

Oak Ridge National Laboratory

Manuscript Completed: November 1985

Date Published: July 1986

Prepared for the

U.S. Nuclear Regulatory .)mmision

Office of Nuclear Regulatory Research

Under Interagency Agreement DOE 40-550-75

NRC FIN No. B0493

Work Performed Under

ORNL Subcontract No. 19X-22270

*Mechanical, Aerospace and Nuclear Engineering Department

University of California, Los Angeles

Los Angeles, California 90024

Prepared by the

Oak Ridge National Laboratory

Oak Ridge, Tennessee 37831

operated by

Martin Marietta Energy System, Inc.

for the

U.S. DEPARTMENT OF ENERGY

under Contract no. DE-ACO5-84OR21400

CONTENTS

ABSTRACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V

ACKNOWLEDGMENTS .... .......... .... ..... ... vii

LIST OF VARIABLES ................... .......................... .. xiii

Chapter page

1. INTRODUCTION AND SUMMARY ........................... ....... 1

2. THE HOT GAS LAYER MODEL ................. ..................... 4

Background ....... ...............

Basic Features of a Room Fire ....

COMPBRN III Hot Gas Layer Model . . .

Mass Transfer Model .........

Thermal Transfer Model .... ........

The Mass Transfer Models ...........

Mass Burning Rate .... ..........

Forced Ventilation Mass Flow Rate .

Fire Induced Door Flow ......

Doorway Coefficients .........

Air Entrainment Model ...........

Plume Entrainment Model .

Doorway Mixing and Wall Jet Mass

Thermal Transfer Models .......

Plume Heat Transfer ............

Heat Transfer Due to Gas Flows . .

Convective Heat Transfer .....

Radiative Heat Transfer .........

Flow Rate

4

4

6

6

8

9

9

10

11

14

15

16

18

21

21

21

22

22

3. SUMMARY OF MODIFICATIONS .............. ................... .. 25

4. SIMULATION OF EXPERIMENTS ............... .................... 30

Simulation of'SNL/UL Cable Tray Fire Experiments

Description of the Cable Tray Tests .......

Comparison of Simulation Results ......

Simulation of Steady-State Flow Experiments . .

30

30

31

33

5. USERS GUIDE TO COMPBRN III ................ ................... 35

Additional Modeling During Application .....

Program Flow .......................... Drogramming Notes ...............

35

36

38

iii
Outputs . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

Inputs . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

Overall Job Parameters (&STRT) .......... ............... .40

Individual Job Parameters (&SIZE) ....... .............. .. 40

Title Card .................. .......................... .. 41

Fuel Bed'Definition (&FUELB) ............................ .. 41

Pilot Fuel Parameters (&PILOT) ........ ............... .. 42

Physical Fuel Parameters (&FUELT) ....... .............. .. 43

Miscellaneous Data (&MISC) ... ................. . ..... 44

Communication Data (&SEE) ........... .................. .44

Non-communication Data (&NSEE) ........ ............... .. 45

Room Data (&ROOM) ............... ...................... .. 45

Initialization Data (&GINIT) ................ .46

Model Variation Factors (&MODVAR) ....... .............. .. 46

Output Definition (&OUTF) ........... .................. .47

6. REFERENCES ..................... .......................... .. 50

Appendix page

A. A SAMPLE PROBLEM ................. ........................ .. 91

B. CODE LISTING ...... ................ . ... ........... ... 129

iv -
ABSTRACT

The computer code COMPBRN III deterministically models the behavior

of 'compartment fires. This code is an improvement of the original

COMPERN codes. It employs a different air entrainment model and

numerical scheme to estimate properties of the ceiling hot gas layer

model. Moreover, COMPBRN III incorporates a number of improvements in

shape factor calculations and error checking, which distinguish it from

the COMPBRN II code. This report presents the ceiling hot gas layer

model employed by COMPBRN III as well as several other modifications.

Information necessary to run COMPBRN III, including descriptions of

required input and resulting output, are also presented. Simulation of

experiments and a sample problem are included to demonstrate the usage

of the code.

v

ACKNOWLEDGMENTS

We would like to thank G. F. Flanagan of Oak Ridge National

Laboratory and B. Buchbinder of the U.S. Nuclear Regulatory Commission

for their support and encouragement throughout the development of

COMPBRN III. We also acknowledge the assistance and helpful comments of

M. Brandyberry of UCLA, and the comments that we have received from

0. Akerlund and S. Dinsmore of Studsvik Energiteknik, Sweden.

vii

LIST OF FIGURES

Figure

1. Flow Chart of Computation Processes in COMPBRN .........

2. Typical Features of Room Fire in a Two Zone Model ....

3. Features of Room Fire in COMPBRN III HGLM .............

4. Room Geometry of Rockett's Air Flow Model ........

5. Effect of Blockage on Mass Flux Ratio ..........

6. Effect of Vertical Wall on Plume Mass Flux ............

7. Radiative Heat Flux Emitted by Hot Gas Layer and Ceiling .

8. Flow Chart of the CGAS Subroutine ............

9. Enclosure Details of SNL/UL Experiment 1 ........... . ,.

pMge

. . . 54

. . . 55

. . . 56

. . . 57

. . . 58

* . . 59

* . . 60

* . . 61

* . . 62

• . . 63

. . . 64

10.

11.

Enclosure

Enclosure

Details of

Details of

SNL/UL Experiments 2-4

SNL/UL Experiments 1-4

12. Simulation of SNL/UL Experiment 1: Hot Gas Layer Temperature

13.

14.

15.

16.

17.

18.

19.

20.

21.

22.

Simulation

Simulation

Simulation

Simulation

Simulation

Simulation

Simulation

Simulation

Simulation

Simulation

of SNL/UL

of SNL/UL

of SNL/UL

of SNL/UL

of SNL/UL

of SNL/UL

of SNL/UL

of -SNL/UL

of SNL/UL

of SNL/UL

Experiment

Experiment

Experiment

Experiment

Experiment

Experiment

Experiment

Experiment

Experiment

Experiment

1:

1:

2:

2:

2:

3:

3:

3:

1:

1:

Cable Jacket Temperature

Heat Flux .............

Hot Gas Layer Temperature

Cable Jacket Temperature

Heat Flux .............

Hot Gas Layer Temperature

Cable Jacket Temperature

Heat Flux ..............

Hot Gas Layer Temperature

Cable Jacket Temperature

65

66

67

68

69

70

71

72

73

74

75

- ix -
23. Simulation of SNL/UL Experiment 1: Heat Flux .... .......... .. 76

24. Simulation of SNL/UL Experiment 2: Hot Gas Layer Temperature . 77

25. Simulation of SNL/UL Experiment 2: Cable Jacket Temperature . 78

26. Simulation of SNL/UL Experiment 2: Heat Flux .... .......... .. 79

27. Simulation of SNL/UL Experiment 3: Hot Gas Layer Temperature . 80

28. Simulation of SNL/UL Experiment 3: Cable Jacket Temperature . 81

29. Simulation of SNL/UL Experiment 3: Heat Flux .... .......... .. 82

30. Simulation of SNL/UL Experiment 4: Hot Gas Layer Temperature . 83

31. Simulation of SNL/UL Experiment 4: Cable Jacket Temperature 84

32. Simulation of SNL/UL Experiment 4: Heat Flux ............ .... 85

33. Experimental Arrangement of the Steady-State Flow Experiments . 86

34. Simulation of the Steady-State Experiments: T.G ............ .. 87

35. Simulation of the Steady-State Experiments: Z D... ......... .. 88

36. Simulation of the Steady-State Experiments: Z ... ......... .. 89

N

37. Programming Flow Chart of COMPBRN III.....................90

- x
LIST OF TABLES

Table

1. Common Parameters Used in the Simulation Comparison ......... .. 32

2. Other Parameters Used in the Simulation Comparison .......... .. 32

3. Parameter List for Simulation of Cable Tray Fire by COMPBRN III . 33

4. Parameter List for Simulation of the Room Fire Experiments . . 34

5. Values of DCFIN and DCFOUT Used in Table 4 .... ........... .. 34

6. COKPBRN III Sample Problem Input ............. ................ 92

7. COKPBRN III Sample Problem Output ....... ............... ... 94

xi

LIST OF VARIABLES

Variable Definition

A Area CmW)

Ci Doorway inflow coefficient

C0 Doorway outflow coefficient

C S Surface controlled burning rate constant (kg/J)

CV Ventilation controlled burning rate constant

F1 -2 Configuration factor from object 1 to object 2

g Gravitational constant (9.8 m/s 2 )

h Convective heat transfer coefficient (W/mIK)

HHeight of doorway (.m)

HR Height of room (m)

kf Gas absorption coefficient (m- )

M Blockage factor

PLCF Entrainment coefficient

4 Heat release rate (W)

T Temperature (K)

t Time (s)

U Volumetric flow rate (m3/s)

V Volumetric flow rate (m3 /s)

W Wall effect factor

i Mass flow rate (kg/s)

WD Door width (m)

WR Room width (m)

Greek Characters Definition

9 Emissivity rFraction of heat radiated to the environment r

B Flame angle

p Density (kg/me)

Reflectivity

Stefan-Boltzmann constant 5.67xi0 (W/m2KV)

xiii
Subscripts Definition

CEIL Ceiling

E Entrainment

e Environment

G Hot gas layer

0 Lower Region

PL Plume

tAmbient

xiv
Chapter 1

INTRODUCTION AND SUMMARY

COMPBRN is a deterministic fire hazards computer program designed to

be used in a probabilistic analysis of fire growth in a particular room.

As described by Apostolakis et al. [1-2], this analysis is required when

assessing the risk associated with fires in nuclear power plants.

Possible output of COMPBRN includes the total heat release rate of the

fire, the temperature and thickness of the hot gas layer formed near the

compartment ceiling, the mass burning rate for individual fuel elements,

the surface temperature of the elements, and the thermal heat flux at

user-specified locations.

COMPBRN III is the most recent version of COMPBRN. The original

version of COMPBRN, called COMPBRN I in this report, is described by Siu

in [3], while the models employed by the code are discussed in [4-61.

The improved version by Chung et al., called COMPBRN II here, is

described in [7).

While COMPBRN I has performed reasonably well in a number of

analyses, it has been recognized that situations could arise where the

damage time predictions of the code could be overly conservative,

because radiative and convective heat losses from the surfaces of most

objects being modeled have not been accounted for. COMPBRN I has

therefore been modified to account for the influence of these losses on

the time-temperature history of a specified object. The resulting code,

COMPBRN II, which incorporates a more general damage model based on fuel

element temperature, has been used to simulate three cable tray fire

experiments, and has performed fairly well (both in an absolute sense

and relatively to COMPBRN I) in two of them [7].. In the one instance

where the predictions of the code are not good, the source of error has

been traced to the hot gas layer model employed by both COMPBRN I and

II.

COMPBRN III employs a different air entrainment submodel in the hot

gas layer model and incorporates a better numerical scheme in the

subroutines CGAS, CSOLVE, CNEWTN and CGASHT to solve for the hot gas

layer properties. A number of minor changes, including changes to the

plume heat transfer, mean plume temperature correlation, cylindrical

shape factor, and vertical fuel cell calculations have also been

incorporated in COMPBRN III. Numerous input error checking statements

and comment cards have been added to make the code more user friendly.

COMPBRN III follows a quasi-static approach to simulate the process

of fire growth during the pre-flashover period in an enclosure.

Briefly, the compartment is modeled using two zones (or control

- 1 -
volumes), which means that the enclosure is divided into two distinct,

homogeneous, stably-stratified regions. The hot gases accumulating

under the ceiling due to fire plume entrainment and negative buoyancy

are defined as the upper layer (the ceiling hot gas layer). The lower

region is assumed to be thermally inert and contains relatively

quiescent cool air, which remains at ambient conditions at all times.

The hot gas layer can play a significant part in the growth rate of the

fire. Heat fluxes from this gas layer preheat non-burning fuel

elements, reducing their time to damage. The burning rate of a fuel

element is used to determine the heat output rate of that element. This

burning rate depends on the physical properties of the fuel and on the

compartment ventilation rate. Using standard shape factor analysis and

idealizing the flame as a cylinder, the heat transferred to other fuel

elements, the walls, and ceiling via radiation is computed.

Correlations are used to determine the convective heat transfer in

the buoyant plume of hot gases above the flames. Provisions are also

made to simply model the layer of hot gases accumulating near the

ceiling as a thermal source. The temperature profile within each "fuel

element" (including the compartment walls and ceiling) is computed as a

function of its thermal environment. An element is considered ignited

(or damaged) if its surface temperature exceeds the user-specified

ignition (damage) temperature. Time is incremented, and the process

starts over, with newly ignited fuel elements adding their contributions

to the total rate of heat release. The flow chart of this process is

shown in Figure 1.

The various steady state models and submodels used to construct

COMPBRN III are obtained from the fire research literature. Efforts are

made to keep the model complexity to a low level due to the large

uncertainties inherent in the modeling of accidental fires. Model

simplicity is desirable from' an economical point of view, since

computing costs can be significant in a probabilistic analysis.

However, simplification in modeling naturally leads to some loss of

accuracy for certain types of scenarios. The assumptions made in

COMPBRN III are geared towards the modeling of relatively small fires in

large enclosures and the hot gas layer is assumed to be formed within

the first time step of simulation (which is usually taken to be one

minute). Thus, the code's predictions are expected to be most

reasonable for fire scenarios involving large fuel loads during their

pre-flashover burning period.

The models used to describe individual phenomena which comprise the

overall model are, with the exception of the hot gas layer model,

algebraically simple. The main role of the computer in COMPBRN III is

to keep track of the heat input and output of each of the many fuel

elements used to model a complex fuel bed.

Chapter 2 describes the phenomena of a typical fire in an enclosure

following a general two zones approach. The hot-gas-layer model (HGLM)

employed in COMPBRN III is defined and a detailed discussion on the

various submodels used in the HGLM is also presented in this chapter.

Chapter 3 lists other major modeling changes in COMPBRN. The results of

-2-
simulations of several experiments are presented in Chapter 4 and they

demonstrate that COMPBRN III can predict the behavior of compartment

fires reasonable well. Chapter 5 provides a users guide to operate

COMPBRN III including a description of required input and resulting

output. A sample problem with a description of its input and output to

demonstrate the usage of COMPBRN III can be found in the. Appendix.

-3 -
Chapter 2

THE HOT GAS LAYER MODEL

2.1 BACKGROUND

In recent years, various mathematical models have been developed to

predict the fire growth processes in compartment fires. Much of the

current research efforts on understanding the development of room fires

have concentrated on the construction of zone models, which divide the

room into distinct, homogeneous regions. A simple model for smoke

movement was first used by Kawagoe [8], who studied the movement of

gases through an opening connecting two regions (i.e., the ambient air

region and the room region which was considered to be a well-mixed,

homogeneous region).. A few years later, Thomas et al. [9], studied

flows in rooms with well defined stratified hot and cold gas layers.

Other works which use similar models are discussed in papers by Rockett

[10], and Quintiere et al. [11-14].

The zone model predicts the average (in the sense of well-mixed) gas

and wall temperatures in various well-defined regions. Of course, this

approximation does not provide information at specific points inside the

room; thus, some processes are ignored. However, the use of spatially

averaged quantities requires only a few equations for each region and

for the coupling between regions.

Typical features 9f an enclosure fire are described in Section 2.2.

The HGLH employed in COMPBRN III, which is developed from the phenomena

described in Section 2.2 with further modifications and assumptions, is

defined in Section 2.3. A detailed discussion of the energy balance

equations and various submodels used in the HGLM is presented in this

chapter.

2.2 BASIC FEATURES OF A ROOM FIRE

The basic features of room- fires described by a typical two zone

model are shown in Figure 2. A fire starts at a distance, Z0 , above the

floor and releases energy at the rate of Q. This energy causes the gas

pressure in the flame zone to rise. The products of combustion, with

temperature higher than that of the environment, are driven upward by

buoyancy forces. A hot turbulent plume is generated and begins to rise.

The upward momentum of the plume depends on the distance between the

fire source and the ceiling, the fire strength, and the thermal

-4-
stratif ication of the room. Indeed, in some conditions the plume may

not even reach the ceiling.

The fraction of Q which effectively drives the plume gases upward is

taken to be (1 - T dQ, where Tr is the fraction of Q lost by radiation

from the flame zone and thel plume itself. Along the axis of the plume,

relatively quiescent air at ambient. temiperature is entrained into the

plume and mixes with the plume gases as they continue their ascent

toward the ceiling. As a result of the air entrainment, the total upward

mass flux in the plume, WpL,, continuously increases, while its

temperature, T PL, decreases. When the plume gases impinge on the

ceiling, they spread and form a relatively thin turbulent ceiling jet.

As this hot jet moves radially outward, it transfers energy by

convection, conduction and radiation to the ceiling causing its

temperature to rise. When this ceiling jet (which is composed of plume

gases and ambient air that has been entrained into the ceiling jet from

below) is blocked by the room boundaries, it turns downward at the

ceiling-wall juncture, thereby initiating a downward directed wall jet.

This wall jet, W rW , is of higher temperature and lower density than the

ambient air into which it is being driven. The wall jet, retarded by its

relative negative buoyancy, turns upward and entrains an additional

amount of cooler air from the lower region on its way up. Eventually, a

relatively quiescent upper gas layer is formed below the continuing jet

flow activities. Thus, stratified regions are formed as the fire grows

and the room is divided into several regions with distinct thermal

boundaries.

With the presence of a doorway, hot gases leave the room through the

opening above the thermal interface, and in exchange, fresh air is

driven into the room due to pressure differences to replace the air

entrained into the plume. Near the doorway, the motions of the hot gases

and fresh air are in opposite directions and a shear layer is formed

between the two layers. Inside this shear layer, hot gases are

entrained into the lower region by the incoming fresh air. Such mixing

flow, W J, and the wall jet, W1,W,, as well, may cause the lower region

temperature to rise.

The momentum of the inf lowing fresh air creates an aerodynamic

disturbance and drives the originally undisturbed plume gases into a

tilted position with an angle 8, as shown in Figure 2. This tilted

plume travels a longer distance than before on its way up into the hot

gas region; thus, more air from the lower region is entrained in the

plume flow. As this tilted plume enters the hot gas region, it

continues -to entrain gases with lower temperature from its surrounding

and turns into a ceiling jet and then a wall jet. The upper region

entrainment and the jet flow activities provide a stirring effect and

-5 -
mix the gases in the upper region. The presence of forced air

ventilation flow enhances the mixing of hot gases in the upper region.

Thus, the gas layer can be approximated as a zone with uniform

properties.

2.3 COMPBRN III HOT GAS LAYER MODEL

COMPBRN III models a room fire having features similar to the above

description with further simplifications and assumptions. Figure 3

depicts the features in the COMPERN III hot gas layer model. The HGLM

separates the room into two zones: the upper hot gas region and the

lower cooler fresh air region. These regions are separated by a thermal

interface with uniform height inside the room and a higher elevation at

the doorway. This interface is formed within the first time step of the

code simulation period. The ceiling jet, plume gases, wall jet and the

doorway mixing region are all considered to be part of the upper region.

The doorway mixing jet and the wall jet are combined with the plume flow

model to form the air entrainment model, since they all take part in the

entrainment of fresh air from the lower region into the HGL. They are

the only mechanisms that allow direct mass exchange between the two

regions.

The lower region is assumed to be thermally inert and its temperature

remains at ambient room temperature all the time. At each time step,

the HGLM computes the thermal interface heights (Z D and Z N ), the HGL

temperature (T G) and the heat fluxes to fuel elements by solving several

coupled mass and heat steady state balance equations. The HGLM, like

all quasi-static models, performs best when the quantities of interest

do not change rapidly and steady state is achieved within a reasonably

short time period. Experimental results (e.g., (11], (121, [151) have

verified that after the initial transient response of a fire ignition

inside an enclosure, thermal and flow characteristics of room gases are

reasonably constant within thirty seconds to five minutes from ignition

depending on the room configuration and fire source properties.

2.4 MASS TRANSFER MODEL

Mass is conserved in the HGLM. The rate of mass gained by a zone is

equal to the rate at which it is lost at any moment. For continuity,

Rate of Mass Gained - Rate of Mass Lost

When this balance equation is applied to each region in the RGLH (see

Figure 3), the following mass flow relations are obtained:

-6 -
For the Upper Region:

Rate of Mass Gained =

Rate of Mass Lost =

For the Lower Region:

Rate of Mass Gained =

Rate of Mass Lost =

For the Compartment:

Rate of Mass Gained =

WE + WVIN

Wo OT + W VOUT

WIN

W E

WIN

WOUT

+ WU,IN + WF

+ WUOUT

+ V,IN + WUIN + WF

Rate of Mass Lost + WVOUT + WUOUT

where

WF Fuel mass burning rate.

WU,IN = Mass flow rate of fresh

forced ventilation.

V U,OUT= Mass flow rate of gases

ventilation.

WV,IN = Mass flow rate of fresh

ventilation.

W VOUT= Mass flow rate of hot

ventilation.

WIN = Mass flow rate of incom:

air into the lower region by

out of the lower region by forced

air into the HGL by

;ases out of the HGL by

forced

forced

ing fresh air through the doorway.

- 7 -
W OUT = Mass flow rate of outgoing hot gases through the doorway.

WE = Mass flow rate of air entrainment due to plume flow

(WPL), wall jet (WW) and doorway mixing jet (Wa).

W PL + WW + W

From the above expressions, the mass balances for the upper and lower

regions are obtained as follows:

WE WVIN WOUT + ,OUT

WIN + WU*IN + WF = WUOUT +

(1)

WPL (2)

2.5 THERMAL TRANSFER MODEL

Since the lower region is assumed to be thermally inert, it is not

necessary to write a heat balance equation. For the upper region, the

HGL, thermal energy is conserved, i.e.,

Rate of Heat Gained = Rate of Heat Lost

By tracing the heat flow path in Figure 3, the following relation is

obtained:

For the HGL:

QPL = QoUT + + QCONV + Q (3)

QPL

%UTr

GRAD

QCONV

= Rate of heat gained by the HGL through plume flow.

= Rate of heat lost from the HGL through doorway outflow.

Rate of heat lost from the HGL due to radiation.

= Rate of heat lost from the HGL due to convection.

- 8 -
QV = Rate of heat lost from the HGL due to forced air

ventilation.

As well as shown in the following sections, the mass flow rates and

energy flow rates depend upon TG, ZD and ZN. Thus, Equations 1, 2 and 3

form a coupled system of non-linear algebraic equations which can be

solved iteratively for the unknown variables of the HGLM (TG,

ZD and ZN), using a variety of approaches (e.g., a Newton-Raphson

iteration scheme).

2.6 THE MASS TRANSFER MODELS

2.6.1 Mass Burning Rate ( WF )

The mass burning rate model used in the HGLM is described in [4].

Briefly, such model is as follows:

For ventilation controlled fires,

WF C V WIN (4)

For surface controlled fires,

.1It .11 1

WF m0 + CS qEXT (5)

where

WIN = Mass flow rate of incoming fresh air through the doorway.

CV = Ventilation controlled burning rate constant.

m 0 = Specific burning rate constant.

CS = Surface controlled burning coefficient.

En11 q EXT = External heat flux impinging on the fuel element.

-9 -
2.6.2 Forced Ventilation Mass Flaw Rate ( WU and WV )

The forced air ventilation system mass exchange rates are functions

of the volumetric flow rate of air and hot gases flowing through the

vents. To avoid pressure built up in the compartment, the volumetric

inflow and outflow rate should be identical at all times if the door is

closed. The vents in the HGLM are assumed to be located either at the

ceiling, or on the floor, or both, to allow gaseous: exchange. The

fractions of incoming air going into, or outflowing hot gases going out,

of the room via the ceiling vent are taken to be FC and FH, and those

through the floor vents are (1 - FC) and (1 - FH), respectively.

Assuming ideal gas properties, the density and temperature

relationship is as follows:

pT = Constant

Therefore, the mass flow rate of gases going through the vents is:

W = Vp

or, if the reference temperature is set to be the room temperature, T0 ,

then

W VT

The forced ventilation mass flow rates can then be expressed as

follows:

WV,IN = (FC)Vp0 (6)

WUIN = (1 - FC)Vp 0 (7)

W-u'o = (1 - FH)Vpo (8)

Wv,OUT = (FH)V T (9)

where

P0 = Ambient air density.

Tn =Ambient air temperature.

- 10 -
TG = HGL temperature

V = Volumetric flow rate of the forced air ventilation system.

FC, (1 - FC) = Fractions of air being pumped into the room

through the ceiling and floor vents, respectively

(0 <- FC < 1).

FH, (1 - FH) = Fraction of gases being pumped out of the room

through the ceiling and floor vents, respectively

(0 S FH S 1).

This is a simple but effective model for assessing the forced

ventilation mass flow rates. Since these flow rates are usually small

compared to the flow rate through the doorway, they become important in

rooms with small openings or without any opening at all. In these cases,

the introduction of cool air into the HGL and/or the removal of hot

gases from the HGL through forced ventilation may decrease the HGL

temperature by a significant amount due to extra convective heat losses

by these processes.

COMPBRN III has been found to perform well in most simulations with

the presence of forced air ventilation, while previous versions of

COMPBRN may generate unreasonable results or may not even generate a

solution at all.

2.6.3 Fire Induced Door Flow ( WIN and WOT )

The temperature difference between the room and its environment

creates a pressure difference which causes fluid flow through the

opening. The correlations used to quantify the mass flow rates of. the

incoming fresh air and the outgoing hot gases may be viewed as

equivalent to satisfying the fluid dynamic equations of mass and

momentum conservation subject to a constraint (the height of the thermal

interface). They are developed by tracing the pressure changes around a

loop [10]: 0- 1 - 2- 3 - 0, as shown in Figure 4.

From Bernoulli's equation, the kinetic energy, PU_, of fluid per

2

unit mass which is -accelerated from rest is equal to the change in

static pressure, AP:

U1

AP = P--•--

2

or

pU = [2pAP]i

where

U = Velocity of fluid flow.

- 11 -
p = Density of fluid.

Let the elevation of

furthermorb, let point 3 be

same elevation. Then

point 2 be Z, such that ZN < Z <HD;

a stagnation point outside the room with the

p2 U = [2p 2 AP]}

AP = P2 - P3

The fluid mass flow rate is defined as:

W = pV = pUA

where

V = Volumetric fluid flow rate.

A = Orifice cross-sectional area.

Therefore, a differential mass flow rate, dW, can be obtained:

dW = P2UA = [2P2APJ]WD dz

Integrating the differential mass flow rate from ZN to "D, we obtain

the mass outflow rate,

WOUT Z N C 0 dW

= ' C0WD[2pAP2' dz

N

where

C = Doorway outflow

Section 2.6.3.1.

Applying Euler's equation:

coefficient to be discussed in

dP

dz = -pg

- 12 -
P(Z)

N

P(Nl

P(Z)

P2

P3

-P

-P

-P

z

dP= (-pg) dz

N

(ZN) - pg(Z- Z1)

(ZN) - p2 g(Z - ZN)

(ZN) - p3 g(Z - ZN)

By the ideal gas law,

P 2 = P

TG

TO

= T0G

TO

AP = pog(l -- TG )(Z

mass outflow rate is:

- zN)

Therefore, the total

WOUT

Ui CoWD{2pT 0(

C W(2p -[G 0 )P~g(Z

-G

- ZN)]}I dz

ZN

3C0WDP0 ( 2g-~-( - 0 (HD - ZN)3/2 (10)

The inflow rate can be obtained in a similar way with a slightly more

complicated integral.

WIN

ZD

z0

T0

CiWD(2pO[pOg(I' G )(ZN - ZD)l dz

ZN

+ I CiVD(2p0[p~g(1-

ZD

)(ZN - z))i dz

fG)(E

- 13 -
3CDPo 2 g(l T N - ZD)} (ZN +-.-) (11)

G

where

C = Inflow doorway coefficient to be discussed in Section 2.6.3.1.

2.6.3.1 Doorway Coefficients ( Ci and CO)

The doorway coefficients are a measure of how efficiently the

pressure difference of the fluid across the opening is converted into

velocity head. A coefficient value of zero represents complete

resistance to flow in and out of the compartment, i.e., the compartment

is sealed off. A value of unity is equivalent to an ideal opening where

air flows without restriction. Necking effects at the door may cause a

slower gas flow into the compartment, therefore, in most cases, we

expect the inflow coefficient (Ci) to be smaller than the outflow

coefficient (C0 ). However, in some cases, where the fire source acts as

a jet pump and creates a high velocity turbulent plume flow, the fresh

air is virtually driven into the room and gives the inflow coefficient a

value greater than 1.0.

When data on the inflow and outflow mass flow rates are available,

the doorway flow coefficients can be obtained by the following

relationship:

W (MEASURED)

W (THEORETICAL)

Since it is impossible to measure the velocity of gases at every

location, average values for the coefficients are used. The exact

values of the coefficients depend on many factors, such as the room

configuration, fire strength, doorway dimensions and materials used to

construct the room. From the experimental data available in the

literature, the outflow coefficient seems to be nearly constant and has

an average value close to 0.7 in most cases. However, the value of the

inflow coefficient seems to vary from experiment to experiment.

Different conditions give different inflow coefficients. For example,

in Quintiere and McCaffrey's wood crib experiment (12], C0 has an

average value of 0.68 and Ci can be quantified by the following

correlation:

C, = 0.58 - 0.31WD; 0 S WD S 1

- 14 -
Of course, these values may not be applicable to other experimental

configurations.

To provide additional perspective on typical values for Ci and C0 , we

note that in the first fourteen of the fifty-three experiments reported

in [13] (a description of the experiments can be found in Chapter 4), C0

has an average value of 0.74 with a standard deviation of 0.06 and the

average value of C. is 1.13 with standard deviation of 0.35, if we use

1

the measured values of TG, ZD and ZN to calculate the theoretical mass

flow rate (using Equations 10 and 11 in Section 2.6.3). Although

Quintiere et al. had computed an average value of 0.73 for C., the

calculational methods used were not consistent with the assumption of a

two zone approach, in which the hot gas layer should be represented by

an average temperature value instead of having separate inner and outer

room temperature values.

When a situation arises which requires the quantification of the

coefficients as input to COMPBRN III, and the user has no previous

knowledge in assessing the flow coefficient values, the use of a typical

value of 0.7 for C is recommended. If it is a free burning situation,

0

Ci may be approximated as 0.6; if it is a fuel injected situation (e.g.,

the fire source is a jet burner), a value of 1.0 for C. is recommended. 1

2.6.4 Air Entrainment Model ( WE )

The air entrainment model is the major modeling difference between

COMPBRN II and III. As described in Section 2.2, fresh air is entrained

into the fire plume and lowers the plume temperature while increasing

its mass flow rate. In COMPBRN III, the air entrainment model consists

of a new plume entrainment model, a wall jet entrainment model and a

model for the doorway mixing effect. COMPBRN II ignored the latter two

phenomena.

The air entrainment model employed in the previous COMPBRN series

(which was composed of plume entrainment only) followed the notation and

analysis of Fang 116]. The mass entrained at height Z by a combusting

plume is:

W =W (o ZD 0 ° )/3+ W (1 (12)

PL FW(J Dr/2 + F)2

where

Z0 = Fire base height.

Df = Fire base diameter.

w = Plume entrainment coefficients.

- 15 -
The weaknesses in this entrainment model as employed in COMPBRN II

can be listed as follows:

1. The equation provides a model of a free burning fire and

is not an appropiate model for enclosure fires;

2. The shape of the fire source (i.e., axisymmetric, line

fire, wall fire, etc.) and drafts in the room which

affect the orientation of the flame are not incorporated

in the above correlation;

3. The model neglects the wall jet and doorway mixing effect,

which may play a significant role in. some situations;

4. Quantification of WPL depends on the prediction of the

flame diameter (Df), flame height, fuel burning rate (WF),

and other parameters (0 and w), which carry significant

uncertainties themselves.

In recent years research activities have been directed toward the

modeling of fire plumes employing different approaches. A number of

them have been found to be accurate, but applicable only to specific

conditions. Zukoski et al. (17] have developed a plume flow model

resulting from the theory of a weakly buoyant point source of heat and

the Boussinesq approximation. The model requires fewer parameters and

is more applicable to room fire situations than Fang's model described

above. To improve COMPBRN, we have changed the original plume

entrainment model of Fang to the more versatile model by Zukoski

described below. This plume flow model, combined with a wall jet and

doorway mixing effect model, forms the new air entrainment model for the

HGLM of COMPBRN III.

2.6.4.1 Plume Entrainment Model

The plume entrainment model in the HGLM is based on the model

developed by Zukoski et al. [17]. Briefly, the fire source is modeled

as a weak point source, with the Boussinesq density approximation; it is

assumed that the vertical velocity U and temperature difference AT have

gaussian profiles in the radial direction. The plume mass flow rate,

WPL, is approximated by the following correlation:

WPT = 0.210 p. 4 V z(Q*)1/ 3 (13)

where

- 16 -
(l - r)Q

Q p.C T Zz Vfj=

Zukoski et al. have demonstrated that the above correlation agrees

with experimental values within approximately ±30%. Disturbances to the

plume flow due to side wind and wall effects in the lower region have

been found to be the causes of the deviation.

Aerodynamic Disturbance

Fresh air coming into the room through the doorway may cause an

aerodynamic disturbance, known as the side wind effect, to the plume

gases. The originally vertical plume flow becomes tilted to an angle,

0, depending on the strength of such incoming wind (see Figure 2). The

plume, then, has to travel a longer distance before it reaches the hot

gas layer. Thus, the mass flow rate is increased due to more air being

entrained into the plume.

To take into account such a deviation, the elevation term, Z, in the

plume entrainment correlation (Equation 13) has been changed to Z/sin 0,

where 9 is the flame angle. Complicated correlations have been developed

to estimated the flame angle. However, these correlations are not

always consistent. Zukoski has also pointed out that the presence of

room boundaries affects the flame angle. Experimental data have shown

that the side wind effect can be represented by a parameter, called the

blockage factor, M. The values of this "actor under different room

boundary conditions are shown in Figurk: 5 [171. The mathematical

relation between the blockage factor and the flame angle may be

described as follows:

1 )5/3 (14) = sinO

The value of the blockage factor for a room fire, H = 1.28, which

corresponds to a flame angle of 600, has been found to be quite

reasonable in estimating the side wind effect on the plume flow in most

room fire situations.

Wall Effect

The effect of placing a vertical wall near the fire source is to

reduce the plume mass flow rate by decreasing the effective area for the

plume to entrain fresh air from its surroundings. The reduction of air

entrainment causes the average plume and hot gas layer temperature to

rise. Since less air is entrained into the plume, the thickness of the

hot gas layer also decreases.

- 17 -
Experimental results (111 have revealed that the plume mass flux can

be reduced by as much as 45% depending on the position of the wall.

Figure 6 shows the effect of a vertical wall on the plume mass flow

rate.

In COMPBRN III, the reduction in plume flow is represented by a wall

effect factor, W, such that

W = 1.0, if the fire source is away from the wall.

W = 0.75, if the fire source is next to a vertical wall.

W = 0.5, if the fire source is at a corner.

COMPBRN III employs a plume entrainment correlation incorporating the

blockage factor (M) and the wall effect (W). The combined plume

entrainment correlation can be expressed as follow:

WPL = M W WpT (15)

where W PT is the original plume entrainment correlation developed by

Zukoski et al. (Equation 13).

2.6.4.2 Doorway Mixing and Wall Jet Mass Flow Rate ( W4 and W )

In addition to the plume entrainment, fresh air can also be

introduced into the hot gas layer region by the doorway mixing and wall

jet effects. The result of these effects is to increase the total amount

of fresh air being entrained into the hot gas layer.

Doorway Mixin Rate (W )

Experiments have verified the existence of doorway mixing which

occurs between the hot gas layer and the lower region. This mixing

effect increases the temperature of the lower region and decreases its

oxygen concentration by dilution with combustion products. The nature

of this mixing is a turbulent shear entrainment that occurs as cold

fresh air enters the doorway and hot gases leave the room above the

thermal interface. Part of the outgoing hot gases is driven into the

lower region by this shearing process. The negatively buoyant hot gases

turn upward and entrain an additional amount of fresh air from the lower

region on their way back to the upper region. This extra amount of fresh

air entrainment (W J) is ignored by previous COMPBRN codes.

A model for this mixing process has been proposed by Quintiere and

McCaffrey [12] as- follows:

- 18 -
WJ= p jAjUj

where

Pj = The density of the fluid entrained.

Ai = The effective jet surface area.

UJ = The velocity normal to the jet surface.

With further assumptions [12], the mixing rate can be expressed as

follows:

W= K.j = K 0 --(1 -l _WRhI/1(--•)" WD) WIN

J eTG ZN V.D I

where K is the entrainment coefficient (with suggested value of 0.5).

e

If we neglect the fuel burning rate and forced ventilation and

approximate WIN = WPL, then

w = f(TG, Zn, ZN) WPL

Quintiere and McCaffrey [18] have estimated ratios of the entrainment

flow rate to the incoming flow rate of 0.2 to 1.5, depending on the vent

dimensions, the temperature of the upper and lower layer, the thermal

interface height and the room configuration. In COMPBRN III, we assume

that f(TG, ZD, ZN) is a constant and has a value equal to 0.5; this

value appears to lead to reasonable results for a number of room fires.,

w = 0.5 WPL (16)

Wall Jet Mass Flow Rate (Ww).

At solid vertical boundaries within a compartment, the

downward-directed wall jet, which results from the ceiling jet, is

negatively buoyant relative to the cool air in the lower region. This

wall jet is buoyed back upward and away from the wall. It contaminates

the lower layer air and entrains an additional (i.e., in addition to the

fire plume) amount of lower layer air into the upper layer. Since the

HGLM in COMPBRN III assumes an undisturbed lower region, this

contamination effect is ignored. Whatever the eventual disposition of

the wall flow contaminants, the basic wall flow phenomenon could

significantly alter the rate of development of hazardous conditions in

the enclosure. If, for example, the flow is buoyed upward as a wall

- 19 -
plume and re-enters the upper hot gas layer, then, having entrained

additional lower layer air, the depth of the upper layer grows more

rapidly than it would otherwise, albeit at a reduced temperature and

product concentration. This significantly affects the determination of

what kind of environment a fuel element is exposed to in a fire involved

compartment.

Such flows have been estimated by Jaluria [19] and Cooper [20] for

specific situations. However, an accurate generic assessment of such jet

flow is not available. In COMPBRN III, this wall jet activity is

approximated as

Ww = 0.1 WPL (17)

These entrainment models (the plume entrainment model, Equation 15,

the doorway mixing model, Equation 16, and the wall jet entrainment

model, Equation 17) comprise the air entrainment model in COMPBRN III.

The combined mathematical model to describe the overall air entrainment

is as follows:

*~1/3

WE 0.210 (PLCF)p g Z 1 / (18)

where

PLCF = 1.6 M W

M = 1.28 in normal room floor fire situations.

= 1.10 in no wall boundary fire situations.

= 1.49 if only two walls are present (see Figure 5).

W = 1.0 if the fire source is away frce wall boundaries. = 0.75 if the fire source is next to a wall boundary.

= 0.5 if the fire source is at a corner.

Therefore, in most room fire simulations using COMPBRN III,

PLCF = 2.0, if the fire source is away from the room boundaries.

PLCF = 1.5, if the fire source is located next to a wall.

PLCF = 1.25, if the fire source is at a corner.

Mass Balance Without a Doorway

In the case of fire in a room without any doorway, hot gases are

assumed to completely fill up the room (unless the forced ventilation is

strong enough to pump out all the combustion products and contaminated

air such that hot gas layer does not form at all). The mass balance of

the room is reduced to:

WF + WUV,IN = U,V,OUT (19)

- 20 -
To avoid pressure built up in the room, leakage of hot gases through

the room boundaries is assumed. Equation 19 is used to determine whether

the hot 'gas layer is formed or not. The unknowns of the HGLM are

obtained by solving only Equation 3. The value of PLCF then, has no

significance in the computation of the hot gas layer properties. Thus,

PLCF = 0.0, if there is no doorway.

2.7 THERMAL TRANSFER MODELS

2.7.1 Plume Heat Transfer

The rate of heat gained by the hot gas layer due

flow is approximated by the following expression [4]:

to the fire plume

QPL = (1 - Ir)Q (20)

where

Q = JJWAH

and

Q = The total heat release rate from the fire source.

= Combustion efficiency.

AH = Heat of combustion of the fuel.

WF = Fuel mass burning rate.

= Fraction of Q lost to the environment by radiation from the

r.

combustion zone and the plume. For flaming fires, T is r

typically in the range 0.3 to 0.5 depending on the fuel

properties. This parameter is found to be very sensitive to

what is being burnt.

2.7.2 Heat Transfer Due to Gas Flows

The heat lost from the hot gas layer due to hot gases flowing through

the doorway and forced ventilation system, and the heat gained from

incoming ambient air arriving through forced ventilation can be

quantified by the following equation:

QFLOW = WFLOW Cp AT (21)

where

QFLOW = QOUT or QV as described in Section 2.5.

- 21 -
WFLOW = WOUT or WV as described in Section 2.4.

C = Specific Heat Capacity of hot gas or ambient air.

AT = Temperature difference between the transfer media.

2.7.3 Convective Heat Transfer ( QCONV)

The heat lost from the hot gas layer to the ceiling and walls due to

convection is given by Newton's law of cooling,

QCONV = hc AT AWALL (22)

where

h = Convective heat transfer coefficient.

c

AT = Temperature difference between hot gas and the heat

exchange surface.

AWALL = Heat exchange surface area.

During a room fire, convective heat transfer is dominated by the high

velocity ceiling jet flow; therefore, only the ceiling area is

considered in the computation of the convective heat exchange between

the hot gas and the room boundaries in COMPBRN III.

2.7.4 Radiative Heat Transfer ( andq11 C

Since COMPBRN does not predict particulate concentrations in room

fires, the assessment of radiative heat transfer between the room

boundaries and the ceiling is performed empirically. Similar to the

quantification of convective heat transfer, only the ceiling area is

used to compute the radiative heat loss of the hot gas layer to the room

boundaries. Assuming that the hot gas layer is an infinite slab with

thickness DG and that the absorption coefficient of the hot gas layer is

wavelength independent (i.e., following the gray body approximation),

the radiative heat lost from the hot gas layer to the ceiling is given

by the Stefan-Boltzmann law:

QRAD = ACEIL FHGL-CEIL (TG - TCEIL) (23)

where F is the effective shape factor.

- 22 -
Further assumming that only surfaces are responsible for the

radiative heat exchange between the hot gas layer and the ceiling (which

is also assumed to be an infinite gray slab), the radiative heat

transfer can be expressed as follows [21]:

ACEIL (TG EIL (24)

QRAD ( WE G + l/W - 1)

where

E W = Emissivity of ceiling.

= 1 - PW (pW is the wall reflectivity).

eG = Emissivity of hot gas.

= 1 - exp(-kfDG); (kf is the gas absorption coefficient).

= a Go the absorptivity of the hot gas layer (following the

gray body approximation approach).

a = Stefan-Boltzmann constant.

= 5.6697xi0 8) W/m1K4

S,%

The radiative heat flux, qCEIL' which a fuel element outside the hot

gas layer receives (see Figure 7) can be expressed as:

• to = It + t!

qCEIL = q CEILING + qHGL (25)

where

-of

q CEILING

"1

EXTC - G - (I + lI/ - 1) G W - a G) +

(1EG+ 1/e~ - 1) aTCEIL ( 1 G

+

4 1

+ a TG {G " I/eG + 1/cw - 1 ] Cl - aG)

The absolute radiative heat flux a fuel element

receives *due to reflection of radiative energy from

external sources and to reflection of radiation from

the hot gas layer to the ceiling.

- 23 -
qHGL ' G •G

The absolute radiative heat flux the hot gas layer

emits.

- 24 -
Chapter 3

SUMMARY OF MODIFICATIONS

In this chapter, we outline the most important modeling changes to

COMPBRN I which are incorporated in COMPBRN III. Some, but not all of

these changes were included in COMPBRN II; they are discussed here for

completeness. These changes are grouped by the subroutine in which they

appear. The numerous NAMELIST, DIMENSION, COMMON, and CALL statements

needed to help implement these changes are not listed in this chapter,

nor are the numerous FORMAT statement changes, used to improve the

appearance of the output.

SUBROUTINE MAIN

1. A set of simple error checking statements has been added.

These primarily check for out-of-bound problem dimensions

and for non-physical real variable values. In general,

parameter input values less than or equal to zero should

be avoided unless specifically intended. If any input

errors are discovered, the job will be terminated.

2. The effective fuel cell radius computations have been

corrected. They now are

V Area/v for horizontal objects

R =

R Width/2 for vertical objects

In previous versions 'of COMPBRN, these formulae were

reversed.

3. The problem input parameter list has been expanded and is

discussed in Chapter 5. Changes have also been made in

the list of variables which may be output. Specifically,

consider a fuel cell whose surface temperature is T . The s

environment temperature is Te, the total impinging

radiative heat flux from other objects in the room is

.011

q EXTC"

COMPBRN III allows the user to output

a) qEXTC (called QEXT).

- 25 -
b) h (the local heat transfer coefficient HCOEF).

c) Te (called TSURR).

.14

d) zqe + acT e + hT (called QEXTOT).

.11 4 4

e) zq8 + ot(Te - T ) + h(Te - Tc) (called QEXCAL).

.11 4 4

f) eq + oE(Te - T ) + h(Te - Ts) (called QEXNET).

where

z = fuel emissivity

T C = fixed "calorimeter temperature" (CALTEM) specified

by the user in NAMELIST &MISC.

If T is set equal to room temperature, QEXCAL

represents the "cold wall heat flux" at the fuel

cell's location.

4. Unlike the previous versions of COMPBRN, COMPBRN III

assumes that the steady state is achieved within the first

time step (typical value is 60 seconds), instead of

instantaneously.

SUBROUTINE SOURCE

1. The gas emissivity is updated at each time step to provide

improved accuracy,

= 1 - exp(kfDG)

where

kf = Gas absorption coefficient.

DG = Thickness of hot gas layer.

2. Steady state is assumed to be formed within the first time

step instead of instantaneouly after the fire ignition.

SUBROUTINE TRANSF

1. In COMPBRN I, a fuel cell's environment was completely

specified by the total heat flux impinging on the fuel

cell. In COMPBRN III, the environment is specified by the

radiative heat flux from discrete objects (QEXT), the fuel

cell environment temperature (TSURR), and the local heat

transfer coefficient (HCOEF). TRANSF has been modified

accordingly to compute and store all three variables. The

latter two, TSURR and HCOEF, are functions of the fuel

cell location, i.e., whether it is in the flame, plume,

hot gas layer, or cold layer.

- 26 -
2. The plume temperature correlation has been changed. The

new correlation developed by Zukoski.et al. [22] is:

T/3 (1TdrQ )2/3 5/3

TPL,MAX = T {l + 9.11 g (T Z

Assuming a Guassian velocity and density (temperature)

profile, the mean plume temperature is 1//2 times the

maximum plume temperature as described above.

3. The correlation for the heat transfer coefficient within

the fire plume has been modified. In Siu [3] the

correlation used in COMPBRN I was derived using an average

over the surface of the fuel cell. In COMPBRN III, values

of temperatures and heat fluxes at distinct points are

used. To make the calculation of the heat transfer

coefficient consistent with this approach, the original

correlation, which was used as the basis for the averaging

procedure of Siu [3], is directly adopted.

SUBROUTINE IGNIT

1. This subroutine has been revised to allow the calculation

of the temperature profile within all objects. In

COMPERN I, an analytical approximate solution for the time

to reach a specified surface temperature was employed. As

discussed by Chung et al. [7], this model did not account

for the surface heat losses to the environment. In

COMPBRN III, the temperature profile is now solved

numerically (by calling SUBROUTINE DIFFUS) for every

object, using an exact boundary condition for the exposed

face. (Note that DIFFUS was available in previous COMPBRN,

but was only employed for calculating the temperatures

within the compartment walls and ceiling).

SUBROUTINE OUTPUT

1. This subroutine now allows the user to output 17

variables, instead of 11, as described in Section 5.18.

SUBROUTINE BARR

1. This subroutine, which was used in previous versions of

COMPBRN to calculate the steady-state temperature in a

slab, is no longer required.

SUBROUTINE. CYLPAR

1. This subroutine, which is used to compute the shape factor

- 27 -
from a vertical cylinder to a differential surface

parallel to the cylinder's base, is a corrected version of

the subroutine documented by Siu [7].

SUBROUTINE DIFFUS

1. Changes have been made to allow treatment of more general

boundary conditions for the back face of the slab. This

is useful for treating barriers (a barrier's back face is

assumed to be exposed to the same environment temperature

at its front face). The method of solution of the

transient heat conduction equation is described in Chung

et al. [7].

SUBROUTINE CEILNG AND ZDNEW

1. These subroutines, which were used in previous versions of

COMPBRN to calculate the ceiling hot gas layer properties,

are replaced by subroutines CGAS, CNEWTN, CSOLVE and

CGASHT.

SUBROUTINE CGAS

1. This subroutine replaces the subroutine CEILNG to estimate

the hot gas layer properties. CGAS is able to predict the

unknown properties in a wider range of room firs scenarios

than the previous COMPBRN.

2. The presence of strong forced air ventilation may affect

the location of the thermal interface. If a large amount

of hot gas is pumped out of the room through the ceiling

vent, the hot gas layer thermal interface may be formed at

the door soffit region or may not form at all. CGAS

identifies such phenomena by comparing the plume mass flow

going into the hot gas layer at different elevations (at

the door height and the ceiling) with the net ventilation

outflow rate through the ceiling vent. Figure 8 depicts

the flow chart of the logical decision in the subroutine

CGAS.

3. The room is assumed to be rectangular in shape; if other

room configuration is used, this assumption can be changed

by replacing a statment in CGAS.

4. CGAS calls subroutines CNEWTN, CSOLVE, CGASHT, and

function subroutine RADEQ to compute the unknowns of the

hot gas layer properties. With the above subroutines, CGAS

can be run independently from the rest of COMPBRN III to

estimate the properties of the hot gas layer formed in

room fires. Part of the simulations performed in

Chapter 4 employ such a program.

- 28 -
5. CGAS computes the heat flux that a fuel element receives

due to external heat sources, the hot gas layer and the

ceiling (Equation 25).

SUBROUTINE CNEWTN

1. This is a new subroutine employed by COMPBRN III to search

for the root (TG) of the mass flow balance equations

(Equation 1 and 2) utilizing a Newton-Raphson numerical

scheme.

2. If the new iterated root is out of the permissible range,

a bisection method will be used to obtain a better

estimate of the unknown. A warning message will be

printed if such situations arise.

3. The iteration limit has been set to 30 and can be changed

easily. If this limit is exceeded, a best guess solution

will be provided and a warning message will be given.

SUBROUTINE CSOLVE

1. This subroutine, when called by CNEWTN, estimates the

first derivatives of the mass flow equations using a

forward different (two point) scheme.

SUBROUTINE CGASHT

1. This subroutine updates the thermal interface heights (ZD,

ZN) by solving the thermal batance equation using the

estimated hot gas layer temperature (TG) from the previous

time step.

- 29 -
Chapter 4

SIMULATION OF EXPERIMENTS

In this chapter COMPBRN III is compared to COMPBRN II by simulating

cable tray experiments performed by Underwriters Laboratories (UL) for

Sandia National Laboratories (SNL) [15]. The room fire experiments

performed by Quintiere et al. [13] are also simulated.

4.1 SIMULATION OF SNL UL CABLE TRAY FIRE EXPERIMENTS

In [7], Chung et al. simulate the room fire experiments conducted by

SNL/UL using COMPBRN II. The goal of these experiments is to test the

validity of the claim that a 6.10 m (20 ft) separation distance without

intervening combustibles or fire hazards (as specified by Section III.G.2.b of Appendix R to 1OCFRSO) would be sufficient to

ensure that at least one train of cables would remain functional [15].

The results provided by [15] are in such a form that a detailed

comparison with the predictions of COMPBRN II and III can be readily

made. In [7], three of the four preliminary cable tray fire experiments

are simulated. COMPBRN II gives satisfactory results in Experiments 1

and 3, while it under-predicts the results of Experiment 2 and does not

generate a solution for Experiment 4. COMPBRN III is able to simulate

all four experiments with satisfactory results. Significant improvement

can be seen by comparing the simulation results.

4.1.1 Description of the Cable Tray Tests

The room configurations of Experiments 1-4 are modeled as shown in

Figures 9 to 11. In all experiments, the compartment is 4.27 m (14 ft)

wide and 3.05 m (10 ft) high. In Experiment 1, the length of the

compartment is 9.14 m (30 ft) and the heptane tank is placed 1.52 m

(6.5 ft) from the left wall, whereas, in experiments 2 to 4, the

compartment is 7.62 m (25 ft) long and the heptane tank is placed

against the wall. The heptane tank contains a.fuel load of 10 gallons and is common to all experiments. One difference between the room

configurations of Experiments 1 to 4 is the size of the compartment door

opening: Experiments 1 and 2 have a 2.44 m (8 ft) by 2.44 m (8 ft) door,

Experiment 3 has a 1.22 m (4 ft) by 2.44 m (8 ft) door, and Experiment 4

has a sealed off doorway.

The horizontal cable trays are separated from the heptane pool fire

by a horizontal distance of at least 6.1 m (20 ft). The two trays, one

- 30 -
of which is directly above the other, are located in the far corner,

close to the ceiling [0.305 m (1 ft) and 0.458 m (1.5ft) below] and

above the door. Instruments are placed throughout the compartment and

within the cable trays to measure the external heat fluxes and the gas

and cable jacket temperatures.

4.1.2 Comparison of Simulation Results

The hot gas layer temperatures, heat fluxes, and cable jacket

temperatures predicted by COMPBRN II and III are compared with observed

values from Experiments 1 to 3 in Figures 12 to 20. Parameters used by

both COMPBRN II and III are kept constant to provide a meaningful

comparison. Two values (0.7 and 1.0) of the fuel combustion efficiency

(q) are used in the comparisons to serve as a general guideline of the

codes' sensitivity and performance. The value % - 1.0 implies perfect

burning with a free supply of oxygen and is an ideal value. During an

actual fire, local oxygen starvation prevents complete combustion; thus,

ideal combustion is rarely seen unless air with enriched oxygen is

supplied. Heptane is a highly flammable substance with combustion

efficiency ranging from 0.7 to nearly 1.0, therefore, the actual

combustion efficiency should be somewhere within this range. The values

of the common parameters used in the comparison are shown in Table 1 and

the differences in some important input parameters are shown in Table

2. These parameters are empirical and depend upon such detailed

characteristics of the fire scenario as the location of the fire source

with respect to the room boundaries and door. In general, these

parameters are not well known for an arbitrary scenario; uncertainties

in their values must be accounted for when analyzing the behavior of

fire in a room.

The following observations can be deduced from the comparison:

1.1 In the simulation of the hot gas layer temperature,

COMPBRN III is able to bracket the actual asymptotic

temperature by using n = 0.7 and 1.0 in all three

experiments, while COMPBRN II underpredicts the steady

state results (see Figures 12, 15 and 18).

2. Both versions of COMPBRN perform reasonably well in

predicting the measured heat flux and the lower tray cable

jacket temperature (Figures 13, 14, 16, 17, 19 and 20).

3. Predictions performed by COMPBRN III using n = 1.0 (ideal

combustion) can be interpreted as the upper bound of the

experiment data. This assumption is clearly verified in

Figures 12-20.

Using the parameters listed in Table 3, COMPBRN III is found to

provide excellent results in all experiments including Experiment 4,

- 31 -
TABLE 1

Common Parameters Used in the Simulation Comparison

Combustion Efficiency (EFF) .............................. 0.7 and 1.0

Convective Heat Transfer Coefficient (HCEIL) ............. 10.0

Fraction of Heat Lost by Radiation (GAMMA) ............... 0.4

Gas Absorption Coefficient (GABSRP) ...................... 1.4

TABLE 2

Other Parameters Used in the Simulation Comparison

COMPBRN II

Doorway Coefficient (DCF) .................................. 0.7

Plume Entrainment Coefficients (PLCF1 and PLCF2) ........... 1.5 and 0.5

Convergence Acceleration Parameter (THETA) ................. 1.5

COMPBRN III

Doorway Inflow Coefficient (DCFIN) ......................... 0.6

Doorway Outflow Coefficient (DCFOUT) ....................... 0.7

Plume Entrainment Coefficient (PLCF) for Experiment 1 ...... 2.0

Plume Entrainment Coefficient (PLCF) for Experiment 2-3 .... 1.5

which COMPBRN II is unable to simulate. In this experiment, the absence

of a doorway gives poor air ventilation and the combustion efficiency is

believed to drop to as low a value as 0.65. The other three experiments

are well ventilated by the doorway, giving a combustion efficiency of

around 0.85. The results of such simulations are shown in Figures 21 to

32.

In these simulations COMPBRN III predicts the steady state values of

the experiments with high accuracy. In Experiment 4 the fire is

originally surface controlled, and as the oxygen content in the room

decreases due to combustion, the fire changes to ventilation controlled

burning and eventually self-extinguishes.

- 32 -
TABLE 3

Parameter List for Simulation of Cable Tray Fire by COMPBRN III

Air Entrainment Coefficient (PLCF) (Experiment 1) ......... 2.00

Air Entrainment Coefficient (PLCF) (Experiment 2-3) ....... 1.50

Air Entrainment Coefficient (PLCF) (Experiment 4) ......... 0.00

Combustion Efficiency (EFF) (Experiment 1-3) .............. 0.85

Combustion Efficiency (EFF) (Experiment 4) ................ 0.65

Convective Heat Transfer Coefficient (HCEIL) .............. 10.0

Doorway Inflow Coefficient (DCFIN) ........................ 0.60

Doorway Outflow Coefficient (DCFOUT) ...................... 0.70

Fraction of Heat Lost by Radiation (GAMMA) ................ 0.45

Gas Absorption Coefficient (GABSRP) ....................... 1.30

4.2 SIMULATION OF STEADY-STATE FLOW EXPERIMENTS

Fifty-five steady-state experiments (in a relatively small room) have

been conducted by Quintiere et al. [13] to study the flow induced by a

simulated pool fire in a compartment under conditions characteristic of

the developing fire period. The steady-state flow experiments are

conducted in a room as shown in Figure 33. The light-weight walls and

ceiling are covered with a ceramic fiber insulation board to establish

near-steady conditions within 30 minutes following ignition of a 30 cm

diameter porous plate diffusion burner. The burner is supplied with

commercial grade methane at a fixed rate.

Movable bidirectional velocity probes and bare wire thermocouples

within the room opening measure the velocities and temperatures of the

opening flows on a two-dimentional grid of 28-144 points depending on

the size of the opening. A fixed array of aspirated thermocouples in

the front corner of the room measure the gas temperature profile. A

similar array of bare-wire thermocouples measure the near-ambient

temperature profile within the large well-ventilated area outside the

room. The experiments are conducted using different fire strengths

(31.6, 62.9, 105.3, and 158 kW), and different door and window sizes.

Since these experiments do not involve the assessment of damage of

components inside the room, it is not necessary to run the entire

COMPBRN III code to simulate them. A separate program has been written

utilizing the subroutines CGAS, CNEWTN, CSOLVE and CGASHT from

COMPBRN III to simulate ten out of the fifty five experiments conducted.

The predicted hot gas layer properties (TG, ZD and ZN) are compared to

the measured steady-state values. The results are shown in Figures 34

to 36.

Since the fire source is a methane diffusion burner, the combustion

efficiency is close to 1.0. The doorway coefficients are calculated from

the measured mass flow rates and the theoretical mass flow rates; these

values are different in each experiment. The input parameters are

- 33 -
listed in Table 4. The values of the parameters DCFIN and DCFOUT used

are listed in Table 5. These values are obtained by substituting the

experimental data into Equations 10 and 11.

TABLE 4

Parameter List for Simulation of the Room Fire Experiments

Air Entrainment Coefficient (PLCF) ........................ 2.00

Combustion Efficiency (EFF) ............................... 1.00

Convective Heat Transfer Coeffieient (HCEIL) .............. 10.0

Doorway Inflow Coefficient (DCFIN) ........................ Varies

Doorway Outflow Coefficient (DCFOUT) ...................... Varies

Fraction of Heat Lost by Radiation (GAMMA) ................ 0.15

Gab Absorption Coefficient (GABSRP) ....................... 1.30

TABLE 5

Values of DCFIN and DCFOUT Used in Table 4

Experiment # DCFIN DCFOUT

1 0.73 0.70

2 0.87 0.73

3 1.06 0.75

4 1.01 0.76

5 1.02 0.75

6 1.20 0.72

7 0.86 0.71

12 1.04 0.70

13 1.60 0.69

14 1.07 0.90

In this simulation, COMPBRN III is able to predict the experimental

results with high accuracy when the values of the input parameters DCFIN

and DCFOUT are well known. This clearly reveals the potential of

COMPBRN III in the prediction of room fires. It also shows that future

research on the estimation of DCFIN and DCFOUT for arbitrary fires will

be helpful in predicting the behavior of these fires.

- 34 -
Chapter 5

USERS GUIDE TO COMPBRN III

The current version of COMPBRN III can be run on IBM, CDC, and Prime

computers (a PROGRAM statement is needed for the CDC machines, however,

and NAMELISTS for both the CDC and Prime machines should be preceded by

"$" instead of "&"). Running time on a mainframe computer. are relatively

short (on the order of a few seconds) for most problems; they &re

directly related to the number of time steps and the total number of

fuel cells used in the scenario of interest.

In this chapter, we describe the input and output for COMPBRN III. We

also provide some notes which are intended to aid the user in modeling

compartment fires using COMPBRN III.

5.1 ADDITIONAL MODELING DURING APPLICATION

Because there are a number of assumptions implicit in COMPBRN III's

various models, further modeling of the compartment is required before

an actual fire can be analyzed.

In general, a compartment fire will involve a fuel bed of arbitrary

geometry, location, and orientation. Furthermore, the fuel bed may be

composed of a number of different fuel types, the relative amounts of

which may vary with location.

I

In preparing the input data for COMPBRN III, the analyst must proceed

as follows:

1. A Cartesian coordinate system is defined with respect to

some arbitrary location in the compartment. The z-axis

always represents the vertical direction. The compartment

walls and ceiling are rectangular in shape, and are

parallel to the planes defined by the coordinate axes.

2. The fuel bed is modeled with a series of homogeneous,

two-dimensional rectangular slabs, called "super modules."

The long axis of each slab defines its "direction," and

must be parallel to one of the coordinate axes. The

direction normal to the slab's face defines its

"orientation," and also must be parallel to one of the

coordinate axes. The imposition of a regular geometry on

the fuel bed is not always a severe modeling restriction,

since a physical fuel element can be modeled as a number

- 35 -
of contiguous super modules. However, COMPBRN III is

presently incapable of modeling fires progressing along an

inclined surface.

3. The super modules are then further discretized (along the

direction of their long axes) into contiguous fuel

packets, called "fuel cells." These fuel cells should be

almost square in dimension when modeling horizontal fuel

beds, since COMPBRN III's flame models for this

configuration are based on results from flames over nearly

square or round pools of fuel.

4. The fuel bed is further modeled using the "porosity

factor" and the "communication matrix." The porosity

factor is required since a ''rough'' fuel element (e.g.

cables in a cable tray section) will have more surface

area available for burning than provided by the

representing flat super module of the same nominal

dimensions. This factor is simply the actual area

available for burning per unit base (super module) area.

The communication matrix is constructed by the analyst.

It allows him to specify which super modules or fuel cells

are contiguous, and which ones cannot transmit heat to

others (due to intervention by other fuel elements,

barriers, etc.). If instructions to the contrary are not

provided, all fuel elements are assumed to be able to

"fcommunicate with," i.e. transmit heat to, all other fuel

elements.

The porosity factor and the communication matrix allow

some fine-tuning of COMPBRN III's simple modeling. it

must be realized however that the memory space requirement

for the communication matrix expands as the square of the

number of fuel cells, and this is a practical limiting

factor in the ability of COMPBRN III to handle complex

problems in detail.

5.2 PROGRAM FLOW

COMPBRN III is a single precision FORTRAN computer code which is

divided into a main program, a group of primary subroutines, and a

number of auxiliary subroutines and function subprograms. The modular

nature of the code is not necessary for execution efficiency, but is

intended to allow the analyst to incorporate improved models as they

become available. All of the subroutines incorporate

variably-dimensioned arrays; if the fuel bed configuration requires a

large number of fuel cells, only the main program need be modified and

recompiled.

- 36 -
As can be seen in Figure 37, COMPBRN III execution begins with the

MAIN program. Fuel bed geometry, initial fire characteristics, fuel

type characteristics, communication matrix data, compartment parameters,

model variation factors, and output format data are read using NAIIELIST

directed input. A simple input error checking routine is employed to

determine if any obvious errors have been made. MAIN calls subroutine

INCHK, in which various portions of the input data can be printed for

verification, and then the two initialization subroutines, INIT and

TINIT.

After problem definition and initialization is complete, subroutine

SOURCE is used to compute the fuel burning rate, the resulting rate of

heat output, and the flame height, for each burning fuel cell. The

models vary according to the degree of compartment ventilation and

whether the fuel element is horizontal or vertical. The strength of

each element as a source of heat flux is then calculated. The auxiliary

subroutine CGAS may be called by SOURCE to determine the heat flux from

the ceiling. Subroutine CGAS, if called, requires the use of function

subroutine RADEQ, which solves a special version of the quartic equation

to obtain an improved value for the hot gas layer temperature,

subroutine CGASHT, which updates the height of the natural density plane

within the compartment given an updated hot gas layer temperature,

subroutine CNEWTN, which solves for the root of the coupled equations

and subroutine CSOLVE, which solves for the mass flow rates.

Subroutine TRANSF follows SOURCE, and transfers the heat fluxes from

the various sources to the target elements via convective and/or

radiative pathways. The *shape factors used in the flame radiation

transfer calculations are computed using the function subroutines CYLPAR

and CYLPER. The shape factors for transfer from rectangular sources

(e.g. the ceiling) were computed earlier using SHAPE and RECT, and are

stored in the communication matrix. Special models are used to account

for the feedback radiation of a flame over a vertical slab back to the

slab, and for the conduction of heat to contiguous (and non-burning)

fuel elements.

Subroutine IGNIT is used to determine if non-burning fuel elements

have absorbed enough heat to ignite. This subroutine employs the

subroutine DIFFUS to solve the transient heat conduction equation (slab

geometry) for every object modeled (except for detectors, which are

described in Section 5.11). Subroutine OUTPUT prints data desired by

the analyst for each time step.

- 37 -
5.3 PROGRAMMING NOTES

As discussed in Chapter 1, COMPBRN III, as well as COMPBRN I and II,

performs best in situations where the fire is fairly small with respect

to the room. The quantitative relationship between the fire size and

room size which determines the boundary of the region of problems for

which COMPBRN III is applicable has not yet been established. This

relationship is also a function of the room door size, the forced

ventilation rate for the room, and the location of the fuel in the room.

To the user, this means that solution convergence may not be obtained

in a limited number of cases. The following notes, derived from the

experience of others who have used the code, as well as that of the

authors, may be useful:

1. The code will almost always achieve a reasonable solution

if the effects of the enclosure are neglected (i.e., IROOM

is set equal to zero)

2. Failure when IROOM=O will occur when the midpoint of a

fuel cell falls within the effective radius (R = 4Area/i)

of a burning fuel cell and the z-coordinates of the two

cells are identical. This condition will also lead to

failure when IROOM=1, and can be avoided by suitably

chosen problem input parameters.

3. Oscillations may occur in the solution of the fuel cell

surface temperature (subroutine DIFFUS) if the fuel cell

is immersed in a very high temperature flame. This

condition, which may occur regardless of the values

specified for IROOM, can be remedied by ensuring that

81*THK*DELT

DENS*SPHT'fY(SDEP) < 0.1

where the variables are explained in Section 5.11. In general,

the solution accuracy improves as the above ratio decreases.

4. When IROOM=-1, failure may occur if the fire is too small

or too large with respect to the room or if the only

source of flames is located too high within the room.

- 38 -
5.4 OUTPUTS

COMPBRN III prints two sections of output data. The first is used to

verify the problem input data, while the second lists user-specified

variables during computations.

The input data check is regulated using the indicator variable

INCHCK. If INCHCK equals 0, only heading material and the model

variation parameters stored in the array FCTR are output. These

variation parameters can be used to multiply the computed results of a

particular correlation, if individual model uncertainties are to be

propagated through the code. A list of the models which can be modified

with FCTR is given in Section 5.17. If INCHCK equals 1, the physical

parameters characterizing the fuel are also output. If INCHCK is Cot.

equal to 0 or 1, all input data, with two exceptions, are printed. In

the case of the super module coordinates, the super module midpoints

input (SMX, SMY, and SMZ in Section 5.9) are not printed when INCHCK is

not equal to 0 or 1. Instead, the code outputs the coordinates of the

first fuel cell in each super module, where the cells are numbered as

described in Section 5.9. Similarly, while the mass of each super module

is an input parameter, the code prints out the mass of each fuel cell in

the super module.

The output data listed each time step is specified with the indicator

variables IOUTPT and NSMOUT, and the arrays MOUTPT and MSMOUT. IOUTPT

determines the number of output variables to be printed, and the

elements of MOUTPT specify which variables are to be printed (see

Section 5.18). Similarly, NSMOUT determines the number of super modules

for which output data is to be printed, and the elements of MSMOUT

specify which particular super modules are included in this number. If

IOUTPT and NSMOUT equal 0, only the elap&-d time since initiation and

the total mass burning rate in the compartment are printed. If IOUTPT

equals 0 and NSMOUT is not equal to 0, the elapsed time, the burning

rate, apd a logical variable array, LBURN, which specifies which fuel

cells (if any) in the specified super module are burning, are printed.

5.5 INPUTS

COMPBRN III requires a large amount of input data to specify each

particular problem. These data are read using NAMELIST format, and the

NAHELISTs must be input in the order presented. If there are any errors

in the input file, the computer bypasses execution.

With respect to the problem input, the COMPBRN III changes to

COMPBRN I are small. The variables EFF and FTDAM (the combustion

efficiency and fuel damage temperature) have been added to NAMELIST

&FUELT, the variables HROOM and CALTEM (the heat transfer coefficient

outside the hot gas layer and plume, and the temperature of any

calorimeter) have been added to NAMELIST &MISC, and the definitions of

the entries in the FCTR and MOUTPT arrays (NAMELISTS &MODVAR and &OUTF)

have been modified, in NAMELIST &ROOM, variables PLCF1 and PLCF2 are

- 39 -
replaced by PLCF, variable DCF is replaced by DCFIN, and DCFOUT.

Variable THETA is deleted from this NAMELIST.

This data block defines parameters which are in effect for all of the

jobs to be performed. All subsequent data blocks apply only for the

particular job being executed.

5.6 OVERALL JOB PARAMETERS (&STRT)

Data Set Members

* NJOB = The number of jobs to be run. In general, the entire set of

input data (starting with NAMELIST &SIZE) must be repeated

for each job.

* NTIME = The maximum number of time steps for each job. Jobs may end

earlier if certain iterative calculations do not converge

sufficiently quickly or if all fuel which can be ignited

has been exhausted.

* NREAD = The logical unit number off which remaining data is to be

read. (Default = 5)

* NWRITE = The logical unit number on which output is to be written.

(Default = 6)

O*DELT = The time step increment in seconds. (Typical value = 60.0)

5.7 INDIVIDUAL JOB PARAMETERS (&SIZE)

The limits given in this data block are for the COMPBRN III version

currently compiled.

Data Set Members

" NSM = The number of super modules. (NSM S 30)

• NFUEL =The maximum number of fuel types. (NFUEL : 5)

* NCOM = The number of entries for the construction of the adjacency

portion of the communication matrix ICOMM. See Section 5.13

(NCOM S 30). (Default=O)

* NNCOM = The number of non-communicating entries for the

construction of ICOMM. See Section 5.14 (NNCOM S 200).

(Default=0)

" NPILOT = The number of fuel cells initially on fire (NPILOT S 10).

" IROOM =The indicator variable which determines if compartment data

are to be included or not. This latter option is useful

when the fire is sufficiently small with respect to the

room such that enclosure effects can be neglected.

IROOM=-1 => compartment data are input.

IROOM0I => no compartment data are input.

In the output, this choice is indicated indirectly by

printing the input parameters specified in NAMELIST &ROOM.

- 40 -
* INITG = The indicator variable which shows if the hot gas layer has

some initial characteristics and/or if the initial external

heat fluxes are non-zero. Input only if IROOM = 1.

INITG=l => Initial values for gas layer and/or heat

fluxes are input.

INITGA1 => TG (Gas Layer Temperature) = RTEMP

DG (Gas Layer Thickness) = 0.0 m

QEXT (External Heat Fluxes for All

Fuel Elements) = 0.0 W/m2 .

5.8 TITLE CARD

The first 80 characters on this card will be reproduced as the job

title in the code output.

5.9 FUEL BED DEFINITION (&FUELB)

This data block must be entered once for each super module, i.e. NSM

times. The first entry corresponds to super module number 1, the second

to module 2, etc. Except for SMX, SMY, and SMZ, negative values or zero

values are not allowed.

Data Set Members

* SMX = x-coordinate midpoint of super module (m).

* SMY = y-coordinate midpoint of super module (m).

* SMZ = z-coordinate midpoint of super module (m).

* SLNG = Super module length (m).

* SWID = Super module width (m).

* SDEP = Super module depth (see point 3 of Section 5.1).

* SMASS = Super module mass (kg).

The fuel mass affects the duration of burning. For

nonburning items, this variable is not used. Note that

COMPBRN III prints out the fuel mass per fuel cell, not

SMASS.

* SPOR = Super module porosity factor f (Dimensionless). p

* SLOSS = Undefined variable. (This variable is not used).

* NFCL = Number of fuel cells in super module. Should be set equal

to unity for a ceiling.

* IORNT = Orientation of super module.

IORNT=I => Normal axis is in the x-direction.

IORNT=2 => Normal axis is in the y-direction.

IORNT=3 => Normal axis is in the z-direction.

* IDIREC = Direction of super module.

IDIREC=l => Long axis is in the x-direction.

IDIREC=2 => Long axis is in the y-direction.

IDIREC=3 => Long axis is in the z-direction.

* IFTYP = Super module fuel name/identification number, used as super

module fuel type location identifier. This parameter

- 41 -
identifies the particular location in the array IFUEL of

NAMELIST block &FUELT (Section 5.11) which corresponds to

the fuel for the super module described.

Example: "IFTYP=3" means that the super module fuel is type 3, where

fuel type 3 is defined by position 3 of array

IFUEL. Note that IFTYP : NFUEL.

COMPBRN III will automatically compute the locations of the fuel

cells in each super module. It will also number the fuel cells, the

numbers increasing with distance in the direction of the long axis.

Thus, if the super module is directed along the x-axis, a fuel cell at

X = 3.0 will have a lower number than a fuel cell at X = 5.5.

Note that a warning message will be given if IDIREC and IORNT have

the same value.

5.10 PILOT FUEL PARAMETERS (&PILOT)

COMPBRN III assumes that a compartment fire starts on top of a small

number of selected fuel cells in the fuel bed. These initial fires,

called pilot fires, may involve materials not comprising the main fuel

bed. For example, a segment of cable tray may be overlaid by an amount

of oil which is used to initiate the compartment fire. The location of

this pilot fire is, however, treated as being identical with the

location of the underlying fuel cell.

Each item in this data block is an array, with the first entry

corresponding to the first pilot fuel cell, the second with the second

cell, and so forth. NPILOT entries should be made for each array.

Data Set Members

" IPIL = Array listing the super modules of the pilot fuels.

" JPIL Array listing the particular fuel cells (within the given

super module) which are assigned pilot fires.

Example: If NPILOT=-2, IPIL=(3,2), and JPIL=(4,5), this

means that there are two pilot fires, the first being

located on the top of the fourth fuel cell of the third

super module, and the second being on top of the fifth fuel

cell of the second super module.

• IPFUEL = Pilot fuel type array. This entry corresponds to IFTYP

defined in Section 5.9. Fuel types are numbered

consecutively. Thus, if the third entry of IPFUEL is '5',

this means that the third pilot fire involves fuel type 5.

' PMASS = Pilot fuel mass array (kg).

Note that pilot fuels are considered separately from the

underlying main fuel. PMASS kg of fuel are assumed to lie

on top of the fuel cell, regardless of what SMASS is. PMASS

can not be negative or zero-valued.

- 42 -
5.11 PHYSICAL FUEL PARAMETERS (&FUELT)

Each of the items in this data block represents an array of dimension

NFUEL. The first entry in each array corresponds to fuel type 1, the

second entry corresponds to fuel type 2, and so forth.

Data Set Members

IFUEL =Array of identification numbers (names) assigned to each

fuel type.

0 < IFUEL(I) < 10 => Super module is combustible

10 :5 IFUELCI) < 20 =>

20 S IFUEL(I) < 30 =>

30 <- IFUEL(I) < 40 =>

40 S IFUEL(I) < 50 =>

fuel.

Super module is a detector

(useful for measuring teat

fluxes and local temperature).

Super module is a wall.

Super module is a thermal

barrier.

Super module is the room

ceiling.

Note that the room ceiling can only be modeled with one

super module and that those super modules modeling the

ceiling and the walls may only have one fuel cell each.

Detectors are passive objects used to indicate the

thermal environment at their location. They are not used in

any source or response calculations. Barriers are slabs

whose back sides may act as heat sources. The front and

back of the barriers are exposed to the environment

temperature; their prime function is to block radiative

heat fluxes.

In the following list, entries must be provided for all fuel types,

but realistic entries are optional for the ranges of IFUEL noted below

(where for notational simplicity, we let K=IFUEL(I)J. Note: Do not

input O's for nonessential parameters.

* DENS = Density (kg/Mr); (10 5 K < 20).

• SPHT = Specific heat (J/kgK); (10 1 K < 20).

* THK = Thermal conductivity (W/mK); (10 : K < 20).

" HEAT = Heating value (J/kg); (10 ý K < 50).

* FIGTP = Piloted ignition temperature (K); (10 S K < 50). This is

used when flames touch a combustible.

* FIGTS = Spontaneous ignition temperature (K); (10 < K < 50). This

is used when the combustible is not touched by any flame.

* FTDAM = Damage temperature (K); (10 5 K < 50).

• BRATV = Ventilation controlled burning rate constant CV

(dimensionless); (10 S K < 50).

parameter only when IROOM=I.

Suggested values:

0.12 for wood,

0.025 for oil,

and 0.05 for cable.

The program uses this

- 43 -
° 11

BRATSO = Specific burning rate constant m 0 (kg/mls); (10 S K < 50).

0 BRATS1 = Surface controlled burning rate constant CS (kg/J);

(10 : K < 50).

" EFF = Combustion efficiency (dimensionless); (10 : K < 50).

Suggested values:

0.8 for heptane in well ventilated condition;

0.6 for heptane in poorly ventilated condition;

0.035 for cable, PMMA.

* GAMMA = Fraction of flame heat released as rad

(dimensionless); (10 S K < 50).

iation

* FABSRP = Absorption coefficient for flame (m 1);

(10 : K < 50).

" REFL = Reflectivity (dimensionless); (10 : K < 20).

gases

5.12 MISCELLANEOUS DATA (&MISC)

Data Set Members

* RTEMP = Room temperature (K). (Default = 298.0)

• FLCF = Heat transfer coefficient for heat transfer in a flame

(W/mzK).

" HROOM = Convective heat transfer coefficient outside of hot gas

layer (W/m2K).

" CALTEM = Calorimeter temperature (K). Used in computation of net

heat flux to a calorimeter.

5.13 COMMUNICATION DATA (&SEE)

This data block is used to input information defining if a given fuel

cell touches another fuel cell. This affects the heat transfer models

used, transfer between contiguous cells being somewhat greater than

transfer between disconnected cells.

COMPBRN III automatically establishes adjacency for consecutive fuel

cells in each super module. Furthermore, by default, all fuel cells can

transmit heat to all other fuel cells (i.e., they "communicate"). The

purpose of this data block is to define some exceptions to these general

rules (non-communication is handled in Section 5.14). NCOM entries must

be made, one for each exception.

- 44 -
Data Set Members

* IV = 4 element array containing adjacency data. If fuel cell j of

super module i is adjacent to fuel cell 1 of super module k,

IV would be (i,j,k,l). If super modules i and k are parallel,

have the same number of fuel cells, are of the same length,

and are adjacent, IV would be (i,999,k,O). The '999' tells

COMPBRN that the jth. cell of super module i is adjacent to

the jth cell of super module k, j ! NFCL. Note that the

adjacency relationship is symmetrical. Two separate entries,

(i,j,k,l) and (k,l,i,j) are not required; only enter one of

the two.

5.14 NON-COMMUNICATION DATA (&NSEE)

This data block defines which fuel cells cannot transmit heat to

certain other fuel cells. It is treated similarly to the preceding data

block, NNCOM entries being required.

Data Set Members

* NV = 4 element array containing non-communication data. If fuel

cell j of super module i cannot transmit heat to fuel cell 1

of super module k, NV would be (i,j,k,l). If all of the fuel

cells in super module i cannot transmit heat to all of the

fuel cells in super module k, NV would be (i,999,k,0). If all

of the fuel cells in super module i cannot transmit heat to

all of the fuel cells in super modules j through j', NV would

be (i,888,j,j'). Note that the non-communication relationship

is asymmetrical.

5.15 ROOM DATA (&ROOM)

This data block should be entered only if IROOM = 1. Default values

are assigned for some of the parameters.

Data Set Members

* DCFIN = Coefficient of inflow air through doorway (dimensionless).

(Default = 1.0)

Suggested values:

1.0 for jet burner.

0.6 for other fire source.

" DCFOUT = Coefficient of discharge for doorway (dimensionless).

(Default = 1.0, Suggested value: 0.7)

* DHGT = Height of doorway (m).

* DWID = Width of doorway (m).

* FC = Fraction of forced ventilation -inflow which enters the gas

layer (dimensionless). (0.0 S FC S 1.0)

- 45 -
" FH = Fraction of forced ventilation outflow which leaves the gas

layer (dimensionless). (0.0 : FH : 1.0)

" GABSRP = Absorption coefficient of hot gas (dimensionless).

(Default = 1.3)

" HCEIL = Heat transfer coefficient for ceiling (W/m2 K). Also used

for heat transfer to objects in the hot gas layer.

" PLCF = Buoyant plume entrainment coefficient, (dimensionless).

(Default = 2.0)

Suggested values:

2.0 for undisturbed room fire.

1.5 for a fire source which is next to a vertical wall.

0.0 for a room fire without any doorway.

" VFV = Forced ventilation volumetric airflow (mW/s).

5.16 INITIALIZATION DATA (&GINIT)

This data block should be entered only if IROOM = 1 and INITG = 1.

Data Set Members

* TG = Initial gas layer temperature (K).

" DG = Initial gas layer thickness (m).

* QEXT = Two dimensional array containing initial external heat fluxes

impinging on each fuel cell, the (i,j) entry corresponding to

fuel cell j of super module i (W/m2 ).

5.17 MODEL VARIATION FACTORS (&MODVAR)

This data block allows the user to multiply the results of various

models by a specified factor. By default, all factors are set to 1.0.

Data Set Members

• FCTR = 15 element array containing the modification factors for 15

models:

1. Modifies room-averaged value for CV (ventilation

controlled burning rate constant).

2. Modifies surface controlled burning rate of fuel.

3. Modifies flame height over horizontal fuel slabs.

4. Modifies flame height over vertical fuel slabs.

5. Modifies radiative heat flux received by target element.

6. Modifies buoyant plume temperature above flame.

- 46 -
7. Modifies heat transfer coefficient for vertical surfaces

in the plume.

8. Modifies heat transfer coefficient for horizontal

surfaces in the plume.

9. Modifies gas layer temperature seen by an object.

10. Modifies heat transfer from flame over vertical fuel bed

back to fuel bed.

11. Modifies conductive heat flux to adjacent fuel cells.

12. Modifies radiative heat flux from the gas layers to

objects below.

13. Modifies heat flux from reflections off of walls and

barriers.

14. Modifies mass burnout fraction. Mass burnout is normally

assumed to occur when 30% of the fuel is remaining. If

100% of fuel is believed to be used up before burnout,

The fraction needs to be changed to 1/0.3.

15. Undefined.

5.18 OUTPUT DEFINITION (&OUTF)

This data block allows the user to specify the printed output desired

(see Section 5.4).

Data Set Members

" INCHCK =

" IOUTPT =

" MOUTPT =

Indicator variable controlling the amount of input data to

be printed.

INCHCK=O => Only heading material and FCTR.

INCHCK=1 => Above, plus fuel parameters

(Section 5.11).

INCHCK=2 => All input data.

Number of output variables to be printed (IOUPT : 17).

Array whose ith element is the identification number of the

output variable desired. IOUTPT elements should be input.

I.D. Number:

1. Total mass burning rate TMDOT (kg/s).

2. Total heat release rate TQDOT (W).

3. Gas layer temperature TG (K).

4. Gas layer thickness DG (m).

- 47 -
S. Fuel cell indicator for damage LDAMGE;

LDAMGE(i,j)=.True. => fuel cell j of super module i is

damaged.

6. Fuel cell indicator variable for burning LBURN;

LBURN(i,j)=.TRUE. => fuel cell j of super module i is

burning. A fuel cell stops burning when 70% or more of

the fuel mass is consumed (see Section 5.17, item 14).

Also note that whether or not a currently nonburning

fuel cell ignites is determined at the end of a time

step.

7. Fuel cell source heat flux QDOT2P (W/m2 ). For

barriers, the source flux is the flux leaving the rear

face of the barrier. For walls and ceilings, it is flux

leaving from the front face. For fuel cells, it

includes both radiative and convective energy from the

flame.

8. Fuel cell radiative external heat flux QEXT (W/M2).

This is the purely radiative heat flux from distant

objects which impinge on the given module (before

reflection). The radiation from the module environment

is not included.

9. Fuel cell total source heat flux QEXTOT (W/m 2 ).

Includes radiative contributions from all sources

(minus reflection), plus convection. Does not include

any losses due to re-radiation or re-convection.

10. Calorimeter heat flux at fuel cell QEXCAL (W/m2 ). Same

as QEXTOT, except that re-radiation and re-convection

losses based on the calorimeter temperature CALTEM are

accounted for. Can be output for any fuel cell,

regardless of that fuel cell's actual fuel type.

11. Fuel cell net heat flux QEXNET (W/M2 ). Same as QEXTOT,

except that re-radiation and re-convection losses based

on the fuel cell surface temperature are accounted for.

12. Fuel cell mass FMASS (kg). This does not include the

pilot mass on top of the fuel cells.

13. Flame height over fuel cell FLHT (m). The flame height

is measured from the base of the fire.

14. Fuel cell flame temperature FLTEMP (K).

15. Fuel cell surface temperature TEMP (K). For barriers,

the front face temperature is printed.

16. Fuel cell heat transfer coefficient HCOEF (W/m2K).

Local convective heat transfer coefficient for fuel

cell.

- 48 -
*NSHIOUT =

*MSMOUT =

17. Fuel cell local environment temperature TSURR (K).

Number of super modules for which variables (I.D. numbers 5

through 17) are to be printed.

Array whose ith element is the identification number of the

super module to be documented.

For example, if the input card is:

&OUTF IOUPT=-3, MOUTPT=1,7,10, NSMOUT-2, MSMOUT=-l,2,

&END

COMPBRN III will print the total mass burning rate for the

compartment, and the source and calorimeter heat fluxes for

each fuel cell in super modules 1 and 2.

Notes: 1. IOUTPTO-0 and NSMOUT=O => Only TMDOT, the total mass

burning rate, is printed.

2. IOUTPT=O and NSMOUT#O => TMDOT and LBURN, an array which

shows which fuel cells are burning, are printed.

4-

- 49 -
Chapter 6

REFERENCES

1. G. Apostolakis, M. Kazarians and D. C. Bley, "Methodology for

Assessing the Risk from Cable Fires," Nuclear Safety, 23(1982),

391.

2. M. Kazarians N. 0. Siu and G. Apostolakis, "Fire Risk Analysis

for Nuclear Power Plants: Methodological Development and

Applications," Risk Analysis, 5(1985), 33.

3. N. 0. Siu, "COMPBRN - A Computer Code for Modeling Compartment

Fires," NUREG/CR-3239, UCLA-ENG-8257, 1983.

4. N. 0. Siu, "Probabilistic Models for the Behavior of Compartment

Fires," NUREG/CR-2269, UCLA-ENG-8090, 1981.

5. N. 0. Siu and G. Apostolakis, "Probabilistic Models for Cable

Tray Fires," Reliability Engineering, 3(1982), 213.

6. N. 0. Siu, "Physical Models for Compartment Fires," Reliability

Engineering, 3(1982), 229.

7. G. Chung, N. 0. Siu and G. Apostolakis, "Improvements in

Compartment Fire Modeling and Simulation of Experiments," Nuclear

Technology, 69(1985), 14.

8. K. Kawagoe, "Fire Behavior in Rooms," Report Number 27, Building

Research Institute, Japan 1958.

9. P. H. Thomas, "Investigation into the Flow of Hot Gases in Roof

Venting," Fire Research Paper Number 7, Department of Scientific

and Industrial Research and Fire Offices' Committee, Joint Fire

Research Organization, Borehamwood, 1963.

10. J. A. Rockett, "Fire Induced Gas Flow in an Enclosure,"

Combustion Science and Technology, 12(1976), 165.

11. J. Quintiere, W. J. Rinkinen, and W. W. Jones, "The Effect of

Room Openings on Fire Plume Entrainment," Combustion Science and

Technology, 26(1981), 187.

12. J. Quintiere and B. J. McCaffrey, "The Burning of Wood and

Plastic Cribs in an Enclosure," 1(1980), NBSIR 80-2054.

- 50 -
13. K. D. Steckler, J. Quintiere and W. J. Rinkinen, "Flow Induced by

Fire in a Compartment," The Nineteenth Symposium on Combustion,

The Combustion Institute, (1982) 913.

14. K. D. Steckler, J. Quintiere and H. R. Baum, "Fire Induced Flows

through Room Openings-Flow Coefficients," NBSIR 83-2801, 1984.

15. D. Cline, W. A. von Riesemann and J. M. Chavez "Investigation of

Twenty Foot Separation Distance as a Fire Protection Method as

Specified in 1OCFRS0, Appendix R," NUREG/CR-3192, SAND83-0306,

1983.

16. J. B. Fang, "Analysis of the Behavior of a Free Burning Fire in a

Quiescent Atmosphere," NBSIR 73-115, 1973.

17. E. E. Zukoski, T. Kubota and M. Cetegen, "Entrainment in Fire

Plumes," NBS-GCR-80-294, 1981.

18. B. J. McCaffrey and J. Quintiere, 'Buoyancy Driven Countercurrent

Flows Generated by a Fire Source', Heat Transfer and Turbulent

Buoyant Convection, Volume II, Hemisphere Pub. Co., (1977) 457.

19. Y. Jaluria, "Buoyancy-Induced Wall Flow Due to Fire in a Room,"

NBSIR 84-2841, 1984.

20. L. Y. Cooper, "On the Significance of a Wall Effect in Enclosures

with Growing Fires," 22nd ASME/AICHE National Heat Transfer

Conference, Seattle, 1983.

21. R. B. Bird, W. E. Stewart and E. N. Lightfoot, Transport

Phenomena, John Wiley & Sons, Inc., N.Y. 1960.

22. E. E. Zukoski, et al., "An Experimental Investigation of the Heat

Trapsfer From a Buoyant Gas Plume to a Horizontal Ceiling,"

Part I, NBS-GCR-77-97, 1975.

23. F. Incropera and D. P. DeWitt, Fundamentals of Heat Transfer,

John Wiley & Sons, Inc., N.Y. 1981.

24. D. K. Edwards, V. E. Denny and A. F. Kills, Transfer Processes,

McGraw-Hill Book Company, N.Y. 1979.

25. H. C. Hottel and A. F. Sarofim, Radiative Transfer, McGraw-Hill

Book Company, N.Y. 1967. Heat Transfer in Flames, Scripta Book

Company, Washington, D.C., 1973.

26. J. Quintiere, "Growth of Fire in Building Compartments," Fire

Standards and Safety, (1977) 131.

27. J. Quintiere, "A Perspective on Compartment Fire Growth,"

Combustion Science and Technolgy, 13(1984), 11.

-51 -
28. P. Chun&, and E. E. Smith, "Emissivity of Smoke," Journal of Fire

and Flammability, 13(1982), 104.

29. D. J. Rasbash, and D. D. Drysdale, "Theory of Fire and Fire

Processes," Fire and Materials, 7(1983), 79.

30. L. Y. Cooper, "The Development of Hazardous Conditions in

Enclosures with Growing Fires," NBSIR 82-2262, 1982.

31. L. Y. Cooper, "Smoke Movement in Rooms of Fire Involvement and

Adjacent Spaces," Fire Safety Journal, 7(1984), 33.

32. B. Hagglund, "A Room Fire Simulation Model," Fire and Materials,

8(1984), 105.

33. H. Takeda, "Small-Scale Experiments of Flame Spread in

Pre-Flashover Compartment Fires," Fire and Materials, 9(1985),

36.

34. R. L. Alpert, "Turbulent Ceiling-Jet Induced by Large-Scale

Fires," Combustion Science and Technolo , 11(1975), 195.

35. J. Quintiere, K. Steckler and D. Corley, "An Assessment of Fire

Induced Flows in Compartments," Fire Science and Technology,

4(1984), 1.

36. L. Y. Cooper, "Convective Heat Transfer to Ceilings Above

Enclosure Fires," The Nineteenth Symposium on Combustion, the

Combustion Institute, (1982) 873.

37. D. Evans, "Calculating Fire Plume Character'stics in a Two Layer

Environment," NBSIR 83-2670, 1983.

38. B. J. McCaffrey, "Purely Buoyant Diffusion Flames: Some

Experimental Results," NBSIR 79-1910, 1979.

39. N. Schultz, Fire and Flammability Handbook, Van Nostrand Reinhold

Company, N.Y., 1985.

40. M. Cetegen, T. Kubota and E. E. Zukoski, "Entrainment and Flame

Geometry of Fire Plumes," NBS-GCR-82-402, 1982.

41. L. Y. Cooper, "A Buoyant Source in the Lower of Two, Homogeneous, Stably-Stratified Layers- A Problem of Fire in an Enclosure,"

ASME Annual Meeting, Boston MA, 1983.

42. T. Z. Harmathy, and J. R. Mehaffey, "Post-Flashover Compartment

Fires," Fire and Materials, 7(1984), 49.

43. W. D. Walton, "ASET-B A Room Fire Program for Personal

Computers," NBSIR 85-3i44, 1985.

- 52 -
44. E. E. Zukoski and T. Kubota, "Experimental Study of Environment

and Heat Transfer in a Room Fire. Mixing in Doorway Flows and

Entrainment in Fire Plumes," NBS-GCR-85-487, 1985.

45. W. W. Jones, "A Review of Compartment Fire Models,"

NBSIR 83-2684, 1983.

46. Y. Jaluria and D. Goldman, "An Experimental Study of Negatively

Buoyant Flows Generated in Enclosure Fires," NBS-GCR-85-487,

1985.

- 53 -
COMPUTE BURNING RATE Act)

COMPUTE HEAT RELEASE RATE 6ct)

CHARACTERIZE GAS

LAYER NEAR CEILING

4= m•4

COMPUTE RATE OF HEAT

TRANSFER TO FUEL

ELEMENTS WITHIN ROOM

~rq i I I I. J I

DETERMINE GAS FLOW

RATE INTO COMPARTMENT

DETERMINE IF NON-BURNING

FUEL ELEMENTS IGNITE

I

INCREMENT TIME

I

Figure 1: Flow Chart of Computation Processes in COMPBRN

- 54 -
FIRE PLUME

CEILING JET

HOT GAS LAYER

0 1

T

z0 LOWER REGION

FIRE SOURCE

MOVEKENT OF

XOVE!X0T OF

COOLER AIR

HOT GASES

Figure 2: Typical Features of Room Fire in a Two Zone Model

- 55 -
MASS FLOW PATH

HEAT FLOW PATH - - - -.

Figure 3: Features of Room Fire in COMPBRN III HGLM

- 56 -
3

~0

0 I 4B I ENT

HD

Zo,ri

Figure 4: Room Geometry of Rockett's Air Flow Model [10]

- 57 -
FIRE SCENARIO BLOCKAGE FACTOR TOP VIEW

NO BLOCKAGE

CORNER FLOW

THREE SIDES BLOCKED

H - 1.10

H = 1.49

X - 1.28

DOOR FLOOR N - 1 .28

Figure 5: Effect of Blockage on Mass Flux Ratio [17]

- 58 -
TOP VIEW

S

SIDE WALL

FIRE SOURCE

SIDE VIEW

WPT 0.97 WPT 0.57 WPT

Figure 6: Effect of Vertical Wall on Plume Mass Flux [17]

- 59 -
CEILING

HOT GAS LAYER

TG

LOW1ER REGION TO0

DG

QCEILING kaG

4CEIL

FLOOR

Figure 7: Radiative Heat Flux Emitted by Hot Gas Layer and Ceiling

- 60 -
Figure 8: Flow Chart of the CGAS Subroutine

- 61 -
ELEVATIOH

Figure 9: Enclosure Details of SNL/UL Experiment 1 (151

- 62 -
to a S" PAX

10 GALLONS IKEPTAKE

tiP e2-4

S GALLONS HIPAKC

UIST 1-9

2 VECRTICAL LYAS

12.S% FILL 43 CA€SLES)

TZITS #1-9 ONLY

NOTE: DOOR WIDTH

to" EXPER.IMENT #t2

U" £1PEpRIUCHT #$

AND ALL TESTS

0" NOP PEftSMEPIS.4

CANOPY

PLAN

1 2.5 /

100 RMMIND AUT

ELEVATION

Figure 10: Enclosure Details of SNL/UL Experiments 2-4 1151

- 63 -
9,14 m (EXPERIMENT 1).

1.22 x 2.44 m2

(Experiments 2-4)

EXPERIMENT 2-4

Figure 11: Enclosure Details of SNL/UL Experiments 1-4
TEST CASES

1.

2.

3,

4.

5,

SHLIUL DATA

COMPBRN III

COMPBRN III

COMPBRN II

COMPBRN II

C

(

C

(

in , 1.0)

n = 0,7)

n = 1.0)

n = 0.7)

LUJ i,--

LL)

.--

Lii

4-

700

600

500

400'

2

° 5 - . -- - -,-i-i- - - -,-

I I I 1 I I I I I I I I r I I

I F I U

300 600 900

TIME (S)

Figure 12: Simulation of SNL/UL Experiment 1: Hot Gas Layer Temperature

- 65 -
MLQSZ

1. SNI/UL DATA

2. COMPBRN III C r = 1.0)

3. COMIPBR1I III (,n = 0.7)

4. COPBRON I I ( n = 1.0)

5. COMPBRN II ( n , 0.7)

I.--"Lu

U-

=60,

,-.

L!1:

2

300 600 9o00

TIME (s)

Figure 13: Simulation of SNL/UL Experiment 1: Coble Jacket Temperature

- 66 -
TEUuST CsE

1i

2.

3.

4,

5.

SNI/UL DATA

COMPBRN III (

COMPBRN III (

COMPBRN II (

COMPBRN II I

I = 1.0)

11= 0.7)

= 1.0)

I = 0.7)

I25

ULUJ

2

• • ,bq•t •o"dV Bg'•. #M,,2

- -

- ,

300 600 900

TIME (S)

Figure 14: Simulation of SNL/UL Experiment 1: Heat Flux

- 67 -
TEST CASES

1. SNL/UL DATA

2. COMPBRN III ( n = 1,0)

3, COMPBRN III n = 0 0.7)

4. COMPBRN I I ( n = 1.0)

5, COMPBRN II n = 0.7)

ILhU

LJJ

- - - - - - - - - -4

I.

I

I- - 5

300 600 900

TIME (S)

Figure 15: Simulation of SNL/UL Experiment 2: Hot Gas Layer Temperature

- 68 -
IES'T AýSES

1. SNI/UL DATA

2. COMPBRN III 1 (1 1.0)

3. COMPBRN III ( n = 0,7)

5. COMPBRN II (, 1, 0)

LU 5s COMPBRI 11 = 0.7)

u 70 1--

LU

,- 600-

Lad Q500 0

LU 0

300 600 900

TIME (S)

Figure 16: Simulation of SNL/UL Experiment 2: Cable Jacket Temperature

- 69 -
TEST CASES

1. SNL/UL DATA

2. COMPBRN III

3. CONPBRN I II

4. COMPBRN 1I

5s COh4PBR I II

( T = 1.0)

C n = 0.7)

( T = t10)

( T =0.7)

12

=LzJ

LLI--

-LJ

u_

8

4

* I ,P% 2 I ~ I g~~I ,

1~~~*~ is - -r' ~i-~I - _______ 5

n a - a -

/ - /

/

1 I I I I .

A 3 S 3 AI I I I I I II

300 600 900

TIME (S)

Figure 17: Simulation of SNL/UL Experiment 2: Heat Flux

- 70 -
MIELOAE

11

2,

3,

4i.

5.

SNUUL DATA

COMPBRN III

COIPBRN III

COMPBRN II

CONPBRN 11

( n =1,.0)

Sn =0,7)

= 1,0)

( Ti = 0.7)

700

Lii

Lii

I--

Act

C.D

600

500

L4O0

2

f -

-

" I

" I

UB

- I

U

-I I

I I I I I I I I I I I I I I I

300 600 900

TIME (S)

Figure 18: Simulation of SNL/UL Experiment 3: Hot Gas Layer Temperature

- 71 -
IEULCA-SES

1, SNWIUL DATA

2. COMPBRN III

3. COMPBRN I II

4. COMPBRN II

5. COMPBRi II

( , = 1.0)

( n = 0.7)

( =1.0)

( I =0.7)

Uii

ULii

=q

C-

- -~ -

- - - - ----- 1

.. ..

300 600 900

TIME (S)

Figure 19: Simulation of SNL/UL Experiment 3: Cable Jacket Temperature

- 72 -
TEST CMSE

:1

2.

3,

LI.

5.

SNL/UL DATA

COGPBRN III

COMPBRN III

COIIPBRN II

COMPBRN I I

(TI=1.0)

( n=0.7)

( n =1.0)

( I =0.7)

16

12

S

U- U..=

Lii

=,[

8

300 600 900

TIME (S)

Figure 20: Simulation of SNL/UL Experiment 3: Heat Flux

- 73 -
1. SNL/UL DATA

* 700 2, COMPBRN III

(see Table 3)

, 600

U "

uj400'/-

300 600 900

TIME (S)

Figure 21- Simulatioal of SNL/UL Experiment 1: Hot Gas Layer Temperature

- 74 -
IESUAIM

1. SNL/UL DATA

2, CONPBRN I I I

(see Table 3) 1±_ 70C

ILU 60C

-500

40O CF " W-•1

a

0

S ... I 0 I 9 I 0 I I I f . ! 300 600 go

TIME (S)

Figure 22: Simulation of SNL/UL Experiment 1: Cable Jacket Temperature

- 75 -
C%4

I16F

121

8

4

1. SNL.•L DATA

2, COMPBRN I I I

(see Table 3)

2

(74.

,,,1

~ ~ - A I'

I

V

,,bj v

I I i i I I i S I I I I I I

I I 3 1 3 3 3 3 3 3 3 * I I

300 600 900

TIME (S)

Figure 23: Simulation of SNL/UL Experiment 1: Heat Flux

- 76 -
TEST-CASES

11

2,

SNI/UL DATA

COMPBRN III

52%7 00

'600

~500

LU

U400

f5 LO

c,,

(see Table 3)

1 - p q.- 0 V - _ .0

2

1 - ,N

/

0

I

I

f

300 600 900

TIME (S)

Figure 24: Simulation of SNL/UL Experiment 2: Hot Gas Layer Temperature

- 7.7 -
LLi

ULLii

Lii

C-j

1, SNUIJL DATA

2a COMPBRN III

700- (see Table 3)

600

50d

I

aft

400%-

I i I I I I I I I I I I I I

300 600 900

TIME (S)

Figure 25: Simulation of SNL/UL Experiment 2: Cable Jacket Temperature

- 78 -
16

1. SNUUL DATA

2s COMPBRN III

(see Table 3)

1

I ,,, 'S *•,% •

I

12

t=

%-j

_C21

U_

8

4

,,, a

I I I I I tI 1 I I I I I I I I

300 600

TIME (S)

Figure 26: Simulation of SNL/UL Experiment 2: Heat Flux

- 79 -
700F 1. SNLIUL DATA

2, COMPBRN I I I

(see Table 3)

CILaj

415

C/3

2 •IP L

600

500

.0

,.0I

- .010.

-

400

300 600 9

T II'E (S)

)0

Figure 27: Simulation of SNL/UL Experiment 3: Not Gas Layer Temperature

- 80 -
MIM~AE

1. SNUUL DATA

2s COMPBRN III

(see Table 3)

Lj

ILU

0LJ

700

600

500

I

ram, 2

1. 1 pI VW

400 - *0

I

I I t I t I I I I I I I I. I

300 - 600 900

TIME (S)

Figure 28: Simulation of SNL/UL Experiment 3: Cable Jacket Temperature

- 81 -
CSJ

16

12

1. SNI/UL DATA

2. COMPBRN III

(see Table 3)

mOP

S2 4%. . p ---

I.,

:8 8

4

S 0 S ~ 3 I I I I I I - I I I I A I- a U300 600 900

TIME (S)

Figure 29: Simulation of SNL/UL Experiment 3: Heat Flux

- 82 -
IEST CASES

1, SNL/UL DATA

2. COMPBRN III (nr= 1.0)

3. COMPBRN III ( T = 0. 65)

(see Table 3)

:-=-i0. ý1 J#% -P"-

2

I--

L,.

I.--

CL

IIC.J

I

I

400 1

300 600 900

TIME (S)

Figure 30: Simulation of SNL/UL Exper-iment 4: Hot Gas Layer Temperature

- 83 -
IESLCAME

1.

2.

3.

SNI/UL DATA

COMPBRN III (n= 1.0)

COMPBRN I I (= 0. 65)

(see Table 3) Lii

UClLii

03

700

600

500

400

2

3.,

300 600 " 900

TIME (S)

Figure 31: Simulation of SNL/UL Experiment 4: Cable Jacket Temperature

- 84 -
TEST CASES

1. SNL'

2. COMP

3. COMP

(see

lUL DATA

12

'BRN III (T= 1.0)

BRN III (n= 0.65)

Table 3)

1LLii

2

8

4

300 600 900

TIME (S)

Figure 32: Simulation of SNL/UL Experiment 4: Heat Flux

- 85 -
MOVABLE BIDIRECTIONAL

VELOCITY PROBES AND

THERM~OCOUPLES

2.8m

Figure 33: Experimental Arrangement of the Steady-State Flow Experiments

1111

- 86 -
LIv

3500

t0i

450~

co

cLU 4500

350

300

450

4--

-I

300 350 400 450 500 550

MEASURED HOT GAS LAYER TEfIPERATUJRE: TG (K)

Figure 34: Simulation of the Steady-State Experiments: TG

- 87 -
450

L&J

LU

L)

LLJ

1.

0.

0.

0.

0.5 0.6

MEASURED

0.7

THERMAL

0.8

HEIGHT:

0.9

ZD

1.0

(M)

Figure 35: Simulation of the Steady-State Experiments: ZD

- 88 -
LLJ

LL)

LU.

LU.

C3-

1- 10.0

9.75

9650

9.25

9.0

9.25 9.50 9.75 10.0

HEASURED THERMAL INTERFACE HEIGHT: ZN (,4)

Figure 36: Simulation of the Steady-State Experiments: ZN

- 89 -
Figure 37: Programming Flow Chart of COMPBRN III

- 90 -
Appendix A

A SAMPLE PROBLEM

In this Appendix, we use a sample problem to demonstrate the usage of

COMPBRN III. The user can utilize the sample input as a guideline for

developing input files for CO0PBRN.

The. sample problem used here is the simulation of SNL(UL

Experiment 1. The enclosure details of the experiment haves been given

in Chapter 4 (see Figure 9, 10 and 11). The other details of the

materials used in the experiment and the locations of the probes can be

found in [15]. There is no forced ventilation in the room and the fire

source is a heptane tank 9.14 m away from the wall (facing the doorway).

The sample input file is shown in Table 6 and portions of the sample

output can be found in Table 7. The results of the simulation are shown

in Figure 21, 22 and 23.

- 91 -
TABLE 6

COMPBRN III Sample Problem Input

&STRT NJOB=l, NTIME=15, NREAD=5, NWRITE=6, DELT=60., &END

&SIZE NSM=10, NFUEL=5, NPILOT=1, NCOM=O, NNCOM=O, IROOM=1,

INITG=O, &END

****TEST CASE: SAMPLE PROBLEM FOR COMPBRN III (SNL/UL EXPT 1) **

&FUELB SMX=2.14, SMY-4.57, SMZ=3.05,

SLNG=9.14, SWID=4.27, SDEP=1.00,

SMASS=1500., SPOR=1.0, SLOSS=1.0,

NFIL=I, IORNT=3, IDIREC=2,

IFTYP=I, &END (CEILING)

&FUELB SMX=2.14, SMY=9.14, SMZ=1.52,

SLNG=4.27, SWID=3.10, SDEP=1.00,

SMASS=610.0, SPOR=1.0, SLOSS=1.0,

NFIL=1, IORNT=2, IDIREC=1,

IFTYP=2, &END (WALL)

&FUELB SMX=3.21, SMY=8.61, SHZ=2.64,

SLNG=.323, SWID=0.46, SDEP=0.11,

SMASS=2.25, SPOR=3.11, SLOSS=I.0,

NFIL=1, IORNT=3, IDIREC=1,

IFTYP=3, &END (CABLE)

&FUELB SMX=2.14, &END

&FUELB SMX=1.07, &END

&FUELB SMX=3.21, SMZ=2.44, &END

&FUELB SMX=2.14, &END

&FUELB SMX=1.07, &END

&FUELB SMX=2.14, SMZ=0.914, &END

&FUELB SMX=2.14, SMY=2.13, SMZ=.152,

SLNG=1.53, SWID=0.31, SDEP=0.31,

SMASS=12.87, SPOR=1.0, SLOSS=1.0,

NFCL=1, IORNT=3, IDIREC=1,

IFTYP=4, &END (HEPTANE FUEL)

&PILOT IPIL=10, JPIL=I, IPFUEL=4,

PMASS=21.88, &END

&FUELT IFUEL=40, 20, 1, 2, 10,

DENS=2*2243.1, 1715., 679., 1.0,

SPHT=2*751.7, 1045., 2192.4, 2.0,

THX=2*1.72, .092, .128, 1.0,

BRATV=2*0.0, 2*0.110, 0.0,

FABSRP=0.0, 0.0, 2*1.4, 0.0,

REFL=4*0.35, 0.1,

BRATS1=0.0, 0.0, 1.8E-7, 0.0, 0.0,

GAMMA=4*.0.45, 0.0,

BRATSO=2*0.0, 0.001, 0.061, 0.0,

HEAT=2*0.0, 2.4E+7, 4.84E+7, 0.0,

EFF=5*0.85,

FIGTP=2*0.0, 789.0; 2*0.0,

FIGTS=2*0,0, 839.0, 2*0.0,

FTDAM=2*0., 543.0, 2*0.0, &END

&MISC RTEMP=298.0, FLCF=22.0, HROOM=10;0, CALTEM=298.0, &END

&ROOM DCFIN=0.6, DCFOUT=0.7, DHGT=2.44, DWID=2.44, FC=0.0, FH=0.0,

- 92 -
GABSRP=1.3, HCEIL=1O.O, PLCF=2.O, VFVO0.O, &END

&MODVAR FCTR=15*1.O, &END

&OUTF INCHCK=2, IOUTPT=17,

MQUTPT=1,2,3,4,5,6,7,8,9,1O,11,12,13,14,15,16,17,

NSMOUT=1O, MSNOUT=1,2,34,5,6,7,8,9,1O, &END

- 93 -
TABLE 7

COHPBRN III SAMPLE PROBLEM OUTPUT

to

w co

- W:i

to u..

La, -

•u.<

(60 *1.

*

0 0

too

QW-I 10 -1

*-ZW 0

a-I.- 6

0~U) cc

- 94 -
VARIABILITY FACTORS FOR FIRE MODELS:

VENTILATION CONTROLLED BURNING RATE

FUEL-SURFACE CONTROLLED BURNING RATE

FLAME HEIGHT FOR HORIZONTAL FUEL

FLAME HEIGHT FOR VERTICAL FUEL

RADIATIVE HEAT FLUX INTERCHANGE

BUOYANT PLUME TEMPERATURE

CONVECTIVE HEAT TRANSFER COEFFICIENT FOR VERTICAL OBJECTS IN PLUME

CONVECTIVE HEAT TRANSFER COEFFICIENT FOR HORIZONTAL OBJECTS IN PLUME

GAS.LAYER LOCAL TEMPERATURE

HEAT TRANSFER TO SELF FOR VERTICAL FUEL

a HEAT TRANSFER TO ADJACENT FUEL

HEAT FLUX FROM CEILING HOT GAS LAYER

HEAT FLUX FROM REFLECTIONS OFF WALLS AND BARRIERS

MASS BURNOUT FRACTION

CURRENTLY UNDEFINED

0.100000E÷01

0. 100000E+01

0.IOOOOOE+O1

O.100000E+O1

O.1OOOOOE÷01

0.100000E+O1

0.IOOOOOE+O1 0.,100000E4O1

0.100000E÷01

0.100000E+01

O.100000E÷01

O.IOOOOOE÷01

0.1OOO00E+O1

0.1OO00OE÷O1

0.100000E+01

0.1000OOE+01
NUMBER OF FUEL TYPES: 

5

DATA FOR FUEL TYPE 1:

FUEL TYPE: (CEILING)

THERMAL CONDUCTIVITY (W/N-K): THERMAL DIFFUSIVITY (M**2/S): REFLECTIVITY:

DATA FOR FUEL TYPE 2:

FUEL TYPE: (WALL)

THERMAL CONDUCTIVITY (WIN-K): THERM4AL DIFFUSIVITY (M**2/S):

REFLECTIVITY:

DATA FOR FUEL TYPE 3:

FUEL TYPE:

OENSITY (KG/M**3): SPECIFIC HEAT (J/KG-K):

THERMAL CONDUCTIVITY (WIN-K):

HEAT OF COMBUSTION (J/KG): COMBUSTION EFFICIENCY:

PILOTED IGNITION TEMPERATURE (DEG. K): 0' SPONTANEOUS IGNITION TEMPERATURE (DEC. K): DAMAGE TEMPERATURE (DEG. K).,

VENTILATION CONTROLLED BURNING RATE FACTOR (KG/M**2.5-S): SURFACE CONTROLLED SPEIFIC BURNING RATý (KG/M0 02-S):

SPECIFIC BURNING RATE RADIATION AUG14ENTATION (KG/J-M**2): FRACTION OF HEAT RELEASED AS RADIATION: SMOKE ATTENUATION FACTOR (1**-1):

REFLECTIVITY:

40

0.172000E+01

0.102006E-05

0.350000E+O0

20

0.172000E+01

0.102008E-05

0.350000E+001

0.171500E+04

0.104500E+04

0.920000E-01

0.240000E+08

0.850000E+O0

0.789000E÷03

0.839000E+03

0.543000E+03

O.110000E+0O

O. lO0000E-02

0.180000E-06

0.450000E+O0

0.140000E+O1

0.350000E+OO
DATA FOR FUEL TYPE 4:

FUEL TYPE:

DENSITY (KG/M**3):

SPECIFIC HEAT (J/KG-K):

THERMAL CONDUCTIVITY (W/M-K):

HEAT OF COMBUSTION (J/KG):

COMBUSTION EFFICIENCY:

PILOTED IGNITION TEMPERATURE (DEG. K):

SPONTANEOUS IGNITION TEMPERATURE (DEC. K):

DAMAGE TEMPERATURE (DEG. K):

VENTILATION CONTROLLED BURNING RATE FACTOR (KG/M**2.5-S):

SURFACE CONTROLLED SPECIFIC BURNING RATE (KG/M**2-S):

SPECIFIC BURNING RATE RADIATION AUGMENTATION (KG/J-M-*2):

FRACTION OF HEAT RELEASED AS RADIATION:

SMOKE ATTENUATION FACTOR (M**•-):

REFLECTIVITY:

DATA FOR FUEL TYPE 5:

FUEL TYPE: (DETECTOR)

2

0.679000E+03

O.219240E+04

0. 128000E+00

0.484000OOOE+

O 850000E+00

0.0

0.0

0.0

O. IIOOOOE+00

0. 610000E-01

0.0

0. 450000E+O0

0. 140000E+01

0. 350000E+00

10

I

%0
ROOM PARAMETERS:

CEILING LENGTH, WIDTH, HEIGHT (M): DOOR HEIGHT (H): DOOR WIDTH (3):

DOORWAY INFLOW COEFFICIENT:

DOORWAY OUTFLOW'COEFFICIENT:

FORCED VENTILATION (H**3/S): FORCED VENTILATION CONSTANTS (FH AND FC): PLUME ENTRAINMENT CONSTANTS (PLCF) GAS ABSORPTION COEFFICIENT (GABSRP):. CEILING HEAT TRANSFER COEFFICIENT (W/M**2 DEG,

0.914000E+O1 0.427000E+O1 0. 305000E+01

0. 244000E+01

0. 244OOOE+O1

0. 600000E00

0. 700000E+O0

0.0

0.0 0.0

0. 200000E+O1

0. 130000E+O1

K ): O.100000E+02

co

I
PILOT FIRE DATA:

NUMBER OF PILOT FIRES: I

DATA FOR PILOT FIRE 1:

LOCATION OF PILOT FIRE (FUEL ARRAYFUEL CELL):

FUEL TYPE:

MASS (KG):

10, 1

. 0.218800E+02

!a

'a
NUMBER OF FUEL ARRAYS: 10

DATA FOR FUEL ARRAY 1:

INITIAL FUEL CELL X-Y-Z COORDINATES (M):

DIMENSIONS (LENGTH,WIDTH,DEPTH) (M):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS): HEAT LOSS FACTOR (UNDEFINED): FUEL TYPE:

DATA FOR FUEL ARRAY 2:

INITIAL FUEL CELL X-Y-Z COORDINATES (M):

DIMENSIONS (LENGTH,WIDTH,DEPTH) (M):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED):

FUEL TYPE:

DATA FOR FUEL ARRAY 3: '--,

o INITIAL FUEL CELL X-Y-Z COORDINATES (M):

DIMENSIONS (LENGTHWIDTHDEPTH) (M):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED):

FUEL TYPE:

DATA FOR FUEL ARRAY 4:

INITIAL FUEL CELL X-Y-Z COORDINATES (M):

DIMENSIONS (LENGTH,WIDTH,DEPTH) (M):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED):

FUEL TYPE:

0.214000E+01 0.457000E+01 0. 305000E+01

0.914000E+01 0.427000E+01 0. 100000E+01

0.214000E+01 0.91'4000E+01

0.427000E+01 0. 310000E+01

1

Y 

Z

0.150000E+04

0.10000OE÷01 0.100000E+011

0.152000E+01

0.100000E+011

X 

Y

0.610000E+03

0.100000E+O1

O.100000E+012

0.264000E+01

0.110000E-O1

1

X 

Z

0.225000E+01

0.311000E+01

0. 100000E+013

0.264000E+01

0.110000E-01

1

X 

Z

0.225000E+01

0.311000E+01

0.100000E÷013

O.321000E+01 0.861000E+01

0.323000E+00 0.460000E+00

0.214000E+01 O.861000E+01

0.323000E+00 0.460000E+O0
DATA FOR FUEL ARRAY 5:

INITIAL FUEL CELL X-Y-Z COORDINATES (N):

DIMENSIONS (LENGTH,WIOTH,DEPTH) (M):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED):

FUEL TYPE:

0.107000E+01 0.861000E+01 0.264000E+01

0.323000E+00 O.460000E+O0 0.1100OOE-O11

X Z

0.225000E+01

0.311000E+O1

O. IOOOOOE+01

3

I
DATA FOR FUEL ARRAY 6:

INITIAL FUEL CELL X-Y-Z COORDINATES (NW: DIMENSIONS (LENGTH,WIDTH,DEPTH) (M): NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS): HEAT LOSS FACTOR (UNDEFINED): FUEL TYPE:

DATA FOR FUEL ARRAY 7:

INITIAL FUEL CELL X-Y-Z COORDINATES (N): DIMENSIONS (LENGTHWIDTHDEPTH) (N): NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

4ASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED): FUEL TYPE:

DATA FOR FUEL ARRAY 8:

INITIAL FUEL CELL X-Y-Z COORDINATES (M): I-- DIMENSIONS (LENGTHWIDTH,DEPTH) (H): 0 NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS): HEAT LOSS FACTOR (UNDEFINED): FUEL TYPE:

0.321000E+01 0.861000E+01

0.323000E+00 0.460000E+00

0.214000E+01 0.861000E+01

0.323000E+00 0.460000E+00

0.107000E+01 0.861000E+01

0.323000E+00 O.460000E+O0

0.244000E+01

0.11OOOOE-O1

1

X 

z 0.225000E+01

0.311000E+01

O.1000OOE+O1

3

0.244000E+01

0.110000E-O1

1

X 

Z

0.225000E+01

0.311000Ee01

0.100000E+013

0.244000E+01

0.110000E-011

X 

Z

0.225000E+01

0.311000E+01

0. 100000E013
DATA FOR FUEL ARRAY 9:

INITIAL FUEL CELL X-Y-Z COORDINATES (M):

DIMENSIONS (LENGTH,WIDTH,DEPTH) (M):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED):

FUEL TYPE:

DATA FOR FUEL ARRAY 10:

INITIAL FUEL CELL X-Y-Z COORDINATES (M):

DIMENSIONS (LENGTH,WIDTH,DEPTH) (N):

NUMBER OF FUEL CELLS:

DIRECTION OF AXIS, ORIENTATION:

MASS (KG):

POROSITY FACTOR (DIMENSIONLESS):

HEAT LOSS FACTOR (UNDEFINED):

FUEL TYPE:

0.214000OE+01 0.861000E+01

0. 323O00E+OO 0. 46OOO0E+O0

0.21U4000E+01 0.213000E+01

0. 153000E+01 0. 310000E+00

O.914OOOE+OO

0.1100OOE-011 x z

0.225000E+01

0.311000E+01

0.100000E+013

0.152000E+00

0.310000E+OO1 x z 0.128700E+02

O lOOOOOE+01

O.lOOOOOE+O14

I-, 0

L.)
MISCELLANEOUS:

ROOM TEMPERATURE (DEG. K); CALORIMETER TEMPERATURE (DEG. K): CONVECTIVE HEAT TRANSFER COEFFICIENT FOR FLAME (W/MO2-K): CONVECTIVE HEAT TRANSFER COEFFICIENT FOR ROOM (W/1M42-K): (FOR OBJECTS OUTSIDE OF HOT GAS LAYER) TIME INCREMENT (S):

NUMBER OF TIME STEPS FOR JOB:

0.298000E+03

0.298000E+03

0.220000E÷02

0.100000E+02

0.600000E+02

5

I
***** TEST CASE: SNL CABLE TRAY

TIME (SEC): 0.

TOTAL MASS BURNING RATE (KG/S):

TOTAL HEAT RELEASE RATE (W)

HOT GAS LAYER TEMPERATURE (K)

HOT GAS LAYER THICKNESS (M)

EXPERIMENT #1 (EFF=O.8) COMP3 •

.0

.0

298.0

.0

I

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

123456789

10123456789

10123456789

10

DAMAGE

DAMAGE

DAMAGE

DAMAGE

DAMAGE

DAMAGE

DAMAGE

DAMAGE

DAMAGE

DAMAGE

7????7

BURNING?

BURNING?

BURNING?

BURNING?

BURNING?

BURNING?

BURNING?

BURNING?

BURNING?

BURNING?

FFFFFFFFFFFFFFFFFFFT

SOURCE

SOURCE

SOURCE

SOURCE

SOURCE

SOURCE

SOURCE

SOURCE

SOURCE

SOURCE

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0
MODULE: 1 EXTERNAL FLUX .0

MODULE: 2 EXTERNAL FLUX .0

MODULE: 3 EXTERNAL FLUX .0

MODULE: 4 EXTERNAL FLUX .0

MODULE: 5 EXTERNAL FLUX .0

MODULE: 6 EXTERNAL FLUX .0

MODULE: 7 EXTERNAL FLUX .0

MODULE: 8 EXTERNAL FLUX .0

MODULE: 9 EXTERNAL FLUX .0

MODULE: 10 EXTERNAL FLUX .0

MODULE: 1 TOTAL FLUX .0

MODULE: 2 TOTAL FLUX .0

MODULE: 3 TOTAL FLUX .0

MODULE: 4 TOTAL FLUX .0

MODULE: 5 TOTAL FLUX .0

MODULE: 6 TOTAL FLUX .0

MODULE: 7 TOTAL FLUX .0

MODULE: 8 TOTAL FLUX .0

MODULE: 9 TOTAL FLUX .0

MODULE: 10 TOTAL FLUX .0

MODULE: 1 MEAS'D FLUX .0

0 MODULE: 2 MEAS'D FLUX .0

MODULE: 3 MEAS'D FLUX .0

MODULE: 4 MEAS'D FLUX .0

MODULE: 5 MEAS'D FLUX .0

MODULE: 6 MEAS'D FLUX .0

MODULE: 7 MEAS'D FLUX .0

MODULE: 8 MEAS'D FLUX .0

MODULE: 9 MEAS'D FLUX .0

MODULE: 10 MEAS'D FLUX .0

MODULE: 1 NET FLUX .0

MODULE: 2 NET FLUX .0

MODULE: 3 NET FLUX .0

MODULE: 4 NET FLUX .0

MODULE: 5 NET FLUX .0

MODULE: 6 NET FLUX .0

MODULE: 7 NET FLUX .0

MODULE: 8 NET FLUX .0

MODULE: 9 NET FLUX .0

MODULE: 10 NET FLUX .0
,.,4

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

123456789

10123456789

10123456789

10123456789

10

FUEL M

FUEL !

FUEL H

FUEL H

FUEL M

FUEL 

M

FUEL M

FUEL M

FUEL M

FUEL M

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FUEL 1

FUEL 1

FUEL 1

FUEL 1

FUEL 1

FUEL 1

FUEL

FUEL 1

FUEL 1

FUEL 1

ASS

ASS

[ASS

ASS

lASS

ASS

ASS

ASS

ASS

ASS

HOT

HGT

HGT

HOT

HGT

HGT

HGT

HGT

HOT

HGT

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.0

.1 50E+04

610.

2.25

2.25

2.25

2.25

2.25

2.25

2.25

12.9

298.

298.

298.

298.

298.

298.

298.

298.

298.

298.
MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

123456789

10

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

HEAT TRANS COEF

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

ENVIRONMENT TEMP

10.0

10.0

10.0

10.0

10.0

10.0

10.0

10.0

10.0

10.0

298.

298.

298.

298.

298.

298.

298.

298.

298.

298.

MODULE: 

1

MODULE: 

2

MODULE: 

3

MODULE: 

4

MODULE: 

5

MODULE: 

6

MODULE: 

7

MODULE: 8

MODULE: 

9

MODULE: 10

0

I0
**** TEST CASE: SNL CABLE TRAY EXPERIMENT #1 (EFF=O.8) COMP3 *•**

TIME (SEC): 60.

TOTAL MASS BURNING RATE (KG/S): .2893E-01

TOTAL HEAT RELEASE RATE (W) : .1190E+07

HOT GAS LAYER TEMPERATURE (K) : 504.2

HOT GAS LAYER THICKNESS (M) 1.446

MODULE: 1 DAMAGE ? 

F

MODULE: 2 DAMAGE ? 

F

MODULE: 3 DAMAGE ? 

F

MODULE: 4 DAMAGE ? 

F

MODULE: 5 DAMAGE ? 

F

MODULE: 6 DAMAGE ? 

F

MODULE: 7 DAMAGE ? 

F

MODULE: 8 DAMAGE ? 

F

MODULE: 9 DAMAGE ? 

F

MODULE: 10 DAMAGE ? 

F

MODULE: 1 BURNING? 

F

MODULE: 2 BURNING? 

F

MODULE: 3 BURNING? 

F

0 MODULE: 4 BURNING? 

F

MODULE: 5 BURNING? 

F

MODULE: 6 BURNING? 

F

MODULE: 7 BURNING? 

F

MODULE: 8 BURNING? 

F

MODULE: 9 BURNING? 

F

MODULE: 10 BURNING? 

T

MODULE: 1 SOURCE FLUX .329E+04I

MODULE: 2 SOURCE FLUX 291.

MODULE: 3 SOURCE FLUX .0

MODULE: 4 SOURCE FLUX .0

MODULE: 5 SOURCE FLUX .0

MODULE: 6 SOURCE FLUX .0

MODULE: 7 SOURCE FLUX .0

MODULE: 8 SOURCE FLUX .0

MODULE: 9 SOURCE FLUX .0

MODULE: 10 SOURCE FLUX .158E+06
IMODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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MODULE:

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MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

123456789

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10123

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EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

EXTERNAL

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

TOTAL FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

MEAS'D FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

FLUX

.238E+04

526.

295.

308.

295.

282.

293.

282. . 177E+054 . 161E+04 . 897E+04

.1777E+04

.762E+04 . 762 E+04 . 762E+014

.761 E+04 . 762E+04

.761 E+04

.442E+04

. 432E+04

.570E+04

.450E+04

.435E+04

.435E+04 .435E+04

. 434E+04 . 434 E+04 . 434 E+04

.1 15E+04

. 105E+04 . 570E+04 . 450E+04

.435E+04

. 435E+04

.435E+04

.434E+04

.434E+04

.434E+04

.115E+04

.105E+04

NET

NET

NET

NET

NET

NET

NET

NET

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NET

FLUX

FLUX

FLUX

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FLUX

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MODULE:

MODULE:

MODULE:

MODULE:

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MODULE:

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MODULE:

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MODqLE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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10123456789

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FUEL t

FUEL F

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FUEL I

FUEL F

FUEL I

FUEL F

FUEL I

FUEL 

P

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

lASS

lASS

lASS

lASS

lASS

lASS

IASS

•ASS

lASS

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HOT

HOT

HOT

HOT

HOT

HGT

HOT

HOT

HGO

HOT

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

.0

.0

.0

.0

.0

.0

.0

.0

.0

2.88

.150E+04

610.

2.25

2.25

2.25

2.25

2.25

2.25

2.25

12.9

.0

.0

.0

.0

.0

.0

.0

.0

.0

.129E+0I4

301.

300.

346.

346.

346.

346.

346.

346.

311.

298.
MODULE: 1 "EAT TRANS COEF 10.0

MODULE: 2 HEAT TRANS COEF 10.0

MODULE: 3 HEAT TRANS COEF 10.0

MODULE: 4 HEAT TRANS COEF 10.0

MODULE: 5 HEAT TRANS COEF 10.0

MODULE: 6 HEAT TRANS COEF 10.0

MODULE: 7 HEAT TRANS COEF 10.0

NODULE: 8 HEAT TRANS COEF 10.0

MODULE: 9 HEAT TRANS COEF 10.0

MODULE: 10 HEAT TRANS COEF 10.0

MODULE: 1 ENVIRONMENT TEMP 504.

MODULE: 2 ENVIRONMENT TEMP 504.

NODULE: 3 ENVIRONMENT TEMP 504.

MODULE: 4 ENVIRONMENT TEMP 504.

MODULE: 5 ENVIRONMENT TEMP 504.

MODULE: 6 ENVIRONMENT TEMP 504.

MODULE: 7 ENVIRONMENT TEMP 504.

MODULE: 8 ENVIRONMENT TEMP 504.

MODULE: 9 ENVIRONMENT TEMP 298.

MODULE: 10 ENVIRONMENT TEMP 298.

t-A
**** TEST CASE: SNL CABLE TRAY EXPERIMENT #1 (EFF=O.8) COMP3 

•

TIME (SEC): 120.

TOTAL MASS BURNING RATE (KG/S): .2893E-01

TOTAL HEAT RELEASE RATE (W) : .1190E+07

HOT GAS LAYER TEMPERATURE (K) : 504.6

HOT GAS LAYER THICKNESS (M) 1.446

MODULE: 1 DAMAGE ? 

F

MODULE: 2 DAMAGE ? 

F

MODULE: 3 DAMAGE ? 

F

MODULE: 4 DAMAGE ? 

F

MODULE: 5 DAMAGE ? 

F

MODULE: 6 DAMAGE ? 

F

MODULE: 7 DAMAGE ? 

F

MODULE: 8 DAMAGE ?. 

F

MODULE: 9 DAMAGE ? 

F

MODULE: 10 DAMAGE ? 

F

MODULE: 1 BURNING? 

F

MODULE: 2 BURNING? 

F

MODULE: 3 BURNING? 

F

MODULE: 4 BURNING? 

F

w MODULE: 5 BURNING? 

F

MODULE: 6 BURNING? 

F

MODULE: 7 BURNING? 

F

MODULE: 8 BURNING? 

F

MODULE: 9 BURNING? 

F

MODULE: 10 BURNING? 

T

MODULE: 1 SOURCE FLUX .333E+04

MODULE: 2 SOURCE FLUX 483.

MODULE: 3 SOURCE FLUX .0

MODULE: 4 SOURCE FLUX .0

MODULE: 5 SOURCE FLUX .0

MODULE: 6 SOURCE FLUX .0

MODULE: 7 SOURCE FLUX .0

MODULE: 8 SOURCE FLUX .0

MODULE: 9 SOURCE FLUX .0

MODULE: 10 SOURCE FLUX .158E+06
MODULE: I EXTERNAL FLUX .239E+04

MODULE: 2 EXTERNAL FLUX 526.

MODULE: 3 EXTERNAL FLUX 386.

MODULE: 4 EXTERNAL FLUX 403.

MODULE: 5 EXTERNAL FLUX 386.

MODULE: 6 EXTERNAL FLUX 383.

MODULE: 7 EXTERNAL FLUX 399.

MODULE: 8 EXTERNAL FLUX 383.

MODULE: 9 EXTERNAL FLUX .190E+04

MODULE: 10 EXTERNAL FLUX .163E+04

MODULE: 1 TOTAL FLUX .899E+04

MODULE: 2 TOTAL FLUX .778E014

MODULE: 3 TOTAL FLUX .769E+04

MODULE: 4 TOTAL FLUX .770E+04

MODULE: 5 TOTAL FLUX .769E+04

MODULE: 6 TOTAL FLUX .768E+04

MODULE: 7 TOTAL FLUX .770E÷04

MODULE: 8 TOTAL FLUX .768E+04

MODULE: 9 TOTAL FLUX .451E+04

MODULE: 10 TOTAL FLUX .433E+04.

MODULE: 1 MEAS'D FLUX .572E+04

MODULE: 2 MEAS'D FLUX .451E+04

MODULE: 3 MEAS'D FLUX .442E+04

MODULE: 4 MEAS'D FLUX .443E+04

MODULE: 5 MEAS'D FLUX .442E+04

MODULE: 6 MEAS'D FLUX .441E+04

MODULE: 7 MEAS'D FLUX .442E÷04

MODULE: 8 MEAS'D FLUX .441E+04

MODULE: 9 HEAS'D FLUX .123E+04

MODULE: 10 MEAS'D FLUX .106E÷04

MODULE: 1 NET FLUX .568E+04

MODULE: 2 NET FLUX .448E÷04

MODULE: 3 NET FLUX .370E+04

MODULE: 4 NET FLUX .370E+04

MODULE: 5 NET FLUX .370E+04

MODULE: 6 NET FLUX .370E+04

MODULE: 7 NET FLUX .370E+•4

MODULE: 8 NET FLUX .370E+04

MODULE: 9 NET FLUX .105E+04

MODULE: 10 NET FLUX .106E+04
IMODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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MODULE:

MODULE:

MODULE:

123456789

10123

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10123456789

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FUEL M

FUEL M

FUEL H

FUEL H

FUEL H

FUEL M

FUEL M

FUEL M

FUEL M

FUEL M

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FUEL 1

FUEL 1

FUEL

FUEL 1

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

ASS

ASS

[ASS

LASS

IASS

IASS

ASS

lASS

ASS

ASS

HGT

HGT

HOT

HGT

HGT

HGT

HGT

HOT

HOT

HGT

.0

.0

.0

.0

.0

.0

.0

.0

.0

2.88

.150E+04 610.

2.25

2.25

2.25

2.25

2.25

2.25

2.25

12.9

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

rEMP

TEMP

FEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

.0

.0

.0

.0

.0

.0

.0

.0

.0

.129E+04#

306.

304.

388.

389.

388.

388.

389.

388.

323.

298.
MODULE: 1 HEAT TRANS COEF 10.0

NODULE: 2 HEAT TRANS COEF 10.0

MODULE: 3 HEAT TRANS COEF 10.0

MODULE: 4 HEAT TRANS COEF 10.0

MODULE: 5 HEAT TRANS COEF 10.0

MODULE: 6 HEAT TRANS COEF 10.0

MODULE: 7 HEAT TRANS COEF 10.0

MODULE: 8 HEAT TRANS 0OEF 10.0

MODULE: 9 HEAT TRANS COEF 10.0

MODULE: 10 HEAT TRANS 0OEF 10.0

MODULE: 1 ENVIRONMENT TEMP 505.

NODULE: 2 ENVIRONMENT TEMP 505.

MODULE: 3 ENVIRONMENT TEMP 505.

MODULE: 4 ENVIRONMENT TEMP 505.

MODULE: 5 ENVIRONMENT TEMP 505.

MODULE: 6 ENVIRONMENT TEMP 505.

MODULE: 7 ENVIRONMENT TEMP 505.

MODULE: 8 ENVIRONMENT TEMP 505.

NODULE: 9 ENVIRONMENT TEMP 298.

MODULE: 10 ENVIRONMENT TEMP 298.
****• TEST CASE: SNL CABLE TRAY EXPERIMENT #1 (EFF=0.8) COMP3 

•

TIME (SEC): 180.

TOTAL MASS BURNING RATE (KG/S): .2893E-01

TOTAL HEAT RELEASE RATE (W) : .1190E+07

HOT GAS LAYER TEMPERATURE (K) : 505.4

HOT GAS LAYER THICKNESS (M) : 1.445

MODULE: 1 DAMAGE ? 

F

MODULE: 2 DAMAGE ? 

F

MODULE: 3 DAMAGE ? 

F

MODULE: 4 DAMAGE ? 

F

MODULE: 5 DAMAGE ? 

F

MODULE: 6 DAMAGE ? 

F

MODULE: 7 DAMAGE ? 

F

MODULE: 8 DAMAGE ? 

F

MODULE: 9 DAMAGE ? 

F

MODULE: 10 DAMAGE ? 

F

MODULE: 1 BURNING? 

F

MODULE: 2 BURNING? 

F

MODULE: 3 BURNING? 

F

MODULE: 4 BURNING? 

F

"4 MODULE: 5 BURNING? 

F

MODULE: 6 BURNING? 

F

MODULE: 7 BURNING? 

F

MODULE: 8 BURNING? 

F

MODULE: 9 BURNING? 

F

MODULE: 10 BURNING? 

T

MODULE: 1 SOURCE FLUX .335E+04

MODULE: 2 SOURCE FLUX 500.

MODULE: 3 SOURCE FLUX .0

MODULE: 4 SOURCE FLUX .0

MODULE: 5 SOURCE FLUX .0

MODULE: 6 SOURCE FLUX .0

MODULE: 7 SOURCE FLUX .0

MODULE: 8 SOURCE FLUX .0

MODULE: 9 SOURCE FLUX .0

MODULE: 10 SOURCE FLUX .158E+06
MODULE: I EXTERNAL FLUX .239E+04

MODULE: 2 EXTERNAL FLUX 526.

MODULE: 3 EXTERNAL FLUX 394.

MODULE: 4 EXTERNAL FLUX 411.

MODULE: 5 EXTERNAL FLUX 394.

MODULE: 6 EXTERNAL FLUX 392.

MODULE: 7 EXTERNAL FLUX 409.

MODULE: 8 EXTERNAL FLUX* 392.

MODULE: 9 EXTERNAL FLUX .192E+04

MODULE: 10 EXTERNAL FLUX .165E+04

MODULE: 1 TOTAL FLUX .901E+04

MODULE: 2 TOTAL FLUX .780E+04

MODULE: 3 TOTAL FLUX .771E+04

MODULE: 4 TOTAL FLUX .773E+04

MODULE: 5 TOTAL FLUX .771E04

MODULE: 6 TOTAL FLUX .771E+04

MODULE: 7 TOTAL FLUX .772E+04

MODULE: 8 TOTAL FLUX .771E+04

MODULE: 9 TOTAL FLUX .452E÷04

MODULE: 10 TOTAL FLUX .434E+04

MODULE: 1 MEAS'D FLUX .574E+04

MODULE: 2 MEAS'D FLUX .453E+04

MODULE: 3 MEAS'D FLUX .444E+04

MODULE: 4 MEAS'D FLUX .446E+04

MODULE: 5 MEAS'D FLUX .444E+04

MODULE: 6 MEAS'D FLUX .444E+04

MODULE: 7 MEAS'D FLUX .445E+04

MODULE: 8 MEAS'D FLUX .444E+04

MODULE: 9 MEAS'D FLUX .125E+04

MODULE: 10 MEAS'D FLUX .107E÷04

MODULE: 1 NET FLUX .563E+04

MODULE: 2 NET FLUX .444E+04

MODULE: 3 NET FLUX .299E÷O4

MODULE: 4 NET FLUX .300E+04

MODULE: 5 NET FLUX .299E04

MODULE: 6 NET FLUX .299E+04

MODULE: 7 NET FLUX .300E+04

MODULE: 8 NET FLUX .299E+04

MODULE: 9 NET FLUX 885.

MODULE: 10 NET FLUX .107E+04
I-h

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MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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MODULE:

MODULE:

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MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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MODULE:

MODULE:

MODULE:

MODULE;

MODULE:

MODULE:

MODULE:

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MODULE:

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FUEL 1

FUEL

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FUEL 1

ASS

ASS

ASS

ASS

ASS

ASS

ASS

ASS

PASS

PASS

HGT

HGT

HGT

HGT

HGT

HGT

HGT

HGT

HOT

HGT

.0

.0

.0

.0

.0

.0

.0

.0

.0

2.88

.150E+04

610.

2.25

2.25

2.25

2.25

2.25

2.25

2.25

12.9

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

rEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

.0

.0

.0

.0

.0

.0

.0

.0

.0

.129E+04

311.

308.

400.

400.

400.

399.

400.

399.

327.

298.
MODULE: 1 HEAT TRANS COEF 10.0

MODULE: 2 HEAT TRANS COEF 10.0

MODULE: 3 HEAT TRANS COEF 10.0

MODULE: 4 HEAT TRANS COEF 10.0

MODULE: 5 HEAT TRANS COEF 10.0

MODULE: 6 HEAT TRANS COEF 10.0

MODULE: 7 HEAT TRANS COEF 10.0

MODULE: 8 HEAT TRANS COEF 10.0

MODULE: 9 HEAT TRANS COEF 10.0

MODULE: 10 HEAT TRANS COEF 10.0

MODULE: 1 ENVIRONMENT TEMP 505.

MODULE: 2 ENVIRONMENT TEMP 505.

MODULE: 3 ENVIRONMENT TEMP 505.

MODULE: 4 ENVIRONMENT TEMP 505.

MODULE: 5 ENVIRONMENT TEMP 505.

MODULE: 6 ENVIRONMENT TEMP 505.

MODULE: 7 ENVIRONMENT TEMP 505.

MODULE: 8 ENVIRONMENT TEMP 505.

MODULE: 9 ENVIRONMENT TEMP 298.

MODULE: 10 ENVIRONMENT TEMP 298.

C
***** TEST CASE: SNL CABLE TRAY EXPERIMENT #1 (EFF=O.8) COMP3 •

TIME (SEC): 240.

TOTAL MASS BURNING RATE (KG/S): .2893E-01

TOTAL HEAT RELEASE RATE (W) .1190E+07

HOT GAS LAYER TEMPERATURE (K) 506.2

HOT GAS LAYER THICKNESS (M) : 1.445

MODULE: 1 DAMAGE ? F

MODULE: 2 DAMAGE ? F

MODULE: 3 DAMAGE ? F

MODULE: 4 DAMAGE ? F

MODULE: 5 DAMAGE ? F

MODULE: 6 DAMAGE ? F

MODULE: 7 DAMAGE ? F

MODULE: 8 DAMAGE ? F

MODULE: 9 DAMAGE ? F

MODULE: 10 DAMAGE ? F

MODULE: 1 BURNING? F

MODULE: 2 BURNING? F

MODULE: 3 BURNING? F

MODULE: 4 BURNING? F

MODULE: 5 BURNING? F

MODULE: 6 BURNING? F

MODULE: 7 BURNING? F

MODULE: 8 BURNING? F

MODULE: 9 BURNING? F

MODULE: 10 BURNING? T

MODULE: 1 SOURCE FLUX .337E+04

MODULE: 2 SOURCE FLUX 518.

MODULE: 3 SOURCE FLUX .0

MODULE: 4 SOURCE FLUX .0

MODULE: 5 SOURCE FLUX .0

MODULE: 6 SOURCE FLUX .0

MODULE: 7 SOURCE FLUX .0

MODULE: 8 SOURCE FLUX .0

MODULE: 9 SOURCE FLUX .0

MODULE: 10 SOURCE FLUX .158E+06
NODULE: 1 EXTERNAL FLUX .239E+04

MODULE: 2 EXTERNAL FLUX 526.

MODULE: 3 EXTERNAL FLUX 402.

MODULE: 4 EXTERNAL FLUX 420.

MODULE: 5 EXTERNAL FLUX 402.

MODULE: 6 EXTERNAL FLUX 401.

MODULE: 7 EXTERNAL FLUX 418.

MODULE: 8 EXTERNAL FLUX 401.

MODULE: 9 EXTERNAL FLUX .194E+O4

MODULE: 10 EXTERNAL FLUX .166E+04

MODULE: 1 TOTAL FLUX .904E04

MODULE: 2 TOTAL FLUX .782E+04

MODULE: 3 TOTAL FLUX .774E+04

MODULE: 4 TOTAL FLUX .775E+04

MODULE: 5 TOTAL FLUX .774E÷04

MODULE: 6 TOTAL FLUX .774E÷04

NODULE: 7 TOTAL FLUX .775E+04

MODULE: 8 TOTAL FLUX .774E+04

MODULE: 9 TOTAL FLUX .453E)04

MODULE: 10 TOTAL FLUX .435E+04

NODULE: 1 MEAStD FLUX .577E04

14ODULE: 2 MEAS'D FLUX .455E+04

MODULE: 3 NEAS'D FLUX .447E+04

MODULE: 4 MEAS'D FLUX .448E+04

MODULE: 5 MEAS'D FLUX .447E+04

MODULE: 6 MEAS'D FLUX .447E+04

MODULE: 7 MEAS'D FLUX .448E+04

MODULE: 8 MEAS'D FLUX .447E4"04

MODULE: 9 NEAS'D FLUX .126E+04

MODULE: 10 MEAS'D FLUX .108E+04

MODULE: 1 NET FLUX .558E+O4

MODULE: 2 NET FLUX .441E+04

MODULE: 3 NET FLUX .281E04

MODULE: 4 NET FLUX .281E+04

MODULE: 5 NET FLUX .281E+04

MODULE: 6 NET FLUX .281E+04

MODULE: 7 NET FLUX .282E+04

MODULE: 8 NET FLUX .281E+04

MODULE: 9 NET FLUX 837.

MODULE: 10 NET FLUX .108E+04
MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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MODULE:

MODULE:

MODULE:

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MODULE:

MODULE:

MODULE:

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MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

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TEMP

TEMP

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TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

.150E+04

610.

2.25

2.25

2.25

2.25

2.25

2.25

2.25

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316.

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414.

332.

298.
MODULE: 1 HEAT TRANS COEF 10.0

MODULE: 2 HEAT TRANS COEF 10.0

NODULE: 3 HEAT TRANS COEF 10.0

MODULE: 4 HEAT TRANS COEF 10.0

MODULE: 5 HEAT TRANS COEF 10.0

MODULE: 6 HEAT TRANS COEF 10.0

MODULE: 7 HEAT TRANS COEF 10.0

MODULE: 8 HEAT TRANS COEF 10.0

MODULE: 9 HEAT TRANS COEF 10.0

MODULE: 10 HEAT TRANS COEF 10.0

MODULE: 1 ENVIRONMENT TEMP 506.

MODULE: 2 ENVIRONMENT TEMP 506.

MODULE: 3 ENVIRONMENT TEMP 506.

MODULE: 4 ENVIRONMENT TEMP 506.

MODULE: 5 ENVIRONMENT TEMP 506.

MODULE: 6 ENVIRONMENT TEMP 506.

MODULE: 7 ENVIRONMENT TEMP 506.

MODULE: 8 ENVIRONMENT TEMP 506.

MODULE: 9 ENVIRONMENT TEMP 298.

MODULE: 10 ENVIRONMENT TEMP 298.

H>
***** TEST CASE: SNL CABLE TRAY EXPERIMENT #1 (EFF=0.8) COMP3 4*

TIME (SEC): 300.

TOTAL MASS BURNING RATE (KG/S): .2893E-01

TOTAL HEAT RELEASE RATE (W) : .1190E+07

HOT GAS LAYER TEMPERATURE (K) : 506.9

HOT GAS LAYER THICKNESS (M) : 1.445

MODULE: 1 DAMAGE ? 

F

MODULE: 2 DAMAGE ? 

F

MODULE: 3 DAMAGE ? 

F

MODULE: 4 DAMAGE ? 

F

MODULE: 5 DAMAGE ? 

F

MODULE: 6 DAMAGE ? 

F

MODULE: 7 DAMAGE ? 

F

MODULE: 8 DAMAGE ? 

F

MODULE: 9 DAMAGE ? 

F

MODULE: 10 DAMAGE ? 

F

MODULE: 1 BURNING? 

F

MODULE: 2 BURNING? 

F

MODULE: 3 BURNING? 

F

t% MODULE: 4 BURNING? 

F

MODULE: 5 BURNING? 

F

MODULE: 6 BURNING? 

F

MODULE: 7 BURNING? 

F

MODULE: 8 BURNING? 

F

MODULE: 9 BURNING? 

F

MODULE: 10 BURNING? 

T

MODULE: 1 SOURCE FLUX .340E+04

MODULE: 2 SOURCE FLUX 535.

MODULE: 3 SOURCE FLUX .0

MODULE: 4 SOURCE FLUX .0

MODULE: 5 SOURCE FLUX .0

MODULE: 6 SOURCE FLUX .0

MODULE: 7 SOURCE FLUX .0

MODULE: 8 SOURCE FLUX .0

MODULE: 9 SOURCE FLUX .0

MODULE: 10 SOURCE FLUX .158E+06
MODULE: 1 EXTERNAL FLUX .239E+04

MODULE: 2 EXTERNAL FLUX 526.

MODULE: 3 EXTERNAL FLUX 410.

MODULE: 4 EXTERNAL FLUX 428.

MODULE: 5 EXTERNAL FLUX 410.

MODULE: 6 EXTERNAL FLUX 411.

MODULE: 7 EXTERNAL FLUX 428.

MODULE: 8 EXTERNAL FLUX 411.

MODULE: 9 EXTERNAL FLUX .196E+04

MODULE: 10 EXTERNAL FLUX .167E+04

MODULE: 1 TOTAL FLUX .906E÷04

MODULE: 2 TOTAL FLUX .784E04

MODULE: 3 TOTAL FLUX .777E+04

MODULE: 4 TOTAL FLUX .778E÷04

MODULE: 5 TOTAL FLUX .777E+04

MODULE: 6 TOTAL FLUX .777E+04

MODULE: 7 TOTAL FLUX .778E÷04

MODULE: 8 TOTAL FLUX .777E+04

MODULE: 9 TOTAL FLUX .455E+04

MODULE: 10 TOTAL FLUX .436E+04

MODULE: I MEAS'D FLUX .579E+04

MODULE: 2 MEAS'D FLUX .457E+04

MODULE: 3 MEAS'D FLUX .450E+04

MODULE: 4 MEAS'D FLUX .451E+04

MODULE: 5 MEAS'D FLUX .450E+04

MODULE: 6 MEAS'D FLUX .450E+04

MODULE: 7 MEAS'D FLUX .451Ee04

MODULE: 8 MEAS'D FLUX .450E÷04

MODULE: 9 MEAS'D FLUX .128E+04

MODULE: 10 MEAS'D FLUX .108E÷04

MODULE: 1 NET FLUX .553E+04

MODULE: 2 NET FLUX .437E+04

MODULE: 3 NET FLUX .254E+04

MODULE: 4 NET FLUX .254E+04

MODULE: 5 NET FLUX .254E+04

MODULE: 6 NET FLUX .254E+04

MODULE: 7 NET FLUX .254E+04

MODULE: 8 NET FLUX .254E+04

MODULE: 9 NET FLUX 779.

MODULE: 10 NET FLUX .108E+04
IA

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

MODULE:

123456789

10123

.456789

10123456789

10123

'456789

10

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FLAME

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

FUEL

HOT

HOT

HOT

HGT

HOT

HOT

HOT

HOT

HGT

HGT

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

FUEL MASS

.150E+04

610.

2.25

2.25

2.25

2.25

2.25

2.25

2.25

12.9

.0

.0

.0

.0

.0

.0

.0

.0

.0

2.88

.0

.0

.0

.0

.0

.0

.0

.0

.0

.129E+04

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

TEMP

321.

316.

421.

421.

421.

421.

421.

421.

335.

298.
MODULE: 1 HEAT TRANS COEF 10.0

MODULE: 2 HEAT TRANS COEF 10.0

MODULE: 3 HEAT TRANS COEF 10.0

MODULE: 4 HEAT TRANS COEF 10.0

MODULE: 5 HEAT TRANS COEF 10.0 MODULE: 6 HEAT TRANS COEF 10.0

MODULE: 7 HEAT TRANS COEF 10.0 MODULE: 8 HEAT TRANS COEF 10.0

MODULE: 9 HEAT TRANS COEF 10.0

MODULE: 10 HEAT TRANS COEF 10.0

MODULE: 1 ENVIRONMENT TEMP 507.

MODULE: 2 ENVIRONMENT TEMP 507.

MODULE: 3 ENVIRONMENT TEMP 507.

MODULE: 4 ENVIRONMENT TEMP 507.

MODULE: 5 ENVIRONMENT TEMP 507.

MODULE: 6 ENVIRONMENT TEMP 507.

MODULE: 7 ENVIRONMENT TEMP 507.

MODULE: 8 ENVIRONMENT TEMP 507. MODULE: 9 ENVIRONMENT TEMP 298. MODULE: 10 ENVIRONMENT TEMP 298.

I-
Appendix B

CODE LISTING

- 129 -
C *

C COMPBRN III - REVISED COMPUTER CODE FOR MODELING THE BEHAVIOR *

C OF COMPARTMENT FIRES

C *

C AUTHORS - VINCENT HO AND NATHAN SIU

C *

C *

C MAIN PROGRAM (READS INPUT DATA, CALLS SUBROUTINES) *

C

C* ........ AAAA:.... ******A;AAAA*AAAAA.~!A:A,......

IMPLICIT LOGICAL (L)

DOUBLE PRECISION XNAIIE

C

C

C

FUEL CELL ARRAYS: DIMENSION=(IDIM1 X IDIM2)

DIMENSION

1

2

3

4

5

6

BRAT(30,5), FLHT(30,5), FLTEMP(30,5), FMASS(30,5),

FX(30,5), FY(30,5), FZ(30,5), GAMN(30,5), HCOEF(30,5),

HCOEFO(30,5), Q(30,5), QDOTC(30,5), QDOT2P(30,5),

QEXCAL(30,5), QEXNET(30,5), QEXT(30,5), QEXTOT(30,5),

QEXTO(30,5), TSURR(30,5), TSURRO(30,5), TE MP(30,5,10),

ICOUNT(30,5), LBURN(30,5), LDAMGE(30,5),_LFMASS(30,5),

LPIGN(30,5), LPLUME(30,5), LSTRTO(30,5), LTOP(30,5)

C

C

C

C

C

C

C

C

C

SUPER-MODULE VECTORS: DIMENSION=(IDIM1)

DIMENSION AREA(30), DELS(30), DEP(30), FLNG(30), FLOSS(30),

1 FMASS0(30), RAD(30), POR(30), WID(30),

2 IDIR(30), IORT(30), ITYP(30), MSMOUT(30), NFC(30),

3 LB(30), LC(30), LD(30), LW(30)

FUEL TYPE VECTORS: DIMENSION=(IDIM6)

DIMENSION BRATS0(5), BRATS1(5), BRATV(5), DENS(5), DIFF(5),

1 EFF(S), FABSRP(5), FIGTP(5), FIGTS(5), GAMMA(5),

2 HEAT(5), FTDAM(5),SPHT(5), REFL(5), THX(5),

3 IFUEL(5),

4 LBF(5), LCF(5), LDF(5), LWF(5)

PILOT FIRE VECTORS: DIMENSION=(IDIM7)

DIMENSION

1

2

3

PBRATV(10), PBRTSO(10), PBRTS1(1O), PEFF(1O),

PHEAT(10), PMASS(10), PMDOTS(10),

IPIL(10), IPFUEL(1O), JPIL(1O),

LPMASS(10)

C

C

C

C

C

C

C

COMMUNICATION ARRAYS AND VECTORS:

ICOMM DIMENSION=(IDIM1*IDIM2 X IDIMI*IDIM2)

IAD DIMENSION=(IDIM4 X 4)

NAD DIMENSION=(IDIM5 X 4)

DIMENSION IV(4), NV(4), ICOMM(150,150), IAD(30,4), NAD(200,4)

- 130 -
c

C MISCELLANEOUS VECTORS

C

DIMENSION XNAME(12)

C

C NAMELIST DESIGNATIONS

C

NAMELIST /STRT/ NJOB,NTIME, NREAD, NWRITE, DELT

NAMELIST /SIZE/ NSM, NCOM, NFUEL, NNCOM, NPILOT, IROOM, INITG

NAMELIST /FUELB/ SMX, SMY, SMZ, SLNG, SWID, SDEP, SMASS, SPOR,

1 SLOSS, NFCL, IORNT, IDIREC, IFTYP

NAMELIST /PILOT/ IPIL, JPIL, IPFUEL, PMASS

NAMELIST /FUELT/ IFUEL, DENS, SPliT, THK, HEAT, EFF, FIGTP, FTDAM,

1 FIGTS, BRATV, BRATSO, BRATS1, GAMMA, FABSRP, REFL

NAMELIST /SEE/ IV

NAMELIST /NSEE/ NV

NAMELIST /MISC/ RTEMP, FLCF, HROOM, CALTEM

C

C OLD VERSION:

C NAMELIST /ROOM/ DWID, DHGT, DCF, FC, FH, GABSRP, HCEIL, PLCF1,

C 1 PLCF2, THETA, VFV

C

C NEW VERSION:

C

NAMELIST /ROOM/ DCFIN, DCFOUT, DHGT, DWID, FC, FH, GABSRP,

1 HCEIL, PLCF, VFV

NAMELIST /GINIT/ TG, DG, QEXT

NAMELIST /MODVAR/ FCTR

NAMELIST /OUTF/ INCHCK, IOUTPT, MOUTPT, NSMOUT, MSMOUT

C

C COMMON STATEMENTS

C

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

1 FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

2 RADCON, TG, VFV, WHEAT, ZD, ZN,

3 LSMALL

C

C DATA STATEMENTS

C

DATA IDIM1/30/, IDIM2/5/, IDIM3/150/, IDIM4/30/, IDIM5/200/,

1 IDIM6/5/, IDIM7/10/, IDIM8/17/, NREAD/5/, NWRITE/6/

DATA XNAME/8H$STRT ,8H$SIZE ,8H$FUELB ,8H$PILOT

I 8H$FUELT ,8H$SEE ,8H$NSEE ,8H$MISC

2 8H$ROOM ,8H$GINIT ,8H$MODVAR ,8H$OUTF

C

C BEGIN DATA INPUT

C

LINERR = .FALSE.

READ (NREAD,STRT)

C ERROR CHECKING AND DEFAULT SETTINGS FOR NAMELIST STRT

- 131 -
IF ((NJOB*NTIME*NREAD*NWRITE).GT.0) GO TO 100

WRITE (NWRITE,9501) XNAME(1)

NJOB =MAXO(1,NJOB)

NTIME = MAXO(1,NTIME)

IF (NREAD.LE.0) NREAD = 5

IF (NWRITE.LE.0) NWRITE = 6

100 IF (DELT.GT.O.) GO TO 200

LINERR = .TRUE.

WRITE (NWRITE,9502) XNAME(1)

C

C IF (NJOB.LE.O) NJOB = 1

200 DO 8000 IJOB=1,NJOB

C

C JOB-SPECIFIC INPUT DATA

C

READ (NREAD, SIZE)

C ERROR CHECKING FOR NAMELIST SIZE

IF ((NSM*NFUEL*NPILOT).GT-O) GO TO 300

LINERR = .TRUE.

WRITE (NWRITE,9503) XNAME(2), IJOB

300 IF (NSM.LE.IDIMl) GO TO 310

LINERR = .TRUE.

WRITE (NWRITE,9504) XNAME(2), IJOB, IDIM1

310 IF (NFUEL.LE.IDIM6) GO TO 320

LINERR = .TRUE.

WRITE (NWRITE,9505) XNAME(2), IJOB, IDIM6

320 IF (NPILOT.LE.IDIM7) GO TO 330

LINERR = .TRUE.

WRITE (NWRITE,9506) XNAME(2), IJOB, IDIM7

330 IF (NCOM.LE.IDIM4) GO TO 340

LINERR = .TRUE.

WRITE (NWRITE,9507) XNAME(2), IJOB, IDIM4

340 IF (NNCOM.LE.IDIM5) GO TO 350

LINERR = .TRUE.

WRITE (NWRITE,9508) XNAME(2), IJOB, IDIM5

C

C

C

C

350 READ (NREAD,9100) TITLE

READ FUEL BED CHARACTERISTICS

DO 1000 I=1,NSM

READ (NREAD,FUELB)

C ERROR CHECKING FOR NAMELIST FUELB

IF ((NFCL*IORNT*IDIREC*IFTYP).GT.0) G(

LINERR = .TRUE.

WRITE (NWRITE,9509) XNAMIE(3), IJOB, I

400 IF (NFCL.LE.IDIM2) GO TO 410

LINERR = .TRUE.

WRITE (NWRITE,9510) XNAMIE(3), IJOB, I

410 IF (IORNT.LE.3) GO TO 420

LINERR = .TRUE.

WRITE (NWRITE,9511) XNAME(3), IJOB, I

420 IF (IDIREC.LE.3) GO TO 430

LINERR = .TRUE.

) TO 400

, IDIM2

- 132 -
WRITE (NWRITE,9512) XNAME(3), IJOB, I

430 IF (IFTYP.LE.NFUEL) GO TO 440

LINERR = .TRUE.

WRITE (NWRITE,9513) XNAME(3), IJOB, I, NFUEL

440 IF (IORNT.NE.IDIREC) GO TO 450

WRITE (NWRITE,9514) XNAME(3), IJOB, I

450 IF ((SLNG*SWID*SDEP*SMASS*SPOR).GT.O.) GO TO 460

LINERR = .TRUE.

WRITE (NWRITE,9515) XNAME(3), IJOB, I

C

460 XNFCL = FLOAT(NFCL)

DELS(I) = SLNG/XNFCL

AREA(I) = DELS(I)*SWID

RAD(I) = SQRT(AREA(I)/3.14159)

C

C CORRECTION TO COMPUTATION OF FUEL CELL RADIUS

C

C OLD VERSION:

C IF (IORNT.EQ.3) RAD(I) = SWID/2.

C

C NEW VERSION:

C

IF (IORNT.NE.3) RAD(I) = SWID/2.

C

FMASSO(I) = SMASS/XNFCL

WID(I) = SWID

POR(I) = SPOR

FLOSS(I) SLOSS

FLNG(I) = SING

DEP(I) SDEP

IDIR(I) IDIREC

IORT(I) = IORNT

ITYP(I) = IFTYP

NFC(I) = NFCL

LD(I) = .FALSE.

LW(I) = .FALSE.

LB(I) = .FALSE.

LC(I) = .FALSE.

CALL SETUP(I,IDIREC,IDIH1,IDIM2,NFCL,SMX,SMY,SMZ,SLNG,DELS(I),

1 FXFYFZ)

DO 500 J=I,NFCL

FMASS(I,J) = FHASSO(I)

500 CONTINUE

1000 CONTINUE

C

C READ PILOT FIRE CHARACTERISTICS

C

READ (NREAD,PILOT)

C ERROR CHECKING FOR NAMELIST PILOT

DO 2000 I=1,NPILOT

IF ((IPIL(I)*JPIL(I)*IPFUEL(I)).GT.0) GO TO 1100

LINERR = TRUE.

WRITE (NWRITE,9516) XNAME(4), IJOB, I

1100 IF (IPIL(I).LE.NSM) GO TO 1200

- 133 -
LINERR = .TRUE.

WRITE (NWRITE,9517) XNAME(4), IJOB, I, NSM

1200 IF (JPIL(I).LE.NFC(IPIL(I))) GO TO 1300

LINERR = .TRUE.

WRITE (NWRITE,9518) XNAME(4), IJOB, I, NFC(IPIL(I))

1300 IF (IPFUEL(I).LE.NFUEL) GO TO 1400

LINERR = .TRUE.

WRITE (NWRITE,9519) XNAME(4), IJOB, I, NFUEL

1400 IF (PMASS(I).GT.0.) GO TO 2000

LINERR = .TRUE.

WRITE (NWRITE,9520) XNAME(4), IJOB, I

2000 CONTINUE

C

C

C READ FUEL TYPE CHARACTERISTICS

C

READ (NREAD ,FUELT)

DO 2900 I=1,NFUEL

C ERROR CHECKING FOR NAMELIST FUELT

IF (IFUEL(I).GT.O) GO TO 2100

LINERR = .TRUE.

WRITE (NWRITE,9521) XNAME(S), IJOB, I

2100 IF ((DENS(I)*SPHT(I)*THK(I)).GT.0.) GO TO 2200

LINERR = .TRUE.

WRITE (NWRITE,9522) XNAME(5), IJOB, I

2200 IF (IFUEL(I).GE.10) GO TO 2400

IF ((HEAT(I)*EFF(I)*GAMMA(I)).GT.O.) GO TO 2300

LINERR -. TRUE.

WRITE (NWRITE,9523) XNAME(5), IJOB,I

2300 IF ((EFF(I).LE.1.).OR.(GAMMA(I).LE.1.)) GO TO 2•

LINERR = .TRUE.

WRITE (NWRITE,9524) XNAME(5), IJOB, I

MO0

C

2400 DIFF(I) = THK(I)/(DENS(I)*SPHT(I))

LDF(I) .FALSE.

LWF(I) .FALSE.

LBF(I) = .FALSE.

LCF(I) = .FALSE.

ITYPE = IFUEL(I)

IF (ITYPE.LT.10) GO TO 2900

IF ((ITYPE.GE.10).AND.(ITYPE.LT.20))

IF ((ITYPE.GE.20).AND.(ITYPE.LT.30))

IF ((ITYPE.GE.30).AND.(ITYPE.LT.40))

IF ((ITYPE.GE.40).AND.(ITYPE.LT.50))

DO 2500 J=1,NSM

IF (ITYP(J).NE.I) GO TO 2500

IF (LDF(I)) LD(J) = .TRUE.

IF (LWF(I)) LW(J) = .TRUE.

IF (LBF(I)) LB(J) = .TRUE.

IF (.NOT.LCF(I)) GO TO 2500

LC(J) = .TRUE.

ICEIL = J

2500 CONTINUE

2900 CONTINUE

?(I) = .TRUE.

M(I= .TRUE.

?(I) = .TRUE.

?(I) = .TRUE.

LDI

LW! LBF

LC•

- 134 -
READ (NREAD,MISC)

C DEFAULT SETTING FOR NAMELIST MISC

RTEMP = AMAX1(0.,RTEMP)

C

DO 3100 I=1,IDIM3

DO 3000 J=1,IDIM3

ICOMM(I,J) = 1

3000 CONTINUE

3100 CONTINUE

IF (NCOM.LE.0) GO TO 3500

DO 3300 I=1,NCOM

READ (NREAD, SEE)

DO 3200 J=1,4

IAD(I,J) = IV(J)

3200 CONTINUE

3300 CONTINUE

3500 IF (NNCOM.LE.0) GO TO 3900

DO 3800 I=1,NNCOM

READ (NREADNSEE)

DO 3700 J=1,4

NAD(I,J) = NV(J)

3700 CONTINUE

3800 CONTINUE

3900 CALL COMM(NCOM,NNCOM,NSM, IDIMI, IDIM3,IDIM4, IDIM5,NFC,IAD,NAD,

1 ICOMM)

LROOM = (IROOM.EQ.1)

IF (.NOT.LROOM) GO TO 5000

C

C READ ROOM CHARACTERISTICS

C

READ (NREAD, ROOM)

C DEFAULT SETTINGS FOR NAMELIST ROOM

IF (DCFIN.EQ.0.) DCFIN = 1.

IF (DCFOUT.EQ.0.) DCFOUT=I.

IF (GABSRP.EQ.0.) GABSRP-I..3

IF (PLCF.EQ.0.) PLCF = 2.

CFV = 352.6*VFV

IF (INITG.EQ.1) READ (NREAD,GINIT)

C

C THE VARIABLE WFVC IS NO LONGER NEEDED

C WFVC = CFV/RTEMP

C

5000 READ (NREADJMODVAR)

C DEFAULT SETTINGS FOR NAMELIST MODVAR

DO 6000 I=1,15

IF (FCTR(I).LE.O.0) FCTR(I) = 1.0

6000 CONTINUE

READ (NREAD, OUTF)

C ERROR CHECKING FOR NAMELIST OUTF

IF (IOUTPT.GE.0) GO TO 6500

LINERR = .TRUE.

WRITE (NWRITE,9525) XNAME(12), IJOB

IF (IOUTPT.EQ.0) GO TO 6500

DO 6400 I=1,IOUTPT

- 135 -
IF (MOUTPT(I).GT.0) GO TO 6200

LINERR .TRUE.

WRITE (NWRITE,9526) XNAME(12), IJOB, I

GO TO 6400

6200 IF (MOUTPT(I).LE.IDIM8) GO TO 6400

LINERR = .TRUE.

WRITE (NWRITE,9527) XNAME(12), IJOB, I, IDIM8

6400 CONTINUE

6500 IF (NSMOUT.LE.NSM) GO TO 6900

LINERR - .TRUE.

WRITE (NWRITE,9528) XNAME(12), IJOB

IF (NSMOUT.LE.0) GO TO 6900

DO 6800 I=1,NSMOUT

IF (MSMOUT(I).GT.0) GO TO 6600

LINERR = .TRUE.

WRITE (NWRITE,9529) XNAME(12), IJOB, I

GO TO 6800

6600 IF (MSMOUT(I).LE.NSM) GO TO 6800

LINERR -. TRUE.

WRITE (NWRITE,9530) XNAME(12), IJOB, I

6800 CONTINUE

C

C JOB AND ALL SUBSEQUENT JOBS FAIL IF ANY INPUT ERORS ARE DETECTED

C

6900 IF (LINERR) GO TO 8000

C

C

C MAIN PROGRAM SUBROUTINES

C

C

C ECHO CHECK FOR INPUT DATA

C

CALL INCHK (FXFY,FZ,QEXT,DEP,FLNG,FLOSS,FMASSO,POR,WID,BRATS0,

1 BRATS1,BRATV,DENS ,DIFF,EFF ,FABSRP,FIGTP,FIGTS ,FTDAM,GAMHA,HEAT,

2 REFLSPHT,THK,PMASS,IDIR,IORT,ITYP,NFC,IFUEL,IPIL,IPFUEL,JPIL,

3 IAD,NAD,LBF,LCF,LDF,LWF,IDIM1,IDIM2,IDIM4,IDIM5,NCOM,

4 NFUEL,NJOB,NNCOMNPILOT,NSM,NTIME,NWRITE)

C

C INITIALIZE JOB VARIABLES

C

CALL INIT(FX,FY,FZ,HCOEF,QEXT,TSURR,TEMP,LBURN,LDAMGE,LFMASS,AREA,

I DELS,POR,WID,BRATSO,BRATS 1,BRATV,EFF,HEAT,PBRATV,PBRTSO,PBRTS1,

2 PEFF,PHEAT,PMASS,IDIR, IORT,NFC, IPIL, IPFUEL,JPIL,LPMASS, ICOMM,

3 LB,LC,LW,IDIM1,IDIM2,1IDIM3,NFUEL,NPILOT,NSM)

C

C IN NEW VERSION, AT TIME=0, THE OUTPUT WOULD BE THE INITIAL CONDITION,

C THE STEADY STATE IS ASSUMED TO BE FORMED WITHIN THE FIRST TIME STEP

C

IF (TG.LT.RTEMP) TG = RTEMP

TIME = 0.0

TQDOT = 0.0

TMDOT 0.0

TG = RTEMP

DG = 0.0

- 136 -
CALL OUTPUT(FLHT,FLTEMP,FMASS,HCOEF, QDOT2P, QEXCAL,QEXNET,QEXT,

1 QEXTOT, TEMP,TSURR, LBURN, LDAMGE,NFC ,MSMOUT,

2 IDIH1, IDIH2,NSM, NSMOUT,NWRITE)

TIME = TIME + DELT

DO 7000 ITIME=1,NTIME

C

C TIME-STEP INITIALIZATIONS

C

CALL TINIT(FLHT,FLTEMP,HCOEF,HCOEFO, QQDOT2P,QEXT,QEXTO,TSURR,

1 TSURRO,LPIGN,LPLUME,LSTRTO,NFC, IDIMI IDIM2,NSM)

C

C COMPUTE SOURCE HEAT FLUXES

C

CALL SOURCE(BRAT,FLT, FLTEMP,FMASS,FZ,GAMNQ,QDOTC,QDOT2P,QEXT,

1 QEXTOTEMP,AREADELS,DEP,FMASSO,POR,RAD,WID,PBRATV,PBRTSO,PBRTS1,

2 PEFF,PHF.AT,PMASSPMDOTS,BRATSOBRATS1,BRATV,DIFFEFF,GAMMA,HEAT,

3 REFL,THK,ICOUNT,IORTITYP,NFC,IPILIPFUEL,JPIL,LBURNLFMASS,

4 LSTRTOLTOP,LB,LCLD,LW,LPMASSLDAiGE,IDIM1,IDIM2,NFUEL,NPILOT,

5 NSM,NWRITE)

IF (LEND) GO TO 8000

C

C COMPUTE HEAT FLUX TRANSFER TO RECEIVERS

C

CALL TRANSF(FLIIT FLTEMP,FX,FY,FZ,HCOEF,QDOTC,QDOT2P,QEXCAL,

1 QEXNET,QEXT,QEXTOT,TSURR,TEMP,AREA,DELS,RAD,WID,FABSRP ,GAMMA,

2 REFL, ICOMM,ICOUNTIORT, ITYP,NFC,LBURNLDAMGELPIGN,LPLUME,

3 LB,LC,LD,LW,IDIM1,IDIM2,IDIM3,NFUEL,NSK,NWRITE)

IF (LEND) GO TO 8000

C

C DETERMINE IF OTHER FUEL CELLS IGNITE

C

CALL IGNIT(HCOEF, HCOEFO,QEXT,QEXTO ,TSURR,TSURRO ,TEMP,DEP,DIFF,

1 FIGTP,FIGTS,FTDAM,REFL,THK, ITYPNFC,LBURN, LDAMGELFMASS,LPIGN,

2 LPLUME,LB,LC,LD,LWIIDIM1,IDIM2,NFUELNSH,NWRITE) C "I

C OUTPUT FOR EACH TIME STEP

C

C UPDATED TO ALLOW OUTPUT OF LOCAL CONVECTIVE HEAT TRANSFER

C COEFFICIENT (HCOEF) AND LOCAL ENVIRONMENT TEMPERATURE (TSURR)

C

C OLD VERSION:

C

C CALL OUTPUT(FLHT,FLTEMP,FMASS,QDOT2P, QEXCAL,QEXNET,QEXT,QEXTOT,

C 1 TEMP,LBURN,LDAMGE,NFC,MSMOUT,IDIM1,IDIM2,NSM,NSMOUT,NWRITE)

C 2 IDIK1,IDIM2,NSM,NSMOUT,NWRITE)

C

C NEW VERSION:

C

CALL OUTPUT(FLHT,FLTEMP, FMASS , HCOEF, QDOT2P, QEXCAL,QEXNET,QEXT,

1 QEXTOT, TEMP,TSURR, LBURN, LDAMGE,NFC, MSMOUT,

2 IDIMI, IDIM2,NSM,NSMOUT,NWRITE)

TIME - TIME + DELT

C

7000 CONTINUE

- 137 -
8000 CONTINUE

9100

9501

9502

FORMAT

FORMAT

FORMAT

1

9503 FORMAT

1

9504 FORMAT

1

9505 FORMAT

1

9506 FORMAT

1

9507 FORMAT

1

9508 FORMAT

1

9509 FORMAT

1

2

9510 FORMAT

1

9511 FORMAT

1

9512 FORMAT

1

9513 FORMAT

1

9514 FORMAT

1

9515 FORMAT

1

2

9516 FORMAT

1

2

9517 FORMAT

1

9518 FORMAT

1

9519 FORM AT

1

9520 FORMAT

1

9521 FORMAT

1

9522 FORMAT

1

2

9523 FORMAT

1

2

9524 FORMAT

1

(20A4)

(1HO,44HWARNING: DEFAULT VALUES ASSIGNED IN NAMELIST,A8)

(1HO,18HERROR IN NAMELIST ,A8,12H: DELT MUST ,

20HBE GREATER THAN ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBI3,12H: NSM, NFUEL,

37H AND NPILOT MUST BE GREATER THAN ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBI3,13H: NSM MUST BE,

24H LESS THAN IDIMI (IDIM1=,12,1H))

(1HO,18HERROR IN NAMELIST ,A8,5H: JOBI3,12H: NFUEL MUST,

27H BE LESS THAN IDIM6 (IDIM6=,I2,1H))

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBI3,13H: NPILOT MUST,

27H BE LESS THAN IDIM7 (IDIM7=,I2,1H))

(1HO,18HERROR IN NAMELIST ;A8,5H, JOBI3,11H: NCOM MUST,

27H BE LESS THAN IDIM4 (IDIM4=,I2,1H))

(1HO,18HERROR IN NAMELIST ,A8,5H, JOB,I3,12H: NNCOM MUST,

27H BE LESS THAN IDIM5 (IDIM5=,I2,1H))

(1HO,18HERROR IN NAMELIST ,A8,5H, JOB,13,7H, ENTRY,13,1H:,

52H NFCL, IORNT, IDIREC, AND IFTYP MUST BE GREATER THAN,

SH ZERO)

(IHO,18HERROR IN NAMELIST ,A8,SH, JOBJ3,7H: ENTRY,13,1H:,

37H NFCL MUST BE LESS THAN IDIM2 (IDIM2=,I2,1H))

(IHO,18HERROR IN NAMELIST ,A8,5H, JOBI3,7H, ENTRY,13,1H:,

26H IORNT MUST BE LESS THAN 3)

(iHO,18HERROR IN NAMELIST ,A8,51f, JOB,I3,7H, ENTRY,13,1H:,

27H IDIREC MUST BE LESS THAN 3)

(1H0,18HERROR IN NAMELIST A8,5H, JOB,I3,7H, ENTRY,13,lH:,

38H IFTYP MUST BE LESS THAN NFUEL (NFUEL=,12,lH))

(IHO,21HWARNING FOR NAMELIST ,A8,5H, JOBI3,7H, ENTRYI3,

16H: IORNT - IDIREC)

(1HO,18HERROR IN'NAMELIST ,A8S5H, JOB,I3,7H, ENTRY,13,lH:,

50H SLNG, SWID, SDEP, SMASS, AND SPOR MUST BE GREATER,

10H THAN ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBI3,10H, POSITION,I3,

54H: IPIL(I), JPIL(I), AND IPFUEL(I) MUST BE GREATER THAN,

SH ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBI3,10H, POSITION,I3,

37H: IPIL(I) MUST BE LESS THAN NSM (NSM=,I2,1H))

(1HO,18HERROR IN NAMELIST ,A8,5H, JOB,3,10H, POSITIONI3,

43H: JPIL(I) MUST BE LESS THAN NFC(IPIL(I)) (=,12,1H))

(1HO,18HERROR IN NAMELIST )A8,5H, JOBI3,10H, POSITIONI3,

43H: IPFUEL(I) MUST BE LESS THAN NFUEL (NFUEIL,I2,IH))

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBJ3,10H, POSITION,I3,

33H: PMASS MUST BE GREATER THAN ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOB,I3,1OH, POSITIONI3,

36H: IFUEL(I) MUST BE GREATER THAN ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOBI3,10H, POSITIONI3,

46H: DENS(I), SPHT(I),AND THK(I) MUST BE GREATER,

1OH THAN ZERO)

(lHO,18HERROR IN NAMELIST ,A8,5H, JOBI3,10H, POSITIONI3,

47H: HEAT(I), EFF(I),AND GAMMA(I) MUST BE GREATER,

32H THAN ZERO FOR COMBUSTIBLE FUELS)

(1HO,18HERROR IN NAMELIST A8,5H, JOBI3,10H, POSITIONI3,

48H: EFF(I) AND GAMMA(I) MUST BE LESS THAN OR EQUAL,

- 138 -
2

9525 FORMAT

1

9526 FORMAT

1

9527 FORMAT

1

9528 FORMAT

1

9529 FORMAT

1

9530 FORMAT

1

9000 STOP

END

31H TO UNITY FOR COMBUSTIBLE FUELS)

(1HO,-18HERROR IN NAMELIST ,A8,5H, JOBI3,13H:

33H BE GREATER THAN OR EQUAL TO ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOB,I3,10H,

37H: MOUTPT(I) MUST BE GREATER THAN ZERO)

(1HO,18HERROR IN NAMELIST ,A8,5H, JOB,I3,1OH,

30H: MOUTPT(I) MUST BE LESS THAN ,J2)

(IHO,18HERROR IN NAMELIST A8,5H, JOB,I3,13H:

29H BE LESS THAN OR EQUAL TO NSM)

(1H0,18HERROR IN NAMELIST ,A8,5H, JOBI3,10H,

37H: MSMOUT(I) MUST BE GREATER THAN ZERO)

(1H0,18HERROR IN NAMELIST ,A8,5H, JOBI3,10H,

45H: MSMOUT(I) MUST BE LESS THAN OR EQUAL TO

IOUTPT MUST,

POSITIONI3,

POSITIONI3,

NSMOUT MUST,

POSITION,I3,

POSITIONI3,

NSM)

- 139 -
C

C SUBROUTINE INCHK (READ CHECK FOR INPUT DATA) -

C *

SUBROUTINE INCHK (FX,FY,FZ,QEXT,DEP,FLNG,FLOSS,FMASSO,POR,WID,

1 BRATSO,BRATS1,BRATV,DENSDIFF,EFF,FABSRP,FIGTP,FIGTS,FTDAM,GAMMA,

2 HEAT,REFL,SPHT,THK,PMASS,IDIR,IORTITYP,NFC,IFUEL,IPIL,IPFUEL,

3 JPIL,IAD,NAD,LBF,LCF,LDF,LWF,IDIM1,IDIM2,IDIM4,IDIM5,NCOM,

4 NFUEL,NJOB,NNCOM,NPILOT,NSMNTIME,NWRITE)

IMPLICIT LOGICAL (L)

DIMENSION FX(IDIM1,IDIM2), FY(IDIMI,IDIM2), FZ(IDIMI,IDIMZ),

1 QEXT(IDIM1, IDIM2)

DIMENSION DEP(NSM), FLNG(NSM), FLOSS(NSM), FMASSO(NSM), POR(NSM),

1 WID(NSM), IDIR(NSM), IORT(NSM), ITYP(NSM), NFC(NSM)

DIMENSION BRATSO(NFUEL), BRATS1(NFUEL), BRATV(NFUEL), DENS(NFUEL),

1 DIFF(NFUEL), FABSRP(NFUEL), FIGTP(NFUEL), FIGTS(NFUEL),

2 GAMMA(NFUEL), HEAT(NFUEL), REFL(NFUEL), SPHT(NFUEL),

3 THK(NFUEL), IFUEL(NFUEL), FTDAM(NFUEL), EFF(NFUEL),

4 LBF(NFUEL), LCF(NFUEL), LDF(NFUEL), LWF(NFUEL)

DIMENSION PMASS(NPILOT),

1 IPIL(NPILOT), IPFUEL(NPILOT), JPIL(NPILOT)

DIMENSION IAD(IDIM4,4), NAD(IDIM5,4)

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

1 FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

2 RADCON, TG, VFV, WHEAT, ZD, ZN,

3 LSMALL

DATA X/1HX/, Y/1HY/, Z/1HZ/

WRITE (NWRITE,9000) TITLE, IJOB, NJOB

WRITE (NWRITE, 9100)

WRITE (NWRITE,9101) FCTR(1)

WRITE (NWRITE,9102) FCTR(2)

WRITE (NWRITE,9103) FCTR(3)

WRITE (NWRITE,9104) FCTR(4)

WRITE (NWRITE,9105) FCTR(5)

WRITE (NWRITE,9106) FCTR(6)

WRITE (NWRITE,9107) FCTR(7)

WRITE (NWRITE,9108) FCTR(8)

WRITE (NWRITE,9109) FCTR(9)

WRITE (NWRITE,9110) FCTR(10)

WRITE (NWRITE,9111) FCTR(11)

WRITE (NWRITE,9112) FCTR(12)

WRITE (NWRITE,9113) FCTR(13)

WRITE (NWRITE,9114) FCTR(14)

WRITE (NWRITE,9115) FCTR(15)

IF (INCHCK.EQ.0) RETURN

WRITE (NWRITE,9200) NFUEL

DO 6000 I=1,NFUEL

WRITE (6,9210) I

IF (LDF(I)) GO TO 1000

- 140 -
IF (LWF(I)) GO TO 2000

IF (LBF(I)) GO TO 3000

IF (LCF(I)) GO TO 4000

WRITE (NWRITE,9220) IFUEL(I)

WRITE (NWRITE,9230) DENS(I)

WRITE (NWRITE,9240) SPHT(I)

WRITE (NWRITE,9250) THK(I)

WRITE (NWRITE,9255) HEAT(I)

WRITE (NWRITE,9258) EFF(I)

WRITE (NWRITE,9260) FIGTP(I)

WRITE (NWRITE,9270) FIGTS(I)

WRITE (NWRITE,9275) FTDAM(I)

WRITE (NWRITE,9280) BRATV(I)

WRITE (NWRITE,9290) BRATSO(I)

WRITE (NWRITE,9300) BRATS1(I)

WRITE (NWRITE,9310) GAMMA(I)

WRITE (NWRITE,9320) FABSRP(I)

WRITE (NWRITE,9330) REFL(I)

GO TO 6000

1000 WRITE (NWRITE,9340) IFUEL(I)

GO TO 6000

2000 WRITE (NWRITE,9350) IFUEL(I)

GO TO 5000

3000 WRITE (NWRITE,9360) IFUEL(I)

GO TO 5000

4000 WRITE (NWRITE,9370) IFUEL(I)

5000 WRITE (NWRITE,9250) THK(I)

WRITE (NWRITE,9400) DIFF(I)

WRITE (NWRITE,9330) REFL(I)

6000 CONTINUE

IF (INCHCK.EQ.1) RETURN

IF (.NOT.LROOM) GO TO 7000

WRITE (IWRITE, 9500)

WRITE (NWRITE,9501) FLNG(ICEIL), WID(ICEIL), FZ(ICEIL,I)

WRITE (NWRITE,9510) DHGT, DWID, DCFIN, DCFOUT

WRITE (NWRITE,9520) VFV

WRITE (NWRITE,9525) FH, FC

WRITE (NWRITE,9530) PLCF

WRITE (NWRITE,9540) GABSRP

WRITE (NWRITE,9570) HCEIL

IF (INITG.EQ.0) GO TO 7000

WRITE (NWRITE,9580) TG, DG

WRITE (NWRITE,9585)

DO 6900 I=1,NSM

NFCI = NFC(I)

WRITE (NWRITE,9590) (QEXT(IJ),Jf1,NFCI)

6900 CONTINUE

7000 WRITE (NWRITE,9600) NPILOT

DO 7500 I=1,NPILOT

WRITE (NWRITE,9605) I

WRITE (NWRITE,9610) IPIL(I), JPIL(I)

WRITE (NWRITE,9620) IPFUEL(I)

WRITE (NWRITE,9630) PMASS(I)

7500 CONTINUE

- 141 -
WRITE (NWRITE,9700) NSM

DO 8000 I=1,NSM

WRITE (NWRITE,9705) I

WRITE (NWRITE,9710) FX(I,I), FY(I,1), F

WRITE (NWRITE,9720) FLNG(I), WID(I), DEJ

WRITE (NWRITE,9730) NFC(I)

IF (IDIR(I).EQ.1) DIREC = X

IF (IDIR(I).EQ.2) DIREC = Y

IF (IDIR(I).EQ.3) DIREC = Z

IF (IORT(I).EQ.1) ORNT = X

IF (IORT(I).EQ.2) ORNT = Y

IF (IORT(I).EQ.3) ORNT = Z

WRITE (NWRITE,9740) DIREC, ORNT

WRITE (NWRITE,9750) FMASSO(I)

WRITE (NWRITE,9760) POR(I)

WRITE (NWRITE,9770) FLOSS(I)

WRITE (NWRITE,9780) ITYP(I)

8000 CONTINUE

IF ((NCOM.NE.0).OR.(NNCOM.NE.0)) WRITE

IF (NCOM.EQ.0) GO TO 8500

WRITE (NWRITE,9800) NCOM

DO 8200 1=1,NCOM

WRITE (NWRITE,9810) I, (IAD(I,J),J=1,4)

8200 CONTINUE

8500 IF (NNCOM.EQ.0) GO TO 8900

WRITE (NWRITE,9820) NNCOM

DO 8800 I=1,NNCOM

WRITE (NWRITE,9810) I, (NAD(I,J),J=1,4)

8800 CONTINUE

8900 WRITE (NWRITE,9900)

WRITE (NWRITE,99 10) RTEMP

WRITE (NWRITE,9915) CALTEM

WRITE (NWRITE,9920) FLCF

WRITE (NWRITE,9925) HROOM

WRITE (NWRITE,9930) DELT

WRITE (NWRITE,9940) NTIME

~(I,1)

~(I)

(NWRITE,9790)

C

C FORMAT STATEMENTS

C

9000 FORMAT (IHI,45HPROGRAM COMPBRN III - A DETERMINISTIC CODE TO,

1 29H COMPUTE THE PROGRESS OF FIRE,/,23X,17HOVER A GIVEN FUEL,

2 35H ARRAY WITHIN ENCLOSING BOUNDARIES.,/,23X,

3 32HALL UNITS ARE IN THE MKS SYSTEM.,///,1X,2OA4,///////,

4 12H INPUT DATA:,///,4H JOB,13,3H OF,I3,5H JOBS)

9100 FORMAT (1H1,36HVARIABILITY FACTORS FOR FIRE MODELS:)

9101 FORMAT (IHO,SX,35HVENTILATION CONTROLLED BURNING RATE,T83,E13.6)

9102 FORMAT (IHO,SX,36HFUEL-SURFACE CONTROLLED BURNING RATE,T83,E13.6)

9103 FORMAT (1H0,5X,32HFLAME HEIGHT FOR HORIZONTAL FUEL,T83,E13.6)

9104 FORMAT (1H0,5X,30HFLAME HEIGHT FOR VERTICAL FUEL,T83,E13.6)

9105 FORMAT (1H0,SX,31HRADIATIVE HEAT FLUX INTERCHANGE,T83,E13.6)

9106 FORMAT (IH0,5X,25HBUOYANT PLUME TEMPERATURE,T83,E13.6)

9107 FORMAT (IHO,SX,41HCONVECTIVE HEAT TRANSFER COEFFICIENT FOR

1 25HVERTICAL OBJECTS IN PLUME,T83,E13.6)

9108 FORMAT (1H0,5X,41HCONVECTIVE HEAT TRANSFER COEFFICIENT FOR

- 142 -
1

9109 FORMAT

9110 FORMAT

1

9111

9112

9113

FORMAT

FORMAT

FORMAT

1

9114

9115

9200

9210

9220

9230

9240

9250

9255

9258

9260

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

1

9270 FORMAT

1

9275 FORMAT

1

9280 FORMAT

1

9290 FORMAT

1

9300 FORMAT

1

9310 FORMAT

1

9320 FORMAT

9330 FORMAT

9340 FORMAT

9350 FORMAT

9360 FORMAT

9370 FORMAT

9400 FORMAT

1

9500 FORMAT

9501 FORMAT

9510 FORMAT

1

2

3

9520 FORMAT

9525 FORMAT

1

9530 FORMAT

1

9540 FORMAT

1

9570 FORMAT

27HHORIZONTAL OBJECTS IN PLUME,T83,E13.6)

(IH0,5X,27HGAS LAYER LOCAL TEMPERATURE,T83,E13.6)

(1H0,5X,39HHEAT TRANSFER TO SELF FOR VERTICAL FUEL,

T83,E13.6)

(1HO,5X,30HHEAT TRANSFER TO ADJACENT FUEL,T83,E13.6)

(1HO,5X,36HHEAT FLUX FROM CEILING HOT GAS LAYER,T83,E13.6)

(1HO,5X,36HHEAT FLUX FROM REFLECTIONS OFF WALLS,

13H AND BARRIERST83,El3.6)

(1H0,5X,21HMASS BURNOUT FRACTION,T83,E13.6)

(1H0,5X,19HCURRENTLY UNDEFINED,T83,E13.6)

(1H1,5X,21HNUMBER OF FUEL TYPES:,I5)

(1HO,5X,18HDATA FOR FUEL TYPE,13,1H:)

(1HO,10X,10HFUEL TYPE:,T91,I5)

(1HO01OX,18HDENSITY (KG/M**3):,T83,E13.6)

(1H ,10X,23HSPECIFIC HEAT (J/KG-K):,T83,E13.6)

(1H 10X,29HTHERMAL CONDUCTIVITY (W/M-K):,T83,E13.6)

(1H 10X,26HHEAT OF COMBUSTION (J/KG):,T83,E13.6)

(1H 10X,22HCOMBUSTION EFFICIENCY:,T83,E13.6)

(1H 10X,38HPILOTED IGNITION TEMPERATURE (DEG. K):,

T83,E13.6)

(1K ,10X,42HSPONTANEOUS IGNITION TEMPERATURE (DEG. K):,

T83,E13.6)

(1H ,10X,28HDAMAGE TEMPERATURE (DEG. K):,

T83,E13.6)

(1H ,10X,42HVENTILATION CONTROLLED BURNING RATE FACTOR,

15H (KG/M**2.5-S):,T83,E13.6)

(1H ,10X,41HSURFACE CONTROLLED SPECIFIC BURNING RATE ,

12H(KG/M**2°S):,T83,E13.6)

(1H ,10X,44HSPECIFIC BURNING RATE RADIATION AUGMENTATION,

13H (KG/J-M**2):,T8',E13.6)

(1H ,10X,39HFRACTION OF HEATtPELEASED AS RADIATION:,

T83,E13.6)

(1H 10X,33HSMOKE ATTENUATION.FACTOR (M**-l):,T83,E13.6)

(1H 10X,13HREFLECTIVITY:,T83,E13.6)

(IHOIOX,21HFUEL TYPE: (DETECTOR),T91,15)

(1HO,1OX,17HFUEL TYPE: (WALL),T91,I5)

(1HO,10X,20HFUEL TYPE: (BARRIER),T91,IS)

(1HO,10X,20HFUEL TYPE: (CEILING),T91,IS)

(1H 10X,29HTHERMAL DIFFUSIVITY (M**2/S):,T83,

E13.6)

(1H1,5X,16HROOM PARAMETERS:)

(1HO,10X,34HCEILING LENGTH, WIDTH, HEIGHT (M):,T57,3E13.6)

(1H ,10X,16HDOOR HEIGHT (M):,T83,E13.6,

/,11X,15HDOOR WIDTH (M):,T83,E13.6,

/,11X,27HDOORWAY INFLOW COEFFICIENT:,T83,E13.6,

/,11X,28HDOORWAY OUTFLOW COEFFICIENT:,T83,E13.6)

(1H ,10X,28HFORCED VENTILATION (M**3/S):,T83,E13.6)

(1 ,10X41HFORCED 0X VENTILATION CONSTANTS (FH AND FC):,

T70,2E13.6)

(1H ,10X,34HPLUME ENTRAINMENT CONSTANTS (PLCF), T83,E13.6)

(1H ,10X,37HGAS ABSORPTION COEFFICIENT (GABSRP):,

T83,E13.6)

(iH ,10X,34HCEILING HEAT TRANSFER COEFFICIENT

- 143 -
1

9580 FORMAT

1

9585

9590

9600

9605

9610

9620

9630

9700

9705

9710

2

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

1

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

1

9720 FORMAT

1

9730

9740

9770

9750

9760

9780

9790

9800

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

15H(W/M-T*2 DEG.K):,T83,E13.6)

(1HO,//,6X,37HINITIAL CEILING GAS LAYER PARAMETERS:,//,

11X,24HAVERAGE GAS TEMPERATURE:,T83,E13.6,/,

11X,16HGAS LAYER DEPTH:,T83,E13.6)

(IH1,32HINITIAL HEAT FLUXES TO FUEL BED:,//)

(11 ,7HMODULE:,I3,(/,1X,10E12.4))

(IHI,16HPILOT FIRE DATA:,/,6X,22HNUMBER OF PILOT FIRES:,I5)

(1HO,5X,19HDATA FOR PILOT FIRE,I3,1H:)

(1HO,1OX,45HLOCATION OF PILOT FIRE (FUEL ARRAYFUEL CELL),

1H:,T89,I3,1H,,I3)

(1H ,10X,1OHFUEL TYPE:,T91,I5)

(11 ,1OX,10HMASS (KG):,T83,E13.6)

(IHI,5X,22HNUHBER OF FUEL ARRAYS:,I5)

(1HO,5X,19HDATA FOR FUEL ARRAY,13,1H:)

(1HO,10X,40HINITIAL FUEL CELL X-Y-Z COORDINATES (M):,

T57,3EI3.6)

(11 ,10X,36HDIMENSIONS (LENGTH,WIDTH,DEPTH) (M):,

T57,3E13.6)

(IH ,10X,21HNUMBER OF FUEL CELLS:,T91,IS)

(I ,10X,31HDIRECTION OF AXIS, ORIENTATION:,T86,A1,8X,A1)

(111 ,1OX,29HHEAT LOSS FACTOR (UNDEFINED):,T83,E13.6)

(1 ,IOX,10HHASS (KG):,T83,E13.6)

(1N ,10X,32HPOROSITY FACTOR (DIMENSIONLESS):,T83,E13.6)

(1N ,IOXIOHFUEL TYPE:,T91,15)

(1H1,5X,19HCOMMUNICATION DATA:,/)

(1H0,5X,46HNUMBER OF ADJACENT FUEL CELLS NOT IN SAME FUEL,

7H ARRAY:,I5,//,14X,14HFUEL CELL PAIR,3X,

471{(FUEL ARRAyFUEL CELL) , (FUEL ARRAYFUEL CELL),/)

(11 ,19X,13,12X,I3,8X,13,11X,l3,8X,I3)

(1HO,//,6X,23HNON-COMMUNICATION DATA:,/,liX, 1OHNUMBER OF

29HNON-COMMUNICATING FUEL CELLS:,I5,//,

14X,14HFUEL CELL PAIR,3X,

47H(FUEL ARRAY,FUEL CELL) , (FUEL ARRAY,FUEL CELL),/)

(111,6X,14HMISCELLANEOUS:)

(1H.,1OX,26HROO TEMPERATURE (DEG. K):,T83,E13.6)

(1H ,10X,33HCALORIMETER TEMPERATURE (DEG. K):,T83,E13.6)

(1H ,lOX,46HCONVECTIVE HEAT TRANSFER COEFFICIENT FOR FLAME,

12H (W/M**2-K):,T83,E13-.6)

(1 ,10X,45HCONVECTIVE HEAT TRANSFER COEFFICIENT FOR ROOM, 12H (W/M**2-K):,T83,E13.6,/,11X,

38H(FOR OBJECTS OUTSIDE OF HOT GAS LAYER))

(I ,10X,19HTIME INCREMENT (S):,T83,E13.6)

(1H ,10X,29HNUHBER OF TIME STEPS FOR JOB:,T91,I5)

2

3

9810 FORMAT

9820 FORMAT

1

2

3

9900

9910

9915

9920

FORMAT

FORMAT

FORMAT

FORMAT

1

9925 FORMAT

1

2

9930 FORMAT

9940 FORMAT

RETURN

END

- 144 -
C

C SUBROUTINE INIT (INITIALIZATION OF PROBLEM PARAMETERS)

C

1

2

3

1

2

3

1

2

2

21

2

3

1

2

3

SUBROUTINE INIT(FX,FYFZ,HCOEF,QEXTTSURRTEMP,LBURN,LDAMGE,

LFMASS, AREA, DELS, POR,WID, BRATSO, BRATS 1, BRATV, EFF, HEAT, PBRATV,

PBRTSO,PBRTS1,PEFF,PHEATPMASS,IDIR,IORT,NFC,IPIL,IPFUEL,JPIL,

I LPMASS,ICOMMLB,LC,LW,IDIM1,IDIM2,IDIM3,NFUELNPILOT,NSM)

IMPLICIT LOGICAL (L)

DIMENSION FX(IDIM1,IDIM2), FY(IDIM1,IDIM2), FZ(IDIM1,IDIM2),

HCOEF(IDIM1, IDIM2), QEXT(IDIM1, IDIM2).

TSURR(IDIM1,IDIM2), TEMP(IDIM1,IDIM2,10),

LBURN(IDIMIIDIM2), LDAMGE(IDIM1,IDIM2), LFMASS(IDIM1,IDIM2)

DIMENSION AREA(NSM), DELS(NSM), POR(NSM), WIDCNSM),

IDIR(NSM), IORT(NSM), NFC(NSM),

LB(NSM), LC(NSM), LW(NSM)

DIMENSION BRATSO(NFUEL), BRATS1(NFUEL), BRATV(NFUEL), EFF(NFUEL),

HEAT (NFUEL)

DIMENSION PBRATV(NPILOT), PBRTSO(NPILOT), PBRTS1(NPILOT),

PEFF(NPILOT), PMASS(NPILOT), PHEAT(NPILOT),

IPIL(NPILOT), IPFUEL(NPILOT), JPIL(NPILOT),

LPIHASS (NPILOT)

DIMENSION ICOMM(IDIM3, IDIM3)

COMMON /ALL/ ACEIL, AWALL, CALTEM; DELT, FCTR(15), FLCF, HROOM,

RTEMP, TIME, TITLE(20),

ICEIL, IJOB, INCHCK, INITG. IOUTPT, MOUTPT(17),

LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

RADCON, TG, VFV, WHEAT, ZD, ZN,

LSHALL

COMMON /VEh•C/

1

2

3

4

AFUEL, AFUELO, CVA, CVAO, QMAX,

QTOT, QTOTO, QTOT1, QTOT2, TMDOT, TMDOTO,

ThDOTS, TQDOT, TQDOTC, WIN,. ZOA,

NBURN, NBURNO,

LDECAY, IFLUX1, LFLUX2, LVENT, LVCONT

C

C COMPUTE SHAPE FACTORS FROM WALLS, BARRIERS, AND CEILING TO OBJECTS

C

IJ = 0

DO 1900 I=1,NSM

NFCI = NFC(1)

IF (LW(I).OR.LB(I).OR.LC(1)) GO TO 1100

IJ = IJ + NFCI

GO TO 1900

1100 DO 1700 J=1,NFCI

IJ = IJ + 1

KM = 0

DO 1500 K=I,NSM

NFCK = NFC(K)

DO 1300 N=1,NFCK

KM = KM + 1

IF (I.EQ.K) ICOMM(IJ,KM) = 0

- 145 -
IF (ICOMM(IJKM).EQ.0) GO TO 1300

F12 = SHAPE(IORT(I),IORT(K),IDIR(I),FX(I,J),FY(I,J),

1 FZ(I,J),FX(K,M),FY(K,M),FZ(K,M),DELS(I),WID(I))

ICOMM(IJ,KM) = IFIX(F12*1000.)

1300 CONTINUE

1500 CONTINUE

1700 CONTINUE

1900 CONTINUE

IF (.NOT.LROOM) GO TO 3000

ZD =0

IF ((INITG.EQ.1).AND.(ZD.GT.0.)) GO TO 2500

TG = RTEMP

ZD = 0.2*DHGT

ZN = 2.*ZD

C

C OLD VERSION:

C2500 IF (TG.EQ.0.) TG = 300.

C NEW VERSION:

2500 IF (TG.LT.RTEMP) TG = RTEMP

CVA = 0.

QTOT = 0.

QTOTO = 0.

QTOTI = 0.

QTOT2 = 0.

AWALL = 2.*FZ(ICEIL,1)*(DELS(ICEIL) + WID(ICEIL))

ACEIL = AREA(ICEIL)

C MAXIMUM HEAT RELEASED FOR A CLOSED ROOM

QMAX = 4.21E6*FZ(ICEIL,1)*ACEIL

LVENT = .FALSE.

LVCONT = .FALSE.

LDECAY = .FALSE.

LFLUX1 = .FALSE.

3000 TMDOT = 0.

TMDOTS 0.

DO 3700 I=1,NSM

NFCI = NFC(I)

DO 3500 J=1,NFCI

LDAMGE(I,J) .FALSE.

LBURN(I,J) = .FALSE.

LFMASS(I,J) = .FALSE.

TSURR(IJ) = RTEMP

HCOEF(I,J) = HROOM

IF (LROOM.AND. (INITG.EQ. 1)) GO TO 3200

QEXT(I,J) = 0.

3200 DO 3300 K=1,10

TEMP(IJ,K) = RTEMP

3300 CONTINUE

3500 CONTINUE

3700 CONTINUE

LEND = .FALSE.

AFUEL = 0.

NBURN - 0

c

C INITIALIZE PILOT FIRES

- 146 -
C

DO 4000 I=I,NPILOT

NBURN = NBURN + 1

AFUEL = AFUEL + POR(IPIL(I))*AREA(IPIL(I))

LBURN(IPIL(I),JPIL(I)) = .TRUE.

IPTYP = IPFUEL(I)

PBRATV(I) = BRATV(IPTYP)

PBRTSO(I) = BRATSO(IPTYP)

PBRTS1(I) = BRATS1(IPTYP)

PHEAT(I) = HEAT(IPTYP)

PEFF(I) = EFF(IPTYP)

LPMASS(I) = .TRUE.

4000 CONTINUE

RETURN

END

- 147 -
C

C SUBROUTINE TINIT (PERFORMS TIME STEP INITIALIZATIONS)

C

SUBROUTINE TINIT(FLHT,FLTEMP,HCOEF,HCOEFO,Q,IQDOT2P,QEXT,

1 QEXTO,TSURR,TSURRO,LPIGN,LPLUME,LSTRTONFC,IDIM1,IDIM2,NSM)

IMPLICIT LOGICAL (L)

DIMENSION FLHT(IDIM1,IDIM2), FLTEMP(IDIM1,IDIM2),

1 HCOEF(IDIM1,IDIM2), HCOEFO(IDIM1,IDIM2), Q(IDIM1,IDIM2),

2 QDOT2P(IDIM1,IDIM2), QEXT(IDIM1,IDIM2), QEXTO(IDIMI,IDIM2),

3 TSURR(IDIM1,IDIM2), TSURRO(IDIM1,IDIM2),

4 LPIGN(IDIMI1,IDIM2), LPLUME(IDIM1,IDIM2), LSTRTO(IDIM1,IDIM2)

DIMENSION NFC(NSM)

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

1 FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

2 RADCON, TG, VFV, WHEAT, ZD, ZN,

3 LSMALL

COMMON /VENTC/ AFUEL, AFUELO, CVA, CVAO, QMAX,

1 QTOT, QTOT0, QTOT1, QTOT2, TMDOT, TMDOT0,

2 TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

3 NBURN, NBURNO,

4 LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

IF (.NOT.LROOM) GO TO 1000

CVAO = CVA*FCTR(I)

CVA = 0.

C FWTA AND FUELA ARE NO LONGER NEEDED

C FHTA = 0.

C FUELA = 0.

ZOA = 0.

LFLUX2 = LFLUX1

LFLUX1 = .FALSE.

LSMALL=. FALSE.

1000 AFUELO = AFUEL

AFUEL = 0.

TMDOTO = TMDOT

TMDOT = 0.

TMDOTS = 0.

TQDOT = 0.

TQDOTC = 0.

NBURNO = NBURN

NBURN = 0

DO 2500 I=1,NSM

NFCI = NFC(I)

DO 2000 J=I,NFCI

QEXTO(IJ) = QEXT(I,J)

QEXT(I,J) = 0.

LPIGN(I,J) = .FALSE.

- 148 -
LSTRTO(I,J) = .FALSE.

FLTEMP(I,J) = 0.

FLHT(I,J) = 0.

QDOT2P(IJ) = 0.

Q(IJ) = 0.

TSURRO(I,J) = TSURR(I,J)

HCOEFO(IJ) = HCOEF(IJ)

TSURR(I,J) = RTEMP

LPLUHE(I,J) = .FALSE.

C

C NOTE USE OF CONSTANT CONVECTIVE HEAT TRANSFER COEFFICIENT

C (UNLESS OBJECT IS IN THE FLAME, PLUME OR HOT GAS LAYER)

c

HCOEF(I,J) = HROOM

2000 CONTINUE

2500 CONTINUE

RETURN

END

- 149 -
C •%-AA A,'• A A ; A . A••AA; A A~.;; ;. .. ** .; **,*** .A;,; A . ,• ;..;* ,'** ;** -* *' * *;, ; , .' , ,¥- ;; ; ,',' .AC *

C SUBROUTINE SOURCE (COMPUTES HEAT FLUX SOURCE STRENGTH OF FUEL *

C ELEMENTS, WALLS, BARRIERS, AND CEILING/GAS *

C LAYER) *

C *

SUBROUTINE SOURCE (BRAT,FLHT,FLTEMP,FMASS,FZ,GAMN,Q,QDOTC,

1 QDOT2P,QEXT,QEXTO,TEMP,AREA,DELS,DEP,FMASSO,POR,RAD,WID,PBRATV,

2 PBRTSO,PBRTS1,PEFF,PHEAT,PMASS,PMDOTS,BRATSO,BRATS1,BRATV,DIFF,

3 EFF,GAMMA,HEATREFL,THK,ICOUNT,IORT,ITYP,NFC,IPIL,IPFUEL,JPIL,

4 LBURN,LFMASS,LSTRTO,LTOP,LB,LC,LD,LW,LPMASS,LDAMGE,IDIM1,IDIM2,

5 NFUEL, NPILOT, NSM, NWRITE)

IMPLICIT LOGICAL (L)

DIMENSION BRAT(IDIM1,IDIM2), FLHT(IDIM1,IDIM2),

1 FLTEMP(IDIMI,IDIM2), FMASS(IDIM1,IDIM2), FZ(IDIM1,IDIM2),

2 GAMN(IDIM1,IDIM2), Q(IDIM1,IDIM2), QDOTC(IDIM1,IDIM2),

3 QDOT2P(IDIM1,IDIM2), QEXT(IDIM1,IDIM2), QEXTO(IDIM1,IDIM2),

4 TEMP(IDIM1,IDIM2,10),

5 ICOUNT(IDIM1,IDIM2), LBURN(IDIM1,IDIM2) ,LDAMGE(IDIM1,IDIM2),

6 LFMASS(IDIM1,IDIM2), LSTRTO(IDIM1,IDIM2), LTOP(IDIM1,IDIM2)

DIMENSION AREA(NSM), DELS(NSM), DEP(NSM), FMASSO(NSM), POR(NSM),

1 RAD(NSM), WID(NSM),

2 IORT(NSM), ITYP(NSM), NFC(NSM),

3 LB(NSM), LC(NSM), LD(NSM), LW(NSM)

DIMENSION PBRATV(NPILOT), PBRTSO(NPILOT), PBRTS1(NPILOT),

1 PEFF(NPILOT), PHEAT(NPILOT), PMASS(NPILOT), PMDOTS(NPILOT),

2 IPIL(NPILOT), IPFUEL(NPILOT), JPIL(NPILOT), LPMASS(NPILOT)

DIMENSION BRATSO(NFUEL), BRATS1(NFUEL), BRATV(NFUEL), DIFF(NFUEL),

1 EFF(NFUEL), GAMMA(NFUEL), HEAT(NFUEL), REFL(NFUEL),

2 THK(NFUEL)

COMMON /ALL/

1

2

3

COMMON /GAS/

1

2

3

COMMON /VENTC

1

2

3

4

ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

RTEMP, TIME, TITLE(20),

ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

LEND, LROOM

CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

RADCON, TG, VFV, WHEAT, ZD, ZN,

LSMALL

* I

'I AFUEL, AFUELO, CVA, CVAO, QMAX,

QTOT, QTOTO, QTOT1, QTOT2, TMDOT, TMDOTO,

TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

NBURN, NBURNO,

LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

C

C

C

C

PILOT FIRE BURNING RATE

DO 1900 I=1,NPILOT

IF (.NOT.LPMASS(I)) GO TO 1900

IPILOT = IPIL(I)

JPILOT = JPIL(I)

PAREA = AREA(IPILOT)

IF (PMASS(I).GT.0.0) GO TO 1500

- 150 -
C PILOT FIRE BURNOUT

C

PAREA*= 0.0

PMASS(I) = 0.0

LPMASS(I) .FALSE.

1500 PMDOTS() = (PBRTSO(I) + PBRTS1(I)*QEXTO(IPILOTJPIIOT))*

1 PAREA*POR(IPILOT)*FCTR(2)

LSTRTO(IPILOTJPILOT) = (LPMASS(I))

1900 CONTINUE

DO 8000 1=1,NSM

C

C PERFORM THE FOLLOWING SOURCE CALCULATIONS ONLY FOR COMBUSTIBLE

C FUELS

C

IF (LD(I).OR.LW(I).OR.LB(I).OR.LC(I)) GO TO 8000

C ASSIGNMENT OF BURNOUT MASS FOR EACH FUEL CELL

FRMASS = .3*FKASSO(I)*FCTR(14)

ITYPE ITYP(I)

NFCI NFC(I)

LORNT (IORT(I).NE.3)

DO 4000 J=I,NFCI

IF (.NOT.LBURN(I,J)) GO TO 4000

NBURN = NBURN + 1

LSTRT - LSTRTOCI,J)

IF (.NOT.LSTRT) GO TO 2500

DO 2000 II=I,NPILOT

IF ((I.NE.IPIL(II)).OR.(J.NE.JPIL(II))) GO TO 2000

INDEX = II

GO TO 2500

2000 CONTINUE

C

C

C BURNING RATES (VENTILATION AND FUEL SURFACE CONTROLLED)

C

C

2500 AFUEL = AFUEL + AREA(I)*POR(I)

C

C SURFACE-CONTROLLED BURNING PER UNIT AREA: ASSUMES LINEAR

C DEPENDENCE ON HEAT FLUX

C

FNDOTS = (BRATSO(ITYPE) + BRATS1(ITYPE)*QEXTO(I,J))*

1 AREA(I)*POR(I)*FCTR(2)

IF (LSTRT) FMDOTS = PMDOTS(INDEX)

IF (FMDOTS.GT.O.) GO TO 2700

C

C STOP BURNING IF BURNING RATE IS NEGATIVE (FOR THRESHOLD FUELS)

C

BRAT(I,J) = 0.

LBURN(I,J) .FALSE.

GO TO 4000

2700 FMDOT = FMDOTS

IF (.NOT.LROOM) GO TO 2900

C

C VENTILATION CONTROLLED BURNING: ASSUMES A LINEAR DEPENDENCE

- 151 -
C ON SURFACE AREA, INPUT AIRFLOW. EMPLOYS AN AVERAGE BURNING

C RATE CONSTANT (AVERAGED OVER TOTAL BURNING AREA)

C

FBV = BRATV(ITYPE)

IF (LSTRT) FBV = PBRATV(INDEX)

CVA = CVA + FBV*AREA(I)*POR(I)

IF (LVENT) FMDOT = WIN*AREA(I)*POR(I)*CVAO*FCTR(1)/AFUELO**2

2900 THDOT = TMDOT + FMDOT

TMDOTS = TMDOTS + FMDOTS

BRAT(I,J) = FMDOT

C

C HEAT PRODUCTION RATE

C

QCOMB = EFF(ITYPE) * HEAT(ITYPE)

IF (LSTRT) QCOMB = PEFF(INDEX) * PHEAT(INDEX)

Q(I,J) = FMDOT*QCOMB

TQDOT = TQDOT + Q(I,J)

GAMN(I,J) = 1. - GAMMA(ITYPE)

IF (LSTRT) GAMN(I,J) = 1. - GAMMA(IPFUEL(INDEX))

C

C DECREMENT FUEL MASS,STOP BURNING ON FUEL CELL IF BURNOUT OCCURS

C

IF (LSTRT) GO TO 3000

XMASS - FMASS(IJ) - FMDOT*DELT

IF (XMASS.GT.FRMASS) GO TO 3500

LBURN(IJ) .FALSE.

LFMASS(IJ) - .TRUE.

FMASS(I,J) = FRMASS

GO TO 4000

C

C DECREMENT PILOT MASS

C

3000 PMASS(INDEX) = PMASS(INDEX) - FMDOT*DELT

GO TO 4000

3500 FMASS(I,J) = XMASS

4000 CONTINUE

C

C FLAME HEIGHTS

C

VMDOT = 0.0

KCOUNT = 0

DO 5900 J=1,NFCI

IF (.NOT.LBURN(I,J)) GO TO 5900

F•IDOT = BRAT(IJ)

IF (LORNT) GO TO 5100

C

C FLAMES OVER HORIZONTAL FUEL SLABS

C

FHT = (30.64*RAD(I)*(BRAT(I,J)/(AREA(I)*SQRT(RAD(I)) )))**.61)

1 *FCTR(3)

C

C SUMS NEEDED IN WEIGHTED AVERAGES FOR FUEL BASE HEIGHT

C (FOR PLUME FLOW MODEL) AND FLAME HEIGHT. POSITION OF

C STATEMENTS RE-ARRANGED FOR HORIZONTAL FIRES.

- 152 -
C

C OLD VERSION:

C

C IF (LROOM) ZOA = ZOA + FZ(I,J)*FMDOT

C

C NEW VERSION:

C

IF (.NOT.LROOM) GO TO 5700

ZOA- ZOA + FZ(I,J)*FMDOT

C FHTA IS NO LONGER NEEDED

C FHTA = FHTA+ FHT*FHDOT

GO TO 5700

C FLAMES OVER VERTICAL FUEL SLABS

C

5100 VMDOT = VMDOT + FMDOT

KCOUNT = KCOUNT + 1

IF (J.EQ.NFCI) GO TO 5200

IF (LBURN(IJ+1)) GO TO 5500

5200 FHT = (29.7*(VMDOT/WID(I))**.6667)*FCTR(4) + DELS(I)

C

C AVERAGE FUEL ABASE ELEVATION (FOR VERTICAL FIRES) IS BASED

C ON LOWEST BURNING CELL (PER FIRE). NEW VERSION CORRECTS

C AVERAGING PROCEDURE FOR ZOA (GIVEN LATER).

C THE BURNING RATE FOR THE ENTIRE FIRE NOW WEIGHTS THE FLAME

C HEIGHT AND BASE ELEVATION; THE PREVIOUS VERSION USED ONLY

C THE BURNING RATE FROM THE TOP ELEMENT FOR ZOA, AND WEIGHTED

C THE FLAME HEIGHT FROM EACH FUEL CELL IN THE VERTICAL FIRE

C SEPARATELY.

C

C OLD VERSION:

C

C IF CLROOM) ZOA = ZOA + FZ(I,J-KCOUNT+I)*FMDOT

C NEW VERSION:

C

IF C.NOT.LROOM) GO TO 5300

ZOA = ZOA + FZ(I,J-KCOUNT+1)*VMDOT

C%%%%%%%% %%% %%

C FHTA IS NO LONGER NEEDED

C FHTA = FHTA + (FHT + (KCOUNT-1)*DELS(I))*VMDOT

5300 VMDOT 0.0

KCOUNT 0

LTOP(I,J) = .TRUE.

GO TO 5700

5500 FliT = DELS(I)

LTOP(I,J) = .FALSE.

5700 FLHT(I,J) = FliT

C

C SEE ABOVE NOTES

C

C OLD VERSION:

- 153 -
C IF (.NOT.LROOM) GO TO 5900

C FUELA = FUELA + AREA(I)

C FHTA = FHTA + FHT*FIMDOT

C

C NEW VERSION: FHTA AND FUELA ARE NO LONGER NEEDED

C

C IF (LROOM) FUELA = FUELA + AREA(I)

C

5900 CONTINUE

C

C

C SOURCE STRENGTH OF FLAMES (HEAT FLUX, TEMPERATURE)

C

C

IF (LORNT) GO TO 7000

C

C HORIZONTAL FUEL SLABS

C

DO 6000 J=1,NFCI

IF (.NOT.LBURN(I,J)) GO TO 6000

HTFLUX = Q(I,J)/(3.14159*RAD(I)*(RAD(I) + 2.*FLHT(I,J)))

QDOT2P(I,J) = HTFLUX

FLTEMP(I,J) = SQRT(SQRT(HTFLUX/5.6697E-8))

QDOTC(IJ) = GAMN(IJ)*Q(I,J)

TQDOTC = TQDOTC + QDOTC(IJ)

6000 CONTINUE

GO TO 8000

C

C VERTICAL FUEL SLABS (ALLOWS FOR MULTIPLE FIRES ON A SUPER MODULE

C

7000 IBOTP = I

C INDEX BURNING CELLS IN A SINGLE FLAME, STARTING WITH THE LOWEST

7100 JCOUNT = 0

LBOT = .FALSE.

IBOT = IBOTP

DO 7300 J=IBOT,NFCI

IF (.NOT.LBURN(I,J)) GO TO 7300

IF (.NOT.LBOT) IBOTP = J

LBOT .TRUE.

JCOUNT = JCOUNT + 1

ICOUNT(I,J) = JCOUNT

IF (LTOP(I,J)) GO TO 7500

7300 CONTINUE

GO TO 8000

7500 ITOP = IBOTP + JCOUNT - 1

TFLHT = 0.0

VQDOT = 0.0

C

C DETERMINE TOTAL FLAME HEIGHT, HEAT PRODUCTION RATE

C

DO 7700

TFLHT =

VQDOT =

7700 CONTINUE

J=IBOTP,ITOP

TFLHT + FLHT(I,J)

VQDOT + Q(I,J)

- 154 -
C

C DETERMINE AVERAGE HEAT FLUX, FLAME TEMPERATURE (USED FOR ALL CELLS)

C

QDOTC(I,ITOP) = VQDOT*GAMN(I,ITOP)

HTFLUX = VQDOT/(2.*TFLHT*WID(I))

FLAMT = SQRT(SQRT(HTFLUX/5.6697E-8))

DO 7900 J=IBOTP,ITOP

QDOT2P(I,J) = HTFLUX

FLTEMP(I,J) = FLAMT

7900 CONTINUE

IBOTP = ITOP + 1

IF (IBOTP.LE.NFCI) GO TO 7100

8000 CONTINUE

IF ((NBURN.EQ.0).OR.(TMDOT.LE.l.E-30)) GO TO 9500

IF (.NOT.LROOM) GO TO 8200

C

C THE FOLLOWING STATEMENTS USED TO

C COMPUTE AVERAGE FUEL RADIUS, AND FLAME HEIGHT

C (USED IN PLUME FLOW MODEL) ARE DELETED FROM THE OLD VERSION

C THE FLAME BASE ELEVATION STEP IS RETAINED

C

C FRADA SQRT(FUELA/3.14159)

C FHTA FHTA/TMDOT

C

ZOA = ZOA/TMDOT

C

C HEAT SOURCE CALCULATINS FOR BARRIERS, CEILING, AND WALLS

C

8200 DO 8900 I=1,NSM

C

IF (.NOT.(LB(I).OR.LC(I).OR.LW(I))) PJ TO 8900

C

ITYPE ITYP(I)

NFCI NFC(I)

EPS = 1. - REFL(ITYPE)

C TK = THK(ITYPE)

C TDIFF - DIFF(ITYPE)

C DELX = DEP(I)/10.

C

C MODIFICATION INCORPORATES TRANSIENT HEAT CONDUCTION EDUATION

C IN BARRIER MODEL, AS SELL AS CEILING AND WALL MODELS.

C HEAT CONDUCTIOIN CALCULATIONS ARE NOW PERFORMED IN IGNIT;

C SURFACE TEMPERATURES AND HEAT FLUXES ARE ASSUMED TO BE GIVEN.

C

C OLD VERSION:

C

C IF (LW(I).OR.LC(I)) GO TO 8500

C IF (LB(I)) CALL BARR(IDIM1,IDIM2,I,NFCI,NWRITE,TK,EPS,

C 1 DEP(I),FZ,QDOT2PQEXT0,TEMP)

C IF (LEND) GO TO 9000

C GO TO 8900

C8500 DO 8560 K=1,NSM

C DO 8550 J=1,NFCI

C IF (LIURN(K,J)) GO TO 8570

- 155 -
C8550 CONTINUE

C8560 CONTINUE

C GO TO 8600

C8570 IF (LC(I)) CALL CEILNG(EPS, REFL(ITYPE),QDOT2P(ICEIL,1),

C 1 QEXTO(ICEIL,1),TEMP(ICEIL,1,1),FZ(ICEIL, 1),NWRITE)

C IF (LEND) GO TO 9000

C8600 DO 8700 J=INFCI

C HL = HCEIL

C IF (LW(I)) QDOT2P(I,J) = 5.6697E-8*EPS*TEMP(I,J,1)**4

C 1 + REFL(ITYPE)*QEXTO(I,J)

C

C NEW VERSION:

C

IF (NBURN.EQ.0) GO TO 8600

C

C CEILING COMPUTATIONS

C

IF (.NOT.LC(I)) GO TO 8600

C

C SUBROUTINE CGAS WILL BE CALLED ONCE AT THE FIRST TIME STEP TO

C COMPUTE THE THICKNESS OF THE HOT GAS, LAYER AND THEN

C USES THIS THICKNESS TO ESTIMATE THE HOT GAS EMISSIVITY

C WHICH HAS BEEN FOUND TO BE INSENSITIVE TO THE HGL

C THICKNESS. THE EMISSIVITY WILL BE UPDATED AT EACH TIME STEP

C.

IF (GEMS.GT.O.) GOTO 8350

CALL CGAS(EPS,REFL(ITYPE) ,QDOT2P(ICEIL, 1),

1 QEXTO(ICEIL,l),TEMP(ICEIL,1,1),FZ(ICEIL,1),NWRITE)

GEMS = 1. - EXP(-GABSRP*DG)

8350 IF ((TQDOTC.LE.1.).OR.(TQDOT.LE.1.)) GOTO 9500

CALL CGAS(EPS,REFL(ITYPE) ,QDOT2P(ICEIL,1),

1 QEXTO(ICEIL,1) ,TEMP(ICEIL,1,1),FZ(ICEIL,1),NWRITE)

GEMS = 1. - EXP(-GABSRP*DG)

QDOT2P(ICEIL,I) = QDOT2P(ICEIL,1)*FCTR(12)

IF (LEND) GO TO 9000

C

C WALLS AND BARRIERS

C

8600 IF (.NOT.(LW(I).OR.LB(I))) GO TO 8900

DO 8700 J=1,NFCI

TEMPS = TEMP(I,JI)

REFLEC = REFL (ITYPE)

C

C WALL SOURCE IS FRONT SIDE OF THE WALL. INCLUDES REFLECTION OF

C EXTERNAL RADIATION. BARRIER SOURCE IS BACKS.IDE OF BARRIER.

C DOES NOT INCLUDE EXTERNAL RADIATION REFLECTION (ASSUMED TO ONLY

C STRIKE FRONT.

C

IF (LW(I)) GO TO 8650

TEMPS = TEMP(I,J, 0)

REFLEC = 0.

8650 QDOT2P(I,J) = 5.6697E-8*EPS*-EMPS**4 + REFLEC*QEXTO(IJ)*

1 FCTR(13)

C

- 156 -
IF (LEND) GO TO 9000

8700 CONTINUE

8900 CONTINUE

9000 RETURN

9500 WRITE (NWRITE,9600)

9600 FORMAT (1H0,35HEND OF JOB: NO FLAMES OVER FUEL BED)

LEND = .TRUE.

RETURN

END

- 157 -
C *

C SUBROUTINE TRANSF (COMPUTES HEAT FLUX TRANSMITTED TO FUEL *

C ELEMENTS, WALLS, BARRIERS, AND CEILING, *

C AND SURROUDING TEMPERATURES) *

C *

SUBROUTINE TRANSF(FLHT,FLTEMP,FX,FY,FZ,HCOEF,QDOTC,QDOT2P,QEXCAL,

1 QEXNET,QEXT,QEXTOT,TSURRTEMP,AREA,DELS,RAD,WID,FABSRP,

2 GAMMA ,REFL, ICOMM, ICOUNT, IORT, ITYP,NFC,LBURN, LDAMGE,LPIGN,LPLUME,

3 LB,LC,LDLW,IDIM1,IDIM2,IDIM3,NFUEL,NSM,NWRITE)

IMPLICIT LOGICAL (L)

DIMENSION FLHT(IDIM1,IDIM2), FLTEMP(IDIM1,IDIM2), FX(IDIM1,IDIM2),

I FY(IDIM1,IDIM2), FZ(IDIM1,IDIM2), HCOEF(IDIMI,IDIM2),

2 QDOTC(IDIM1,IDIM2), QDOT2P(IDIM1,IDIM2), QEXCAL(IDIM1,IDIM2),

3 QEXNET(IDIM1,IDIM2), QEXT(IDIM1,IDIM2), QEXTOT(IDIM1,IDIM2),

4 TSURR(IDIM1,IDIM2),TEMP(IDIM1 ,IDIM2,10), ICOUNT(IDIM1,IDIM2),

5 LBURN(IDIM1,IDIM2), LDAMGE(IDIM1,IDIM2),

6 LPIGN(IDIM1,IDIM2), LPLUME(IDIM1,IDIM2)

DIMENSION AREA(NSM), DELS(NSM), RAD(NSM), WID(NSM),

1 IORT(NSM), ITYP(NSM), NFC(NSM),

2 LB(NSM), LC(NSM), LD(NSM), LW(NSM)

DIMENSION FABSRP(NFUEL), GAMMA(NFUEL), REFL(NFUEL)

DIMENSION ICOMM(IDIM3, IDIM3)

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT; FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

1 FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

2 RADCON, TG, VFV, WHEAT, ZD, ZN,

3 LSMALL

COMMON /VENTC/ AFUEL, AFUELO, CVA, CVAO, QMAX,

1 QTOT, QTOTO, QTOT1, QTOT2,. TMDOT, TMDOT0,

2 TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

3 NBURN, NBURNO,

4 LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

IJ = 0

C

C HEAT FLUX SOURCE LOOP

C

DO 5900 I=I,NSM

NFCI = NFC(I)

IF (.NOT.LD(I)) GO TO 1000

IJ = IJ + NFCI

GO TO 5900

1000 FRAD = RAD(I)

ITYPE = ITYP(I)

LWALBR (LW(I).OR.LB(I).OR.LC(I))

LCEIL LC(I)

LORNT (IORT(I).NE.3)

DO 5800 J=1,NFCI

IJ = IJ + 1

IF (LWALBR) GO TO 2000

- 158 -
IF (.NOT.LBURN(I,J)) GO TO 5800

C

C FLAME LOCATION

C

FIX = FX(I,J)

FLY = FY(I,J)

FLZ1 = FZ(I,J)

IF (LORNT) FLZ1 = FLZ1 - DELS(I)/2.

FLZ2 = FLZ1 + FLHT(I,J)

HTFLUX = GAMMA(ITYPE)*QDOT2P(I,J)

2000 KM = 0

C

C HEAT FLUX RECEIVER LOOP (NON-ADJACENT FUEL CELLS)

C

DO 5500 K=1,NSM

NFCK = NFC(K)

LIK = (I.EQ.K)

3000 IF (LWALBR) GO TO 3500

LORNT2 = (IORT(K).NE.3)

LORNT3 = (LORNT. AND. LORNT2)

3500 DO 5000 M=I,NFCK

KM = KM + 1

IF (ICOMH(IJKM).EQ.0) GO TO 5000

IF (LWALBR) GO TO 4700

IF ((ICOMM(IJKM).EQ.2).OR.(LVCONT.AND.LBURN(K,M))) GO TO 5000

C

C RECEIVER LOCATION (FLAME LOOP)

C

FZKM = FZ(KM)

FR = SQRT((FX(K,M) - FLX)**2 + (FY(K,M) - FLY)**2)

DELZ1 = ABS(FZKM - FLZ1)

DELZ2 = ABS(FZKM - FLZ2)

IF (FR.LE.RAD(I)) GO TO 4300

C

C

C RADIATIVE HEAT FLUXES (WHEN FR.GT.FRAD)

C

C

IF (LORNT2) GO TO 4000

Ql = CYLPAR(DELZ1,FR,FRAD)

Q2 = CYLPAR(DELZ2,FR,FRAD)

GO TO 4100

4000 Q1 = CYLPER(DELZ1,FR,FRAD)

Q2 = CYLPER(DELZ2,FR,FRAD)

4100 IF (FZKM.GT.FLZ2) Q2 = -Q2

IF (FZKM.LT.FLZ1) Qi = -Qi

DELTQ = ((DELZ1*Q1 + DELZ2*Q2)/FLHT(I,J))*HTFLUX*FCTR(S)

GO TO 4800

C

C

C RECEIVER ENVIRONMENT (TEMPERATURE, HEAT TRANSFER COEFFICIENT)

C WHEN RECEIVER IS ABOVE OR BELOW FLAME. USES MAXIMUM TEMPERATURE

C AND ASSOCIATED COEFFICIENT IF MORE THAN ONE VALUE IS POSSIBLE.

C

- 159 -
C

4300 IF ((QDOTC(I,J).LT.100.).OR.(FZKM.LT.FLZ1).OR.

1 ((I.EQ.K).AND.LBURN(K,M))) GO TO 5000

IF (FZKM.GE.FLZ2) GO TO 4400

C

C FLAME ENVIRONMENT

C

DELTQ = 0.

IF (FLTEMP(I,J).LT.TSURR(K,M)) GO TO 4800

TSURR(K,M) = FLTEMP(I,J)

HCOEF(K,M) = FLCF

LPIGN(K,M) = .TRUE.

LPLUME(K,M) = .TRUE.

GO TO 4800

C

C PLUME TEMPERATURE USING ALPERT'S CORRELATION IS CHANGED TO

C ZUKOSKI'S CORRELATION IN ORDER TO BE CONSISTENT WITH THE

C PLUME ENTRAINMENT MODEL

C OLD VERSION:

C

C PLTEMP = .169*(QDOTC(I,J)**.6667)/(DELZ1**1.6667) + RTEMP

C

C NEW VERSION:

C

4400 PLTEMP = RTEMP*(I. + 3.814E-2*(QDOTC(I,J)/RTEMP)**(2./3.)

1 /DELZ1**(5./3.))

PLTEMP = AMIN1(PLTEMP,FLTEMP(I,J))*FCTR(6)

IF (.NOT.LORNT2) GO TO 4500

C

C FOR VERTICAL OBJECTS, HEAT TRANSFER COEFFICIENT - FLAME COEFFICIENT

C

PLCOEF = FLCF*FCTR(7)

GO TO 4600

C

C HEAT TRANSFER COEFFICIENT FOR HORIZONTAL OBJECTS

C

C MODIFICATION TO COMPUTE A POINT VALUE FOR H, RATHER THAN AN

C AVERAGE VALUE (8/22/84). CORRELATION USED IS STILL FROM

C VELDMAN, ET AL. OLD VERSION:

C

C4500 RKM = SQRT(DELS(K)*WID(K)/3.14159)/DELZ1

C PLCOEF = .64

C IF (RKH.LT.0.18) PLCOEF = 2.06

C PLCOEF = (PLCOEF*(QDOTC(I,J)/DELZ1)**.3333)*FCTR(8)

C

C NEW VERSION:

4500 RDZ = AMAX1(0.1,FR/DELZ1)

PLCOEF = 0.9*(RDZ**(-.65))*((QDOTC(I,J)/DELZI)**.3333)*FCTR(8)

C

C PLUME ENVIRONMENT

C

4600 DELTQ = 0.

IF (PLTEMP.LT.TSURR(K,M)) GO TO 4800

TSURR(K,M) = PLTEMP

- 160 -
HCOEF(K,M) i PLCOEF

LPLUME(K,H) = .TRUE.

GO TO 4800

C

C RADIATIVE HEAT TRANSFER FROM

C WALL, BARRIER, AND CEILING SOURCES

C

C

C

C

C THIS IS THE NEW VERSION TO BE INCORPORATED AFTER TESTING

C

4700 DELTQ = 0. IF ((.NOT.LROOM).OR.(FZ(K,M).LT.ZD).OR.(.NOT.LCEIL))

1 DELTQ = ICOMM(IJ,KM)*QDOT2P(I,J)/1000.

4800 QEXT(KM) = QEXT(K,M) + DELTQ

LFLUX1 = TRUE.

C

C CEILING HOT GAS LAYER ENVIRONMENT

C

IF ((.NOT.LROOM).OR.(FZ(K,M).LT.ZD).OR.(TSURR(K,M).GT.TG))

1 GO TO 5000

TSURR(K,M) = TG*FCTR(9)

HCOEF(K,M) = HCEIL

LPLUME(K,M) .FALSE.

C

C THIS IS THE OLD 'INCORRECT' VERSION (CEILING DOES NOT SEE THE

C HOT GAS LAYER ENVIRONMENT)

C

C4700 DELTQ = ICOMM(IJ,KM)*QDOT2P(I,J)/1000.

C IF ((.NOT.LROOM).OR.(.NOT.LCEIL).OR.(FZ(KM).LT.ZD).OR.

C 1 (TSURR(K,M).GT.TG)) GO TO 4800

C

C CEILING HOT GAS LAYER ENVIRONMENT

C

C TSURR(K,M) = TG*FCTR(9)

C HCOEF(KM) = HCEIL

C LPLUME(K,M) = .FALSE.

C DELTQ = 0.

C4800 QEXT(K,M) = QEXT(K,M) + DELTQ

C LFLUX1 = .TRUE.

C%% %%%%%%Y.%%%%%%%/%%%

5000 CONTINUE

5500 CONTINUE

C

C HEAT TRANSFER TO SELF FOR VERTICAL FUEL CELLS

C (USING A BEST-FIT FOR THE SHAPE FACTOR FROM FLAME TO FUEL)

C

IF ((.NOT.LORNT).OR.LVCONT.OR.LWALBR) GO TO 5800

XCOUNT = ICOUNT(I,J)

VSHAPE = -. 197 + .24*WID(I) + .02*FLHT(I,J) + .0538*DELS(I)

1 * (XCOUNT - .5) + .0256*DELS(I)*(XCOUNT-.5)/FLHT(I,J)

2 + .0724*FABSRP(ITYPE)

- 161 -
VSHAPE = AMINl(1.,AMAX1(0.,VSHAPE))

DELTQ = GAMMA(ITYPE)*QDOT2P(I,J)*VSHAPE*FCTR(O)

QEXT(I,J) = QEXT(I,J) + DELTQ

5800 CONTINUE

5900 CONTINUE

IF (.NOT.LROOM) GO TO 6000

C

C

C

C

C

C

C

DETERMINE IF VENTILATION CONTROLLED (USING SIMPSON'S RULE

EXTRAPOLATION FOR HEAT SUPPORT BY AIR INITIALLY IN ROOM

QTOT2 = TQDOT

DQTOT = DELT*(-QTOT0 + 8.*QTOTI + 5.*QTOT2)/12.

QTOT = QTOT + DQTOT

QTOTO = QTOT1

QTOT1 = QTOT2

INDICATOR VARIABLE TO SHOW IF FIRE HAS BEEN BURNING FOR THE

TWO PREVIOUS TIME STEPS

LFLUX = (LFLUX1.AND.LFLUX2)

IF ((.NOT.LVENT) .OR. (LVENT.AND.LDECAY.AND.LFLUX)) TMDTSO TMDOTS

TMDOTV = CVAO-*WIN/AFUELO

LVENT = ((TMDOTV.LT.TMDTSO).AND.(QTOT.GE.QMAX))

LDECAY = (LDECAY.OR.(NBURN.LT.NBURNO))

LVCONT = (LVENT.AND..NOT.LDECAY)

C HEAT TRANSFER TO ADJACENT (NON-BURNING) FUEL CELLS FROM

C CONTINUOUS PROPAGATION OF FLAMES

C

6000 IJ = 0

DO 6900 I=1,NSM

NFCI = NFC(I)

IF (.NOT.(LD(I).OR.LW(I).OR.LB(I).OR.LC(I))) GO TO 6050

IJ = IJ + NFCI

GO TO 6900

6050 ITYPE = ITYP(I)

LORNT = (IORT(I).NE.3)

DO 6600 J=1,NFCI

IJ = IJ + 1

IF (.NOT.LBURN(I,J)) GO TO 6600

FLZ = FZ(I,J)

C

C CONDUCTIVE HEAT TERM

C

QCOND = (.01157+5.6697D-5*FLTEMP(I,J))*(FLTEMP(I,J)-TEMP(I,J,1))*

1 WID(I)

KM = 0

DO 6400 K1tNSH

AREAK f WID(K)*DELS(K)

NFCK = NFC(K)

LORNT2 = (LORNT.AND.(IORT(K).NE.3))

DO 6300 M=1,NFCK

KM = KM + 1

IF ((ICOMM(IJ,KM).NE.2).OR.LBURN(KM)) GO TO 6300

IF (LORNT2) GO TO 6100

QRAD = GAMMA(ITYPE)*QDOT2P(IJ)*AREA(I)

- 162 -
DELTQ = (QRAD + QCOND)/AREAK

GO TO 6200

6100 DELTQ = QCOND/AREAK

C

C REVISE CHARACTERIZATION OF ENVIRONMENT OF ADJACENT VERTICAL

C CELLS, TO BE CONSISTEN WITH TREATMENT FO HORIZONTAL CELLS

C

C OLD VERSION:

C

C IF ((I.EQ.K).AND.(M.GT.J)) DELTQ = QDOT2P(I,J)

C

C NEW VERSION:

C

IF ((FZ(K,M).LT.FLZ).OR.(TSURR(K,M).GT.FLTEMP(I,J)))

1 GO TO 6200

TSURR(K,M) = FLTEMP(IJ)

HCOEF(K,M) = FLCF

LPLUME(K,M) = .TRUE.

C

6200 QEXT(K,M) = QEX.T(K,M) + DELTQ*FCTR(11)

LPIGN(KM) .TRUE.

6300 CONTINUE

6400 CONTINUE

6600 CONTINUE

6900 CONTINUE

C

C COMPUTE NET HEAT FLUX AT SURFACE (FOR OUTPUT PURPOSES ONLY)

C

DO 7500 I=1,NSM

NFCI = NYC(I)

EPS = 1. - REFL(ITYP(I))

FSIG = EPS*5.6697E-8

DO 7000 J=1,NFCI

QEXTOT(I,J) = EPS*QEXT(I,J) + HCOEF(I,J)*TSURR(I,J)

1 + FSIG*TSURR(I,J)**4

QEXCAL(I,J) = QEXTOT(I,J) - HCOEF(I,J)*CALTEM

1 - FSIG*CALTEM**4

QEXNET(I,J) = QEXTOT(I,J) - HCOEF(I,J)*TEMP(I,J,1)

1 - FSIG*TEMP(I,J,1)**4

7000 CONTINUE

7500 CONTINUE

RETURN

END

- 163 -
C *

C SUBROUTINE IGNIT (DETERMINES THERMAL RESPONSE OF OBJECTS IN *

C ROOK, IF OBJECTS ARE DAMAGED, AND IF FUEL

C CELLS ARE IGNITED)

C *

SUBROUTINE IGNIT (HCOEF,IHCOEFO,QEXT,QEXTO,TSURR,TSURRO,TEMPJ,

1 DEP,DIFF,FIGTP,FIGTS,FTDAM,REFL,THK,ITYP,NFC,LBURN,LDAMGE,

2 LFMASS,LPIGN,LPLUME,LB,LC,LD,LW, IDIM1,IDIM2,NFUEL,NSM,NWRITE)

IMPLICIT LOGICAL WL)

DIMENSION HCOEF(IDIM1,IDIM2), HCOEFO(IDIM1,IDIM2),

1 QEXT(IDIM1,IDIM2), QEXTO(IDIM1,IDIM2),

2 TSURR(IDIMI,IDIM2), TSURRO(IDIM1,IDIM2), TEMP(IDIM1,IDIM2,10),

3 LBURN(IDIM1,IDIM2), LDAMGE(IDIM1,IDIM2), LFMASS(IDIM1,IDIM2),

4 LPIGN(IDIM1,IDIM2), LPLUME(IDIM1,IDIM2)

DIMENSION DIFF(NFUEL), FIGTP(NFUEL), FIGTS(NFUEL), FTDAM(NFUEL),

1 REFL(NFUEL), THK(NFUEL)

DIMENSION DEP(NSM), ITYP(NSM), NFC(NSM), LB(NSM), LC(NSM),

1 LD (NSM), LW(NSM)

COMMON /ALL/ ACEIL, AWALL, C4LTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

DO 8000 I=1,NSM

C

C SUBROUTINE NOW PERFORMS HEAT CONDUCTION CALCULATIONS FOR BARRIERS,

C AS WELL AS OTHER FUEL CELLS. SUBROUTINE BARR IS NO LONGER NEEDED.

C

C OLD VERSION:

C

C IF (LD(I).OR.LB(I)) GO TO 8000

C

C NEW VERSION:

C

IF (LD(I)) GO TO 8000

C

LBCW = (LW(I).OR.LC(I).OR.LB(I))

ITYPE = ITYP(I)

NFCI = NFC(I)

C

C ASSIGNMENT OF RIGHT-HAND-SIDE BOUNDARY CONDITION TYPE

C

IBC = 1

IF (LB(I)) IBC =.3

C

TK = THX(ITYPE)

EPSI = 1. - REFL(ITYPE)

TDIFF = DIFF(ITYPE)

C

C CORRECTION TO EARLIER CALCULATION OF INTERVAL WIDTH WITHIN A

C FUEL CELL (10 NODES ARE ASSIGNED PER FUEL CELL).

C

C OLD VERSION:

- 164 -
C

C DELX = DEP(I)/10.

C

C NEW VERSION:

C

DELX = DEP(I)/9.

C

DO 7000 J=1,NFCI

IF (LBURN(I,J).OR.LFMASS(I,J)) GO TO 7000

EPS = EPSI

IF (LPLUME(IJ)) EPS = 0.

C

C NEW VERSION ALLOWS VARIED BOUNDARY CONDITIONS AT THE BACK

C SIDE OF THE FUEL ELEMENT (OLD VERSION CORRESPONDS TO IBC=1)

C

C IBC=1: BACK SIDE FIXED AT RTEMP (SEMI-INFINITE MODEL)

C IBC=2: ADIABATIC BACK SIDE (NOT CURRENTLY IMPLEMENTED IN

C COMPBRN II

C IBC=3: FULL CONVECTION AND RADIATION (USED FOR BARRIERS)

C

C OLD VERSION:

C

C CALL DIFFUS(TEMP,DELX,EPS,HCOEF(IJ),HCOEFO(I,J),QEXT(I,J),

C 1 QEXTO(IJ),TDIFF,TK,TSURR(I,J),TSURRO(I,J),

C 2 IDIM1,IDIM2,I,J,NWRITE)

C

C NEW VERSION:

C

CALL DIFFUS(TEMP,DELX,EPS,HCOEF(I,J),HCOEFO(I,J),QEXT(I,J),

1 QEXTO(I,J),TDIFF,TK,TSURT, (IJ),TSURRO(I,J),

2 IBC, IDIM1,IDIM2,IJNWRIi)

C

IF (LBCW) GO TO 7000

IF (TEMP(I,J,1).GT.FTDAM(ITYPE)) LDAMGE(I,J) = .TRUE.

TIG = FIGTS(ITYPE)

IF (LPIGN(IJ)) TIG = FIGTP(ITYPE)

IF ((TEMP(I,J,1).LT.TIG).OR.(TIME.EQ.0.).OR.(TIME.EQ.DELT))

1 GOTO 7000

LBURN(IJ) = .TRUE.

C LPIGN(I,J) = .TRUE.

7000 CONTINUE

8000 CONTINUE

RETURN

END

- 165 -
C *

C SUBROUTINE OUTPUT (PRINTS PROGRAM OUTPUT)*

C

C NEW VERSION ALLOWS USER TO OUTPUT LOCAL HEAT TRANSFER COEFFICIENT

C AND LOCAL ENVIRONMENT TEMPERATURE FOR A FUEL CELL.

C

C OLD VERSION:

C

C SUBROUTINE OUTPUT(FLHT ,FLTEMP,FMASS,QDOT2P,QEXCAL,QEXNET,QEXT,

C I QEXTOT,TEMP,LBURN,ELDAMGE,NFC,MSMOUT,IDIM1,IDIM2,NSM,NSMOUT,

C 2 NWRITE)

C

C NEW VERSION:

C

SUBROUTINE OUTPUT (FLHT, FLTEMP, FMASS, HCOEF, QDOT2P, QEXCAL,QEXNET,

1 QEXT,QEXTOT,TEMP,TSURR,LBURN,LDAMGE,NFC,MSMOUT,IDIM1,IDIM2,

2 NSM,NSMOUT,NWRITE)

C

IMPLICIT LOGICAL (L)

DIMENSION FLHT(IDIM1 , IDIM2), FLTEMP(IDIM1 , IDIM2),

1 FMASS(IDIM1,IDIM2), QDOT2P(IDIM1,IDIM2),

2 QEXCAL(IDIMI,IDIM2), QEXNET(IDIM1, IDIM2),

3 QEXT(IDIM1, IDIM2), QEXTOT(IDIMI,IDIM2),

4 TEMP(IDIM1,IDIM2,10), LBURN(IDIMI,IDIM2),

5 LDAMGE(IDIM1,IDIM2), NFC(NSM), MSMOUT(NSMOUT)

c

DIMENSION HCOEF(IDIM1, IDIM2), TSURR(IDIM1 , IDIM2)

c

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

1 FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

2 RADCON, TG, VFV, WHEAT, ZD, ZN,

3 LSMALL

COMMON /VENTC/ AFUEL, AFUELO, CVA, CVAO, QMAX,

1 QTOT, QTOTO, QTOT1, QTOT2, TMDOT, TMDOTO,

2 TMDOTS, TQDOT, TQDOTC,"WIN, ZOA,

3 NBURN, NBURNO,

4 LDECAY, LFLUXl, LFLUX2, LVENT, LVCONT

WRITE (NWRITE,9000) TITLE, TIME

C LOUT = (NSMOUT.EQ.0)

LOUT = (NSMOUT.LE.0)

C

IF (IOUTPT.NE.0) GO TO 2000

WRITE (NWRITE,9100) TMDOT

IF (LOUT) RETURN

DO 1000 I=1,NSMOUT

K = MSMOUT(IM

NFCK = NFC(K)

WRITE (NWRITE,9500) K, (LBURN(K,J),J=1,NFCK)

- 166 -
1000 CONTINUE

RETURN

2000 DO 5000 II=1,IOUTPT

INDEX = MOUTPT(II)

C

GO TO (2100,2300,2500,2700,2900,2900,2900,2900,2900,2900,2900,

1 2900,2900,2900,2900,2900,2900), INDEX

C

2100 WRITE (NWRITE,9100) TMDOT

GO TO 5000

2300 WRITE (NWRITE,9200) TQDOT

GO TO 5000

2500 WRITE (NWRITE,9300) TG

GO TO 5000

2700 WRITE (NWRITE,9400) DG

GO TO 5000

2900 IF (LOUT) GO TO 5000

WRITE (NWRITE, 9450)

DO 4000 I=1,NSMOUT

K = MSMOUT(I)

NFCK = NFC(K)

C

GO TO (4000,4000,4000,4000,3000,3050,3100,3200,3300,3350,3400,

1 3500,3600,3700,3800,3900,3950), INDEX

C

3000 WRITE (NWRITE,9500) K,

GO TO 4000

3050 WRITE (NWRITE,9550) K,

GO TO 4000

3100 WRITE (NWRITE,9600) K,

GO TO 4000

3200 iQRITE (NWRITE,9650) K,

GO TO 4000

3300 WRITE (NWRITE,9700) K,

GO TO 4000

3350 WRITE (NWRITE,9725) K,

GO TO 4000

3400 WRITE (NWRITE,9750) K,

GO TO 4000

3500 WRITE (NWRITE,9800) K,

GO TO 4000

3600 WRITE (NWRITE,9900) K,

GO TO 4000

3700 WRITE (NWRITE,9930) K,

GO TO 4000

3800 WRITE (NWRITE,9950) K,

GO TO 4000

C

C ADDED WRITE STATEMENTS:

C

3900 WRITE (NWRITE,9960) K,

GO TO 4000

3950 WRITE (NWRITE,9970) K,

C

(LDAHGE(K,QJ),J=1,NFCK)

(LBURN(K,J), J=1,NFCK)

(QDOT2P(K,J),J=1,NFCK)

.(QEXT(K,J) ,J=1,NFCK)

(QEXTOT(K,QJ),J=1,NFCK)

(QEXCAL(K,J), J=1,NFCK)

(QEXNET(K,J),J=1,NFCK)

(FMASS(K,QJ),J=1,NFCK)

(FLHT(K,J) ,J=1 ,NFCK)

(FLTEMP(K,J),J=1,NFCK)

(TEMP(K,J, 1) ,J=1,NFCK)

(HCOEF(K,J) ,J=1,NFCK)

(TSURR(K,J),J=1,NFCK)

- 167 -
4000 CONTINUE

5000 CONTINUE

9000

9100

9200

9300

9400

9450

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

(1HI,20A4,/,lX,11HTIME (SEC):,F6.0,//)

(IH ,31HTOTAL MASS BURNING RATE (KG/S):,GI2.4)

(IH ,31HTOTAL HEAT RELEASE RATE (W) :,G12.4)

(1H ,31HHOT GAS LAYER TEMPERATURE (K) :,G12.4)

(1H ,31HHOT GAS LAYER THICKNESS (M) :,G12.4)

(IHO)

FORMAT STATEMENTS:

C

C MODIFIED

C

9500

9550

9600

9650

9700

9725

9750

9800

9900

9930

9950

C

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

FORMAT

(1H

(1H

(1H

(1H

(1H

(1H

(1H

(1H

(1H

(OH

(1H

,7HMODULE:,I4,3X,16HDAHAGE ?

,7HMODULE:,I4,3X,16HBURNING?

,7HMODULE:,I4,3X,16HSOURCE FLUX

7HMODULE:,I4,3X,16HEXTERNAL FLUX

,7HMODULE:,I4,3X,16HTOTAL FLUX

,7HMODULE:,I4,3X,16HMEAS'D FLUX

,7HMODULE:,I4,3X,16HNET FLUX

,7HMODULE:,I4,3X,16HFUEL MASS

7HMODULE:,I4,3X,16HFLAME HGT

7HMODULE:,I4,3X,16HFLAME TEMP

,7HMODULE:,I4,3X,16HFUEL TEMP

,10G1.3)

1OG11.3)

,10G11.3)

, 10G11.3)

,10G11.3)

,10G11.3)

,10G11.3)

,10G11.3)

,10G11.3)

,10G11.3)

,10GlG1.3)

C ADDED FORMAT STATEMENTS:

C

9960 FORMAT (1H ,7HMODULE:,I4,3X,16HHEAT TRANS COEF ,10G11.3)

9970 FORMAT (1H ,7HMODULE:,I4,3X,16HENVIRONMENT TEMP,10G11.3)

RETURN

END

- 168 -
C

C SUBROUTINE ADJCTP FILLS IN BLOCKS OF THE ADJACENCY MATRIX.

C IF NADJ(IND,2) EQUALS '999', MODULE NADJ(IND,1) DOES NOT

C COMMUNICATE WITH MODULE NADJ(3). IF NADJ(2) EQUALS '888',

C MODULE NADJ(IND,I) DOES NOT COMMUNICATE WITH MODULES NADJ(IND,3)

C THRU NADJ(IND,4)

•C

C ---------------------------------------------------------------------

SUBROUTINE ADJCTP(IJ,KM,NFCL,NSTOP, IDIM3,ICOMM)

IMPLICIT LOGICAL (L)

DIMENSION ICONM C IDIM3, IDIM3)

IIJ = IJ

DO 2000 MI=1,NFCL

KKM = KM

DO 1000 MM=I,NSTOP

KKN = KKH + 1

ICOMM(IIJ,KKM) = 0

1000 CONTINUE

IIJ = IIJ + 1

2000 CONTINUE

RETURN

END

- 169 -
C

C SUBROUTINE COMM CONSTRUCTS THE ADJACENCY (COMMUNICATION) MATRIX

C FOR THE INDIVIDUAL FUEL CELLS - 0 = NO COMMUNICATION,

C 1 = COMMUNICATION, 2 = ADJACENCY

C

C----------------------------------------------------------------------

SUBROUTINE COMM(NCOM,NNCOM,NSM, IDIM1,IDIM3,IDIM4, IDIM35,NFC,IAD,

1 NAD,ICOMM)

IMPLICIT LOGICAL (L)

DIMENSION IAD(IDIM4,4), NAD(IDIM5,4), ICOMM(IDIM3,IDIM3),

1 NFC(IDIM1)

IF (NCOM.EQ.0) GO TO 1000

DO 900 IND=I,NCOM

IJ = 0

DO 800 I=1,NSM

NFCI = NFC(I)

IF (IAD(IND,1).EQ.I) GO TO 100

IJ = IJ + NFCI

GO TO 800

100 DO 700 J=1,NFCI

IJ = IJ + 1

LIADJ - (IAD(IND,2).EQ.999)

LID - (LIADJ.OR.(IAD(IND,2).EQ.J))

IF (.NOT.LID) GO TO 700

KM = 0

DO 600 K=I,NSM

NFCK = NFC(K)

IF (IAD(IND,3).EQ.K) GO TO 200

KM = KM + NFCK

GO TO 600

200 IF (LIADJ) GO TO 400

DO 300 M=I,NFCK

KM KM + 1

IF (IAD(IND,4).NE.M) GO TO 300

ICOMM(IJ,KM) = 2

ICOMM(KM,IJ) = 2

GO TO 900

300 CONTINUE

400 DO 500 M1I,NFCK

KM = KM + 1

ICOMM(IJ,KM) = 2

ICOMM(KM,IJ) = 2

IJ = IJ + 1

500 CONTINUE

GO TO 900

600 CONTINUE

700 CONTINUE

800 CONTINUE

900 CONTINUE

1000 IF (NNCOM.EQ.0) GO TO 2000

DO 1900 IND=I,NNCOM

IJ = 0

DO 1800 1=1,NSM

- 170 -
NFCI = NFC(I)

IF (NAD(IND,1).EQ.I) GO TO 1100

IJ = IJ + NFCI

GO TO 1800

1100 DO 1700 J=I,NFCI

IJ = IJ + 1

LNADJP = (NAD(IND,2).EQ.888)

LNADJ = (NAD(IND,2).EQ.999)

LND = (LNADJ.OR.LNADJP.OR.(NAD(IND,2).EQ.J))

IF (.NOT.LND) GO TO 1700

KM = 0

DO 1600 K=1,NSK

NFCK = NFC(K)

IF (NAD(IND,3).EQ.K) GO TO 1200

KM = KM + NFCK

GO TO 1600

1200 IF (LNADJP) GO TO 1330

IF (LNADJ) GO TO 1380

IF (NAD(IND,4).EQ.999) GO TO 1400

DO 1300 M=I,NFCK

KM = KM + 1

IF (NAD(IND,4).NE.M) GO TO 1300

ICOMM(IJ,KM) = 0

GO TO 1900

1300 CONTINUE

1330 NSTOP = 0

KM1 = NAD(IND,3)

KM2 = NAD(IND,4)

DO 1350 KMDtUM=KM1,KM2

NSTOP = NSTOP + NFC(KMDUM)

1350 CONTINUE

CALL ADJCTP(IJ,KM,NFCI,NSTOP,IDIM3,ICOMM)

GO TO 1900

1380 NSTOP= NFCK

CALL ADJCTP(IJKM,NFCI,NSTOP,IDIM3,ICOMM)

GO TO 1900

1400 DO 1500 M=1,NFCK

KM KM + 1

ICOMM(IJ,KM) = 0

1500 CONTINUE

GO TO 1900

1600 CONTINUE

1700 CONTINUE

1800 CONTINUE

1900 CONTINUE

2000 IJ = 0

DO 3000 I=1,NSM

NFCI = NFC(I)

DO 2500 J=1,NFCI

IJ = IJ + 1

ICOMM(IJ,IJ) = 0

KM = IJ + 1

IF (J.EQ.NFCI) GO TO 3000

ICOMM(IJ,KM) = 2

- 171 -
ICOMM(KM,IJ) = 2

2500 CONTINUE

3000 CONTINUE

.RETURN

END

- 172 -
C -----------------------------------------------------

C

C FUNCTION CYLPAR FINDS THE HEAT FLUX FROM A CYLINDRICAL FLAME TO

C AN INFINITESIMAL SURFACE PARALLEL TO THE GROUND. OLD VERSION IS

C A CORRECTED VERSION OF SUBROUTINE GIVEN IN COMPBRN I MANUAL, BUT

C IS ONLY GOOD FOR OBJECTS A SMALL DISTANCE AWAY FROM SMALL RADIUS

C FLAMES. NEW VERSION IS OBTAINED AS A LIMITING CASE FOR THE SHAPE

C FACTOR FROM A FRUSTRUM (TRUNCATED CONE) TO A DIFFERENTIAL SURFACE. -

C NEW VERSION ALSO ALLOWS FOR OBJECTS WITHIN THE FLAME (THE SHAPE

C FACTOR IS SET TO UNITY, INSTEAD OF LEADING TO AN ERROR).

C

C-------------------------------------------------------------------

FUNCTION CYLPAR(Z ,FR,FRAD)

IMPLICIT LOGICAL (L)

C

C OLD VERSION:

C

C IF (Z.GT.0.0) GO TO 100

C CYLPAR = 0.0

C RETURN

C 100 X = FR/Z

C R = FRAD/Z

C A = 1. + X**2 - R**2

C B = 1. + X**2 + R**2

C RAT = SQRT((X+R)/(X-R))

C CYLPAR = (ATAN(RAT) - (A/B)*ATAN(1./RAT))/3.14159

C

C NEW VERSION:

C

IF (Z.GT.0.0) GO TO 100

CYLPAR = 0.0

RETURN

100 IF (FR.GT.FRAD) GO TO 200

CYLPAR = 1.0

RETURN

200 A = FR + FRAD

B = FR - FRAD

AA = SQRT(Z**2 + A**2)

BB = SQRT(Z**2 + B**2)

RAT = SQRT(A/B)

CYLPAR = ATAN(RAT) - (Z**2 + FR**2 - FRADI*2)*

1 ATAN(AA/(BB*RAT) ) / (AA*BB)

CYLPAR = CYLPAR/3.14159

C

RETURN

END

- 173 -
C -

C

C FUNCTION CYLPER FINDS THE HEAT FLUX FROM A CYLINDRICAL FLAME TO

C AN INFINITESIMAL SURFACE PERPENDICULAR TO THE GROUND

C

C--------------------------------------------------------------------

FUNCTION CYLPER(Z ,FR,FRAD)

IMPLICIT LOGICAL (L)

PI = 3.14159

IF (Z.NE.0.0) GO TO 100

CYLPER = 0.0

RETURN

100 X = Z/FRAD

Y = FR/FRAD

A = (1.+Y)**2 + X**2

B = (1.-Y)**2 + X**2

YMIN = Y - 1.

YPLS = Y + 1.

CYLPER = (C./(PI*Y))*ATAN(X/SQRT(Y..*2-1.)) + (X/PI)*

1 ((A-2.*Y)*ATAN(SQRT(A*YMIN/(B*YPLS)))/(Y*SQRT(A*B))

2 - (l./Y)*ATAN(SQRT(YMIN/YPLS)))

RETURN

END

- 174 -
CC

C SUBROUTINE DIFFUS SOLVES THE TIME-DEPENDENT HEAT CONDUCTION

C EQUATION FOR GEOMETRY USING A CRANK-NICOLSON SCHEME. THIS

C UPDATED VERSION ALLOWS THE USE OF THREE BOUNDARY CONDITIONS

C AT THE RIGHT SIDE OF THE SLAB:

C

C IRBC=1 => THE RHS TEMPERATURE IS FIXED AT RTEMP

C IRBC=2 => THE NET HEAT FLUX AT THE RHS IS 0 (ADIABATIC)

C IRBC=3 => GENERAL NEWTON COOLING + RADIATION (SAME AS LHS)

C

C -------------------------------------------------------------------

C

C OLD VERSION (USED IN COMPBRN II SIMULATIONS):

C

C SUBROUTINE DIFFUS (TEMP,DELX,EPS,HL,HLO,QXT,QXTO,TDIFF,TK,TENV,

C 1 TENVO, IDIM1, IDIM2, 11,JI,NWRITE)

C NEW VERSION:

C

SUBROUTINE DIFFUS(TEMP,DELX,EPS,HLHLO,QXT,QXTO ,TDIFFTK,TENV,

1 TENVO,IRBC,IDIM1,IDIM2,IlJ1,NWRITE)

IMPLICIT LOGICAL ML)

DIMENSION BETA(9), GAMMA(9), D(9), U(10), V(10),

1 TEMP(IDIMI , IDIM2,10)

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

C INITIALIZATIONS

C

DO 1000 I=1,10

U(I) = TEMP(I1,J1,I)

1000 CONTINUE

FSIG = EPS*5.6697E-8.

TLAM = .5*TDIFF*DELT/DELX**2

DX3 3.*DELX

BJ 1. + 2.*TLAM

C LHS CONSTANT COEFFICIENTS

C

AlP = 1. + 3.5*TLAM + DX3*TLAM*HL/TK

C

BE =-4.TLAM

Cl =STLAM

CHECK = ABS(U(1)-TENVO)

Dl = (1. - 3.5*TLAM)*U(1) + 4.*TLAM*U(2) - .5*TLAMI*U(3)

1 + (DX3*TLAM/TK)*(HL*TENV + FSIG*TENV**4 + EPS*(QXT + QXTO))

IF(CHECK.GT. 1)

1 Dl = DI + (DX3*TLAM/TK)*( HLO*(TENVO - U(1))

2 + FSIG*(TENVO**4 - U(1)**4) )

C RHS CONSTANT COEFFICIENTS

C

IF (IRBC.EQ.1) GO TO 1500

- 175 -
A10 = .5*TLAM

B10 = -4.*TLAM

C10 = 1. + 3.5*TLAM

ClOP = C10 + DX3*TLAM*HL/TK

DIO = (1. - 3.5*TLAM)*U(1O) + 4.*TLAM*U(9) - .5*TLAM*U(8)

DiOP DiO

1500 A9P = -TLAM

B9P BJ

C

C INTERIOR CONSTANT COEFFICIENTS

C

C DO 2000 J=2,8

DO 2000 J=2,9

C

D(J) = U(J) + TLAM*(U(J-1) - 2.*U(J) + U(J+1))

2000 CONTINUE

C

C IMPROVE INITIAL GUESS FOR V(1) (USE AVERAGE OF ENVIORNMENT

C TEMPERATURE AND INITIAL TEMPERATURE).

C

C

C OLD VERSION

C

C VIOLD = U(l)

C NEW VERSION

C

VIOLD = (U(1) + TENV)/2.

C

IF (IRBC.EQ.1)

1 D(9) = TLAM*U(8) + (1. - 2.*TLAM)*U(9) + 2.*TLAM*RTEMP

VIOOLD = UO(10)

C

C BEGIN ITERATIONS

C

DO 8000 ITR=1,20

C LHS BOUNDARY

Al = AlP + DX3*TLAM*FSIG*V1OLD**3/TK

C2 = -TLA14*(1. - Cl/Al)

D2 = D(2) + TLAM*Dl/Al

C

C ADDED TREATMENT OF RHS

C

C RHS BOUNDARY

IF (IRBC.LT.3) GO TO 3000

C10 = ClOP + DX3*TLAM*FSIG*V10LD**3/TK

CHECK = ABS(U(10) - TENVO)

D1O = DIOP + (DX3*TLAM/TK)*(HL*TENV + FSIG*TENV**4)

IF (CHECK.GT.1.)

1 DIO = DIO + (DX3*TLAM/TK)*(HLO*(TENV - U(1O))

2 +.FSIG*(TENVO**4 - U(10)**4))

3000 A9 = A9P

B9 = B9P

D9 = D(9)

IF (IRBC.EQ.1) GO TO 5000

- 176 -
A9 = A9 + A10*TLAM/C10

B9 = B9 + B1O*TLAM/C1O

D9 = D9 + D1O*TLAM/C1O

C

C

C TRANSFORMED COEFFICIENTS (BETA AND GAMMA)

C

5000 BETA(2) BJ + TLAM*Bl/Al

GAMMA(2) = D2/BETA(2)

BETA(3) = BJ + TLAM*C2/BETA(2)

GAMMA(3) = (D(3) + TLAM*GAMHA(2))/BETA(3)

C DO 6000 I-4,9

DO 6000 1=4,8

C

BETA(I) = BJ - TLAM*TLAM/BETA(I-1)

GAMMAI) = (DI) + TLAM*GAMMA(I-1))/BETA(I)

6000 CONTINUE

C

BETA(9) = B9 + A9*TLAM/BETA(8)

GAMMA(9) = (D9 - A9*GAMMA(8))/BETA(9)

C

C

C SOLVE FOR TEMPERATURES

C

V(9) = GAMHA(9)

DO 7000 I=2,7

K =f10 - I

V(K) = GAMMA(K) + TLAM*V(K+1)/BETA(K)

7000 CONTINUE

V(2) = GAMMA(2) - C2*V(3)/BETA(2)

V(1) = (Dl - Bl*V(2) - Cl*V(3))/A1

V(10) = RTEMP

IF (IREC.GT.1) V(10) = (D1O - AIO*V(8) - BI0*V(9))/ClO

C

C CONVERGENCE BASED ON BOUNDARY TEMPERATURE ERROR

C

ERRL = ABS(V(1) - VIOLD)

C

C MODIFIED CONVERGENCE TREATMENT

C

C OLD VERSION:

C

C IF (ERRL.LT.1.) GO TO 8900

C VIOLD = V(1)

C

C NEW VERSION:

C

ERRR = 0.

LEL = (ERRL.LT.1.)

LER = .TRUE.

IF (IRBC.EQ.1) GO TO 7500

ERRR = ABS(V(10) - VIOOLD)

LER = (ERRR.LT.1.)

7500 IF (LEL.AND.LER) GO TO 8900

- 177 -
V1OLD = V(1)

VIOOLD - V(10)

C

8000 CONTINUE

C

C TEMPERATURE DUMP IF ITERATION MAXIMUM EXCEEDED

C

C PRINT OUT RHS ERROR

C

C OLD VERSION:

C WRITE (NWRITE,8100) II, J1, V(1), ERRL

C8100 FORMAT (lH0,44HITERATION MAX EXCEEDED IN SUBROUTINE DIFFUS:,

C 1 /,1X,71*IODULE:,I4,3X,10HFUEL CELL: ,14,/,lX,16HITERATION NO. 20,

C 2 /,X,I20HSURFACE TEMPERATURE:,E15.7,3X,6HERROR:,E15.7)

C

C NEW VERSION:

C

WRITE (NWRITE,8100) II, J1, V(1), ERRL, V(10), ERRR

8100 FORMAT (1H0,44HITERATION MAX EXCEEDED IN SUBROUTINE DIFFUS:,

1 /,IX,7HMODULE:,14,3X,10HFUEL CELL: ,14,/,1X,16HITERATION NO. 20,

2 /,lX,22HSURFACE TEMPERATURE :,E15.7,3X,6HERROR:,E15.7,

3 /,1X,22HBACK-SIDE TEMPERATURE:,E15.7,3X,6HERROR:,E15.7)

C

LEND = .TRUE.

GO TO 9000

8900 DO 8950 I=1,10

TEMP(I1,J1,I) = V(I)

8950 CONTINUE

9000 RETURN

END

- 178 -
C

C

C FUNCTION RADEQ SOLVES THE QUARTIC EQUATION: Xl--4 + A3*X + A4 =0 -

C

C ---------------------------------------------------------------------

FUNCTION RADEQ (A3,A4)

IMPLICIT LOGICAL (L)

R = 0.5*A3**2

Q - -4.*A4/3.

D = R**2 + Q**3

Y1 = (R + SQRT(D))**(1./3.) - (SQRT(D) - R)**(l./3.)

RADEQ = .5*(SQRT(2.*SQRT(Y"**2 - 4.*A4) - Yl) - SQRT(Y1))

RETURN

END

- 179 -
C

C

C FUNCTION RECT(A,B,C,LP) FINDS THE SHAPE FACTOR FROM A DIFFERENTIAL -

C ELEMENT TO A RECTANGLE OF DIMENSIONS A X B, AND SPACED C AWAY

C FROM THE ELEMENT. LP=.TRUE. => ELEMENT IS PARALLEL TO RECTANGLE, -

C LP=.FALSE. => ELEMENT IS PERPENDICULAR

C

C--------------------------------------------------------------------

FUNCTION RECT(ZDEP ,XLEN, YWID,LPARL)

IMPLICIT LOGICAL (L)

IF ((ZDEP.EQ.O.DO).OR.(XLEN.EQ.O.DO).OR.(YWID.EQ.O.DO))

1 GO TO 200

PI = 3.14159

IF (.NOT.LPARL) GO TO 100

X = XLEN/ZDEP

Y = YWID/ZDEP

A = SQRT(1. + X**2)

B = SQRT(1. + Y**2)

RECT = .5*(X*ATAN(Y/A)/A + Y*ATAN(X/B)/B)/PI

RETURN

100 X = XLEN/YWID

Y = ZDEP/YWID

A = SQRT(XLEN**2 + ZDEP**2)

RECT = .5*(ATAN(YWID/ZDEP) - ZDEP*ATAN(YWID/A)/A)/PI

RETURN

200 IF (LPARL.AND.(ZDEP.EQ.O.DO)) RECT - .5

IF (.NOT.LPARL.AND.(ZDEP.EQ.O.DO)) RECT = .25

IF ((XLEN.EQ.O.DO).OR.(YWID.EQ.O.DO)) RECT = 0.

RETURN

END

- 180 -
C

C

C SUBROUTINE SETUP COMPUTES THE FUEL CELL LOCATIONS FROM THE INPUT

C SUPER-MODULE DATA

C

C•-------------------------------------------------------------------

SUBROUTINE SETUP(I,IDIREC,IDIMI,IDIM2INFCL,SMX,SMY,SMZ,SLNG,

1 DS,FX,FY,FZ)

IMPLICIT LOGICAL (L)

DIMENSION FX(IDIM1,IDIM2), FY(IDIM1,IDIM2), FZ(IDIM1,IDIM2)

IF (IDIREC.EQ.3) GO TO 400

IF (IDIREC.EQ.2) GO TO 200

FXO = SMX - (SLNG + DS)/2.

DO 100 J=1,NFCL

FX(I,J) = FXO + J*DS

FYCIJ) = SMY

FZ(IJ) = SMZ

100 CONTINUE

GO TO 600

200 FYO = SMY - (SING + DS)/2.

DO 300 J=I,NFCL

FY(IJ) = FYO + J*DS

FX(I,J) = SMX

FZ(IJ) = SMZ

300 CONTINUE

GO TO 600

400 FZO = SMZ - (SLNG + DS)/2.

DO 500 J=I,NFCL

FZ(I,J) = FZO + J*DS

FX(I,J) = SMX

FY(I,J) = SHY

500 CONTINUE

600 CONTINUE

RETURN

END

- 181 -
C

C

C FUNCTION SHAPE FINDS THE SHAPE FACTOR FROM A DIFFERENTIAL FUEL

C ELEMENT TO AN ARBITRARILY LOCATED RECTANGLE, USING FUNCTION RECT

C

C----------------------------------------------------------------------

FUNCTION SHAPE(IOR,KOR,IDIRC,X1,YI,ZI,X2,Y2,Z2,DID2)

IMPLICIT LOGICAL (L)

DU = ABS(X1 - X2)

IF (IOR.EQ.2) DU = ABS(YI - Y2)

IF (IOR.EQ.3) DU = ABS(Z1 - Z2)

GO TO (100,200,300), IDIRC

100 WO = X2

Wl = Xl - D1/2.

VO = Y2

VI = Yl - D2/2.

IF (IOR.NE.2) GO TO 400

VO = Z2

V1 = Zi - D2/2.

GO TO 400

200 WO = Y2

Wi = Yl - DI/2.

VO = X2

Vi = Xi - D2/2.

IF (IOR.NE.1) GO TO 400

VO = Z2

Vi = Zi - D2/2.

GO TO 400

300 WO = Z2

Wi = Zi - D1/2.

VO = X2

VI = Xi - D2/2.

IF (IOR.NE..) GO TO 400

VO = Y2

Vi = Yi - D2/2.

400 W2 = Wl + Dl

V2 = Vi + D2

WSIGN = 1.

VSIGN = 1.

IF ((WO.GT.W2).OR.(WO.LT.Wi)) WSIGN = -1.

IF ((VO.GT.V2).OR.(VO.LT.Vi)) VSIGN = -1.

DW2 = ABS(W2 - WO)

DWi = ABS(Wi - WO)

DV2 = ABS(V2 - VO)

DV1 = ABS(Vi - VO)

DWA = AMAXi(DW2,DW1)

DWB = AMINI(DW2,DWi)

DVA = AMAXi(DV2,DVi)

DVB = AMINi(DV2,DVi)

LPR = (KOR.EQ.IOR)

IF (.NOT.LPR.AND.(KOR.NE.IDIRC)) GO TO 500

SHAPE = RECT(DUDWA,DVA,LPR) + VSIGN*RECT(DU,DWA,DVB,LPR)

1 WSIGN*RECT(DU,DWB,DVALPR) + VSIGN*WSIGN*RECT(DU,DWB,DVB,LPR)

RETURN

- 182 -
500 SHAPE = RECT(DU,DVA,DWA,LPR) + VSIGN*RECT(DU,DVB,DWA,LPR)

1 WSIGN*RECT(DU,DVA,DWB,LPR) + VSIGN*WSIGN*RECT(DU,DVB,DWBLPR)

RETURN

END

- 183 -
C

C SUBROUTINE CGAS REPLACES SUBROUTINE CEILNG TO CALCULATE

C THE CEILING HOT GAS LAYER PROPERTIES BY SOLVING THREE HIGHLY

C NON-LINEAR HEAT AND MASS BALANCE EQUATIONS WITH NEW PLUME

C FLOW CORRELATION.

C

C--------------------------------------------------------------------

SUBROUTINE CGAS(EPS, WREFL, QCEIL, QEXTC, TCEIL, RHGT, NWRITE)

IMPLICIT LOGICAL (L)

COMMON

1

2

3

COMMON

1

2

3

/ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

RTEMP, TIME, TITLE(20),

ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

LEND, LROOM

/GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

RADCON, TG, VFV, WHEAT, ZD, ZN,

LSMALL

COMMON /VENTC/

1

2

3

4

AFUEL, AFUELO, CVA, CVAO, QMAX,

QTOT, QTOTO, QTOT1, QTOT2,'TMDOT, TMDOTO,

TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

NBURN, NBURNO,

LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

C

C

C

C

C

C

C

C

CHARACTERIZE HOT GAS LAYER

DENSITY OF AIR = 1.18 KG/M"%3 AND CP = 1000 J/KG/K AT 298K

1.18*298 = 351.6

C

C

C

C

C

C

C

C

C

C

C

C

CFV = VFV*3.516E2

:IF THE GAS EMISSIVITY HAS NOT BEEN ASSESSED

IT IS ASSUMED TO BE EQUAL TO WALL EMISSIVITY

AND WILL BE UPDATED AFTER THE FIRST TIME STEP

IF ((GEMS.LT.1.).AND.(GEMS.GT.O.)) GOTO 100

RADCON = 5.6697E-8*EPS

GOTO 150

100 RADCON = 5.6697E-8*GEMS*EPS/(GEMS + EPS - GEMS*EPS)

150 CVENT = (FH - FC)*CFV

0.21*1.18**.6667*(9.8/1000)**.3333 = 0.05018

ENTRAINMENT RATE = PLUCON*(Z.)*•*-(5./3.)

PLUCON = 5.018E-2*PLCF*(TQDOTC/RTEMP)**(1./3.)

THE MAXIMUM HGL TEMPERATURE CAN BE SOLVED BY HEAT BALANCE EQUATION

Al = HCEIL/RADCON

WHEAT = ACEIL.TCEIL*(HCEIL + RADCON*TCEIL**3)

A2 = -1.*(TQDOTC + WHEAT)/ACEIL/RADCON

TGMAX = RADEQ(A1, A2)

- 184 -
C

C WPLRH = PLUME ENTRAINMENT RATE AT CEILING HEIGHT

C TPLRH = MEAN CEILING JET TEMPERATURE

C WVOUT = AIR OUTFLOW AT CEILING DUE TO FORCED VENTILATION

C

WPLRH = PLUCON*(RHGT - ZOA)**(5./3.)

TPLRH = RTEMP*(I. + 3.814E-2*•TQDOTC/RTEMP)**(2./3.)

1 /RHGT**(5./3.))/SQRT(2.)

WVOUT = CFV*(FH/TPLRH - FC/RTEMP)

DAREA = DHGT*DWID

C

C IF OPENINGS ARE PRESENT GOTO 4000

C

IF (DAREA.GT.O.01) GOTO 4000

C

C THE FOLLOWING PROCEDURES ARE TO ASSESSED THE HGL PROPERTIES

C WHEN OPENINGS ARE TOO SMALL TO ALLOW FREE AIR FLOW

C

C IF WPLRH IS SMALLER THAN THE NET FORCED VENTILATION OUTFLOW

C THROUGH CEILING, THEN THERE WILL NOT BE ANY HGL FORMED

C

IF (WPLRH.GE.WVOUT) GOTO 500

C

C ELSE, ONLY CEILING JET WILL BE PRESENT AND A WARNING MESSAGE

C WILL BE PRINTED

C

800 WIN = WPLRH

DG =0.

ZD = RHGT - ZOA

TG TPLRH

WRITE(NWRITE, 710)

710 FORMAT(3X,49H****''-**'** WARNING: HOT GAS LAYER DOESNOT FORM,

1 37H DUE TO STRONG FORCED AIR VENTILATION,

2 /, 26X, 45H ARTIFICIAL SOLUTION IS PROVIDED **ee.•*

GOTO 9000

C

C IF HGL IS FORMED, THE ONLY POSSIBLE STEADY STATE WILL BE ACHIEVED

C IS WHEN THE WHOLE ROOM IS FILLED UP WITH HOT GAS

C

500 ZD = 0.

DG = RHGT

C

C THE SIDE WALL AREA WILL BE LARGE COMPARE TO THE CEILING

C THEREFORE, THE ROOM SURFACE AREA IS RESPONSIBLE FOR HEAT

C TRANSFER INSTEAD OF CEILING ONLY

C

C AN EXTRA AMOUNT OF HOT GAS WILL FLOW OUT OF THE ROOM DUE TO

C PRESSURE DIFFERENT MEXTRA + WVOUT = THDOT + MVIN

C = TMDOT + CFV/RTEMP

C

C THE ROOM IS ASSUMED TO BE RECTANGULAR IN SHAPE

C IF OTHER SHAPE IS CONSIDERED, THE FOLLOWING STATEMENT

C HAS TO BE CHANGED ACCORDINGLY

C

- 185 -
RAREA = ACEIL + AWALL

Al = (HCEIL*RAREA + 2.*l.E3*(TMDOT + CFV/RTEMP))/RADCON/RAREA

A2 = (-TQDOTC - TCEIL*HCEIL*RAREA - RADCON*RAREA.TCEIL**4

1 - 2.*l.E3*(TMDOT + CFV/RTEMP))/RADCON/RAREA

TG = RADEQ(AI, A2)

WIN = TMDOT + CFV/RTEMP

GOTO 9000

C

C THE FOLLOWING PROCEDURES ARE TO BE EXECUTED WHEN OPENINGS ARE

C LARGE ENOUGH TO PROVIDE FREE AIR VENTILATION

C

C SINCE TG > RTEMP, FH MUST BE GREATER THAN FC TO GIVE WVOUT > 0

C OTHERWISE STATEMENT 6000 WILL BE EXECUTED WITHOUT TESTING THE

C FOLLOWING CONDITIONS.

C

4000 IF ((FC.GT.FH).OR.(VFV.LT.1.E-3)) GOTO 6000

IF (FH.EQ.0.) GOTO 6000

C

C WITH THE PRESENT OF FORCED VENTILATION, THE NEUTRAL PLANE OF

C THE HOT GAS LAYER MAY BE FORKED IN THE DOOR SOFFIT REGION

C

C WPLDH = PLUME MASS FLOW AT ZD=DHGT-ZOA

C

WPLDH = PLUCON*(DHGT - ZOA)**(5./3.)

WVOUT1 = CFV*(FH/TGMAX - FC/RTEMP)

IF (WPLDH.GE.WVOUT1) GOTO 6000

C

C IF WPLDH > WVOUT1 THEN THE HGL FORMS UNDER THE DOORWAY(GOTO 6000)

C ELSE HGL EITHER FORMS IN THE DOOR SOFFIT REGION OR

C DOES NOT FORM AT ALL

C

IF (WPLRH.GE.WVOUT) GOTO 5000

C

C ELSE, ONLY CEILING JET WILL BE PRESENT AND A WARNING MESSAGE

C WILL BE PRINTED

C

GOTO 800

C

C NEUTRAL PLANE FORMS AT DHGZRHGT

c

5000 TG = TGMAX

ZD = (WVOUTl/PLUCON)'**0.6 + ZOA

DG = RHGT - ZD

WIN = WVOUTI

WRITE (NWRITE, 720)

720 FORMAT(3X,48H**-********* WARNING: HOT GAS LAYER FORM IN THE,

1 56H DOOR SOFFIT REGION DUE TO STRONG FORCED AIR VENTILATION,

2 I, 26X, 45H ARTIFICIAL SOLUTION IS PROVIDED ***'*,•:-*)

GOTO 9000

C

C WHEN THE ABOVE CONDITIONS DO NOT HOLD, THEN THE HGL FORMS AT

C DHGT>ZD>O.

C

C 2/3*1.18*(19.8)'**.5 = 3.483

- 186 -
C

6000 FLOCON = 3.483*DWID'SQRT(RTEMP)

C INITIAL GUESS VALUE IS CHOSEN TO SOLVE FOR THREE NON-LINEAR

C SIMULTANEOUSLY EQUATIONS

C

TGLOW = RTEMP + (TGMAX - RTEMP)/1O.

C

C SUBROUTINE CNEWTN IS CALLED TO SOLVE FOR THE MINIMUM ALLOWABLE

C HOT GAS LAYER TEMPERATURE

C

CALL CNEWTN(TGLOW, 1,TGMAX,RTEMP,NWRITE)

IF (LEND) GOTO 9900

IF (LSMALL) GOTO 8000

IF (TGLOW.LT.RTEMP) TGLOW r RTEMP

C

C SECOND GUESS VALUE IS ASSIGNED TO CALCULATE THE HOT GAS LAYER

C TEMPERATURE

C

TG = TGLOW + 5.

C

C SUBROUTINE CNEWTN IS CALLED TO SOLVE FOR THE HOT GAS LAYER

C TEMPERATURE BY SOLVING THE MASS BALANCE EQUATION OF THE HOT GAS

C LAYER USING EITHER NEWTON-RAPHSON OR BISECTION METHOD

C

CALL CNEWTN(TG,2 ,TGKAX,TGLOW,NWRITE)

IF (LEND) GOTO 9900

IF (LSMALL) GOTO 8000

C

C THE FINAL ESTIMATE OF THE HOT GAS LAYER PROPERTIES IS COMPUTED:

C

CALL CGASHT (TG, ZN, ZD)

IF (LSMALL) GOTO 8000-

WFL = PLUCON*ZD**(5./3.)

WIN = WFL

DG = RHGT - ZD - ZOA

GOTO 9000

8000 WIN = WPLRH

DG = 0.

ZD = RHGT - ZOA

TG = TPLRH

WRITE (NWRITE, 8010)

8010 FORMAT(3X,49H** *****A' .WARNING: HOT GAS LAYER DOESNOT FORM,

1 24H DUE TO WEAK FIRE SOURCE,

2 /, 26X, 45H ARTIFICIAL SOLUTION IS PROVIDED ***"***)

9000 IF (WIN.LE.0) WIN = (1. - FC)*CFV/RTEMP + TMDOT

IF (TG.LT.RTEMP) TG = RTEMP

C

C QCEIL HAS BEEN CHANGED TO ACCOMODATE THE INTRODUCTION OF GAS

C EMMISSIVITY AND THE ASSUMPTION OF GREY GAS PROPERTIES

C

C OLD VERSION:

C EX1 = EXP(-1.5*GABSRP*DG)

C QCEIL = 5.6697E-8*(EPS*EXI*TCEIL"'*4 C 1 (1.-

FL*EX1)*TG**4) + WREFL*IQEXTC*EXI**2

C

- 187 -
C NEW VERSION:

C

GTRANS 1. - GEMS

QCEIL = RADCON*GTRANS*TCEIL**4 + (GEMS*5.6697E-8*(1.

1 GTRANS) - RADCON*GTRANS)*TG**4

2 QEXTC*(1. - RADCON/5.6697E-8)*GTRANS**2

9900 RETURN

END

- 188 -
C -

C SUBROUTINE CNEWTN PERFORMS THE ACTUAL NEWTON-RAPHSON ITERATION

C SCHEME TO SOLVE FOR THE REQUIRED ESTIMATION OF THE HOT GAS LAYER -

C PROPERTIES. BISECTION METHOD WILL BE EMPLOYED IF THE UPDATED -

C ESTIKATON IS OUT OF THE PERMISSIBLE BOUNDARIES

C

C -------------------------------------------------------------------

SUBROUTINE CNEWTN(TGUESS, IEQN, THAX, THIN, NWRITE)

IMPLICIT LOGICAL (L)

COMMON /ALL/

1

2

3

3

COMMON /GAS/

COMMON /VENT(

ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

RTEMP, TIME, TITLE(20),

ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

LEND, LROOM

CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

RADCON, TG, VFV, WHEAT, ZD, ZN,

LSMALL

/ AFUEL, AFUELO, CVA, CVAO, QMAX,

QTOT, QTOTO, QTOT1, QTOT2, THDOT, TMDOTO,

TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

NEURN, NBURNO,

LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

1

2

3

4

C

C IF TGUESS IS OUT OF BOUND, BISECTION METHOD IS USED

C

IF ((TGUESS .GE .TMAX) .OR. (TGUESS .LE.ThIN))

1 TGUESS = (TMAX + TMIN)/2.

ICOUNT = 0

DO 8000 1=1,30

ICOUNT = ICOUNT + I

CALL CSOLVE (TGUESS, FTG ,DFTG, IEQN, NWRITE)

IF (LEND.OR.LSMALL) GOTO 9000

DELTAX = FTG/DFTG

TGNEW = TGUESS - DELTAX

LTEST = .FALSE.

IF ( TGNEW.LT.TMAX) GOTO 1500

LTEST -. TRUE.

C

C IF LTEST = TRUE THEN BISECTION METHOD WILL BE USED TO SOLVE FOR

C THE REQUIRED ROOT

C

TGNEW = (TGUESS + TMAX)/2.

1500 IF (TGNEW.GT.TMIN) GOTO 2000

LTEST = .TRUE.

TGNEW = (TGUESS + TMIN)/2.

2000 IF (ABS(TGUESS - TGNEW).LE.O.1) GOTO 9000

TGUESS = TGNEW

IF (ICOUNT.EQ.30) GOTO 8500

IF (LTEST.OR.(ABS(DELTAX).GT.0.1)) GOTO 8000

RETURN

8000 CONTINUE

8500 WRITE(NWRITE, 8600)

8600 FORMAT(/,43H1** *****r-"WARNING: CONVERGENCE LIMIT EXCEEDS,

- 189 -
I 47H, SOLUTION PROVIDED IS THE BEST-GUESS********.**)

9000 RETURN

END

- 190 -
C

C SUBROUTINE CSOLVE COMPUTES F(ZN-ZD) AND DF(ZN-ZD)/DTG WHICH ARE

C USED TO CALCULATE THE MINIMUM ALLOWABLE HOT GAS LAYER TEMPERATURE, -

C OR F(TG) AND DF(TG)/DTG WHICH ARE USED TO SOLVE FOR THE HOT GAS

C LAYER TEMPERATURE. THE DERIVATIVE OF THE CORRESPONDING FUNCTIONS -

C ARE COMPUTED BY USING THE FIRST PRINCIPLE OF DIFFERENTIATION:

C LIM (F(H+DH) - F(H-DH))/2DH = DF/DH

C

C--------------------------------------------------------------------

SUBROUTINE CSOLVE(TSOLVE, FN, DFN, IEQN, NWRITE)

IMPLICIT LOGICAL (L)

DIMENSION TGUESS(3), ZDTG(3), ZNTG(3), DWIN(3), DWOUT(3), CTGFN(3)

COMMON /ALL/

1

2

3

COMMON /GAS/

1

2

3

ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

RTEMP, TIME, TITLE(20),

ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

LEND, LROOM

CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

RADCON, TG, VFV, WHEAT, ZD, ZN,

LSMALL

COMMON /VENTC/ AFUEL, AFUELO, CVA, CVAO, QMAX,

1 QTOT, QTOTO, QTOT1, QTOT2, TMDOT, TMDOTO,

2 TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

3 NBURN, NBURNO,

4 LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

DELTA = 1.E-2

TGUESS(1) = TSOLVE

TGUESS(2) = TSOLVE - DELTA

TGUESS(3) = TSOLVE + DELTA

DO 100 1-1,3

CALL CGASHT(TGUESS(I) ,ZNTG(I) ,ZDTG(I))

IF (LSMALL) GOTO 5000

100 CONTINUE

C

C IF IEQN = 1 THE SUBROUTINE COMPUTES F(ZN - ZD)

C IF IEQN = 2 THE SUBROUTINE COMPUTES F(TG)

C

IF (IEQN.EQ.2) GOTO 1000

C

C SOLVE FN = ZN(TG) - ZD(TG) = 0

C

FN ZNTG(1) - ZDTG(1)

DFN = (ZNTG(3) - ZDTG(3) - ZNTG(2) + ZDTG(2))/(2.*DELTA)

RETURN

1000 DO 1100 I=1,3

C

C SOLVE CTGFN = SUMIN + TMDOT - SUMOUT

C

IF (ZNTG(I).LT.ZDTG(I)) GOTO 2000

DWIN(I) = DCFIN*FLOCON*SQRT((1./RTEMP - I./TGUESS(I))*(ZNTG(I)

1 - ZDTG(I)))*(ZNTG(I) + .5*ZDTG(I))

DWOUT(I) = DCFOUT*FLOCON*SQRT(1./TGUESS(I) - RTEMP/TGUESS(I)*.*.v2)

1 *(DHGT - ZNTG(I))**1.5

- 191 -
1100 CTGFN(I) = DWIN(I) + TMDOT - DWOUT(I) + FH-CFV*(I./RTEMP -

1 1./TGUESS(I))

FN = CTGFN(1)

DFN = (CTGFN(3) - CTGFN(2))/(2.*DELTA)

RETURN

2000 LEND = .TRUE.

WRITE(NWRITE, 3000)

3000 FORMAT(/,53H**¶.:.AA:.*-WARNING: ZD, ZN GOES OUT OF BOUNDS IN CSOLVE,

1 33H, EXECUTION TEPtINATED D• ,)

5000 RETURN

END

- 192 -
C --

C

C SUBROUTINE CGASHT FINDS THE CURRENT ZN AND ZN IN TERMS OF THE -

C CURRENT HOT GAS LAYER TEMPERATURE

C

C---------------------------------------------------------------

SUBROUTINE CGASHT(TGUESS, ZNTG, ZDTG)

IMPLICIT LOGICAL (L)

COMMON /ALL/ ACEIL, AWALL, CALTEM, DELT, FCTR(15), FLCF, HROOM,

1 RTEMP, TIME, TITLE(20),

2 ICEIL, IJOB, INCHCK, INITG, IOUTPT, MOUTPT(17),

3 LEND, LROOM

COMMON /GAS/ CFV, CVENT, DCFIN, DCFOUT, DG, DHGT, DWID,

1 FC, FH, FLOCON, GABSRP, GEMS, HCEIL, PLCF, PLUCON,

2 RADCON, TG, VFV, WHEAT, ZD, ZN,

3 LSMALL

COMMON /VENTC/ AFUEL, AFUELO, CVA, CVAO, QMAX,

1 QTOT, QTOTO, QTOT1, QTOT2, TMDOT, TMDOTO,

2 TMDOTS, TQDOT, TQDOTC, WIN, ZOA,

3 NBURN, NBURNO,

4 LDECAY, LFLUX1, LFLUX2, LVENT, LVCONT

C

C THE HEIGHT OF THE PLANES ARE FOUND AS A FUNCTION OF HOT GAS TEMPERATURE

C

QGAIN = TQDOTC - ACEIL*HCEIL*TGUESS - ACEIL*RADCON*TGUESS**4

1 + WHEAT

IF ((QGAIN.LE.10.).OR.(TGUESS.LE.RTEMP)) GOTO 50

WDOUT = QGAIN/I.E3/(TGUESS - RTEMP) - CFV*(FH/TGUESS + FC/RTEMP)

IF (WDOUT.LT.O.) GOTO 50

ZDTG = (WDOUT/PLUCON)**0.6

ZNTG = DHGT - (WDOUT/DCFOUT/FLOCON/SQRT(l./TGUESS

1 - RTEMP/TGUESS*"2))**(2./3.)

RETURN

50 LSMALL = .TRUE.

RETURN

END

- 193 -

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NRC FORM 335 U S. NUCLEAR REGULATORY COMMISSION 1. REPORT NUMBER (A sipeed bV DOC"

'" '"NT.REG/CR-4 566

BIBLIOGRAPHIC DATA SHEET 01uMLE/-1005,

4 TITLE AND SUBTITLE (Add Volume No.. ,,9aoper.arel i 2. ILeave blankJI

COMPBPN III - A Computer Code for Modeling Compartment

Fires 3. RECIPIENTS ACCESSION NO,

A :UTHOR(SI Vincent Ho 5. DATE REPORT COMPLETED

Nathan Stu Io4NTH YEAR

- eorge Agostolakis November 1985

9 PERFORMING ORGANIZATION NAME AND MAILING ADDRESS (Include Zop Codel DATE REPORT ISSUED

Oak Ridge National Laboratory MONTH J YEAR

Engineering Physics and Mathematics Division April 1986

Building 6025 6. (Leave •a,,k)

P.O. Box X J

Oak Ridg Tevn e Tge 8. fLeave biank)

12 %PONSORING ORGANIZATION NAME AND MAILING ADDRESS (Include Z~p Code)

Division of Risk Analysis and Operations 10. PROJECT/TASKiWORK UNIT NO

Office of Nuclear Regulatory Research 11. FIN NO.

U. S. Nuclear Regulatory Commission _

Washington, D. C. 20555 B0493

I

1.1 TYPE USý REVoH1

NUREG/CR I PERIOD COVERED (inclusive dJewsl 1 1.* : pp E ,..&tta n.e .. ~.ee I .r.. ,nn. .. t,,c@ t I "Oulco

114. Leave olanki I I I

5f01STRACT 1700Q ovoids o' lessi

The computer code COMPBRN III deterministically models the behvior of compartment

fires. This code is an improvement of the original COHPBRN codes. It employs a different

air entrainment model and numerical scheme to estimate properties of the ceiling hot gas

layer model. Moreover, COMPBRN III incorporates a number of improvements in shape factor

calculations and error checking, which distinguish it from the COMPBRN II code. This

report presents the ceiling hot gas layer model employed by COMPBRN III as well as

several other modifications.* Information necessary te run COMPBRN III, including

descriptions of required input and resulting output, are also presented. Simulation of

experiments and a sample problem are included to demonstrate the usage of the code.

.1

*1

I

Ila DESCRIPTORS I

I

.. I" 1-%%* .131. Ila$$

*U.S. GOVERNMENT PRINTING OFFICE 1986--631-056/40018